Entries |
Document | Title | Date |
20080199300 | MEANS TO REDUCE SECONDARY FLOW IN A CENTRIFUGAL PUMP - A technique improves the pumping performance of a centrifugal pump in a cost-effective manner. The centrifugal pump comprises a pumping component having one or more vanes defining fluid flow paths. A passage is formed through at least one vane such that an end of the passage is exposed to a low energy flow, i.e. secondary flow, region. Each passage enables the flow of a small amount of fluid from the low energy region to an opposite side of the vane to reduce the secondary flow effects and improve pumping efficiency. | 08-21-2008 |
20080206039 | TIP CLEARANCE CONTROL SYSTEM - The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal P | 08-28-2008 |
20080219831 | Pipe flow-driven power generator - A pipe flow-driven power generator includes a vane wheel pivotally mounted in a water chamber in a water pipe and rotatable by a flow of water running through the water pipe, a dynamo pivotally mounted on the outside of the water chamber and coupled to the vane wheel through a transmission gear set for generating electricity upon running of water through the water pipe, and a storage battery for storing electricity generated by the dynamo. | 09-11-2008 |
20080226439 | Blade variation in dependence of the degree of throttling on fluid-flow machine - A method for the variation of at least one blade row of a fluid-flow machine, in which, in dependence of the actual operating point, in addition to an aerodynamic speed, at least one further quantity pertinent to the position of the operating point in the family of characteristics of the fluid-flow machine is employed for control. | 09-18-2008 |
20080232949 | Turbomachine Having an Axially Displaceable Rotor - The invention relates to a compressor, which is axially flowed through, for a gas turbine having an axially displaceable rotor. An annular flow channel, which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface and an inner delimiting surface on the rotor. A stationary ring comprised of guide profiles and at least one ring comprised of moving profiles attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade is located opposite an axial section of one of both delimiting surfaces while forming a radial gap. The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor. To this end, the invention provides that the size of the radial gap between the end of each moving or guide blade and the opposite axial section of the delimiting surface is constant at least over the path of displacement of the rotor, and the radial gap extends parallel to the rotation axis of the rotor. | 09-25-2008 |
20080232950 | METHOD FOR DETECTING ROTATING STALL IN A COMPRESSOR - A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall. | 09-25-2008 |
20080247860 | Hydroelectric power plant and method of generating power - A hydroelectric power plant includes a fluid intake, a fluid exhaust, a fluid engine located in a fluid path between the fluid intake and the fluid exhaust, and a fluid accelerating device located adjacent to the fluid exhaust. The fluid accelerating device is configured to accelerate fluid past the fluid exhaust and is approximately shaped as a portion of a cone. | 10-09-2008 |
20080279675 | OPERATION OF AN AIRCRAFT ENGINE AFTER EMERGENCY SHUTDOWN - A method of emergency operation of an aircraft turbofan engine during an aircraft flight is provided. The engine includes a fan shaft with a fan, and an electric motor/generator mounted for rotation therewith. The method includes shutting down the engine while allowing the engine to windmill, operating the electric motor/generator to rotate the shaft at a determined windmilling speed which is desired for the fan shaft, and operating the engine at the desired windmilling speed for substantially a remainder of the aircraft flight. | 11-13-2008 |
20080279676 | Turbine Anti-Rotating Stall Schedule - A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window. | 11-13-2008 |
20090035121 | Fluid Flow Modulation and Measurement - In fluid flow measurement applications, apparatus and associated systems, computer program products, and methods may include a positive displacement fluid flow meter having an actuator to control fluid flow through the meter, and further having two or more rotating members with substantially parallel axes that rotate in response to the actuator and to fluid flow through the meter. In various implementations, the actuator may promote and/or retard a fluid flow being measured through the meter. In some examples, the fluid flow meter may operate as a pump to controllably increase a line pressure, controllably regulate a fluid flow rate by opposing rotation of the rotating members, substantially stop a fluid flow, and/or reverse a base fluid flow direction. In an illustrative example, the meter may operate to accurately monitor and control fluid flow (e.g., fluid pressure, velocity, and/or volume) before, during, and/or after a line break. | 02-05-2009 |
20090035122 | CENTRIFUGAL COMPRESSOR, IMPELLER AND OPERATING METHOD OF THE SAME - A centrifugal compressor is equipped with an impeller having a blade angle distribution that makes it possible to achieve a relatively wide operating range. The blade angle of a shroud side facing a circular plate of a blade is termed a first angle and a blade angle of a hub side disposed at the circular plate is a second angle. The shroud side is formed in a curved shape having an angle distribution from a front area in a shaft direction toward a centrifugal direction in which the first angle is the local maximum point before a substantially middle portion and the local minimum point after the substantially middle point. The hub side is formed in a curved shape having an angle distribution from the front area in the shaft direction toward the centrifugal direction in which the second angle is the maximum local point before the substantially middle portion. | 02-05-2009 |
20090047116 | System and method for loads reduction in a horizontal-axis wind turbine using upwind information - A system and method provide a proactive mechanism to control pitching of the blades of a wind turbine to compensate for rotor imbalance during normal operation by pitching the blades individually or asymmetrically, based on turbulent wind gust measurements in front of the rotor, determined before it reaches the rotor blades. | 02-19-2009 |
20090053035 | APPARATUS AND METHOD FOR REDUCING ECCENTRICITY AND OUT-OF-ROUNDNESS IN TURBINES - A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided. | 02-26-2009 |
20090060704 | ACTIVE FLOW CONTROL FOR NACELLE INLET - The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition. | 03-05-2009 |
20090060705 | Sanitary Air Jet Device - A sanitary air jet device [ | 03-05-2009 |
20090060706 | BALL BEARING AND PUMP FOR CRYOGENIC USE - A ball bearing for use in cryogenic applications has an inner ring and an outer ring that define a raceway between them, and there is a set of rolling balls in the raceway with slug ball separators between adjacent rolling balls. The bearing may be used in a pump for cryogenic fluids such as LNG, LOX, LH2, etc. | 03-05-2009 |
20090067978 | VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes a ring of turbine nozzle segments each having paired turbine vanes. Turbine throat area is modulated by rotating each rotational turbine vanes about an axis of rotation which is located such that rotation changes the turbine throat area concurrently between one rotational stator vane and two adjacent fixed turbine vanes. Each paired turbine vane doublet includes at least one rotational turbine vane between two fixed turbine vanes. | 03-12-2009 |
20090081019 | Systems and Methods for Controlling the Stability of a Water Brake Dynamometer - A system for stabilizing a water brake including at least two rotor disks, a chamber of the water brake for containing water positioned between the at least two rotor disks, a pressure measuring device for measuring a partial pressure in the chamber, and an air injection device for injecting air into the chamber to increase the partial pressure in the chamber. | 03-26-2009 |
20090087298 | COMPRESSOR AND HEAT PUMP SYSTEM - A centrifugal turbocompressor including an open-type impeller and a casing compresses a gaseous body that condenses into a liquid. The compressor suppresses erosion due to accumulation of a liquid on a casing surface in the compressor. Such accumulation is possible during the starting time of the compressor, if the gaseous body that has come into contact with the casing condenses on the surface of the casing and changes into liquid droplets, centrifugal force may cause the droplets to accumulate on the surface of the casing positioned outside an impeller, and thus to grow into coarser and larger droplets or a liquid film. If the blade tips of the impeller rotating at high speed scrape the droplets or the film upward, erosion of the blade tips is liable to result. | 04-02-2009 |
20090087299 | FOIL GAS BEARING SUPPORTED HIGH TEMPERATURE CENTRIFUGAL BLOWER AND METHOD FOR COOLING THEREOF - This invention provides a blower design capable of high temperature operation due to use of a self-sustaining cooling scheme through a sealed motor housing in which a cooling circuit can be created, and the use of a thermal barrier across which a temperature gradient may be formed. The thermal barrier may be formed by a thermal choke plate assembly positioned between a hot side and a cold side of the blower to dissipate heat conducted from the hot side. Alternatively, the thermal barrier may be formed by an internal fan ring provided with the blower's rotating assembly to dissipate heat conducted from the blower's impeller. The thermal choke plate assembly and the fan ring may further be used in combination to block heat transfer by all modes between a hot side and a cold side of the blower. | 04-02-2009 |
20090097959 | Optimization method for power generation systems - Apparatus for controlling the power output efficiency of a power generation system based on an operator input. A processor is coupled to the input means and (i) receives the generated operator command, (ii) receives a plurality of detected ambient air conditions, (iii) receives a plurality of detected engine. performance parameters, (iv) determines first and second engine control commands based on the received pilot thrust command, the detected ambient environmental conditions, and the engine performance parameters, and (v) outputs control commands to optimize the efficiency of the power generation system. | 04-16-2009 |
20090110536 | Blade outer air seal with improved thermomechanical fatigue life - A blade outer air seal for a gas turbine has an abradable coating with a substantially uniform thickness during service use. Prior to being placed in service, the abradable coating has a central portion with a greater thickness than leading and trailing portions. When placed in service, the blade outer air seal is positioned so that the central portion of the abradable coating with the greater thickness is located in a blade rub path of the turbine blades. As a result of abrasion in the blade rub path, the thickness of the central portion of the abradable coating is reduced so that it becomes substantially similar to the thickness of the leading and trailing portions. | 04-30-2009 |
20090116951 | METHOD AND APPARATUS FOR FAN SHAFT BEARING LUBRICATION - A lubrication system for a bearing assembly includes a fan shaft with a plurality of conduits, a first bearing rotatably supporting the fan shaft, and a second bearing rotatably supporting the fan shaft where the second bearing is axially spaced from the first bearing. The plurality of conduits includes at least a first conduit aligned with the first bearing and a second conduit aligned with the second bearing. A spray bar includes a plurality of supply orifices that direct lubricating fluid to the first and second bearings via at least the first and second conduits. | 05-07-2009 |
20090129913 | Computer Room Environmental Conditioning Unit with Translatable Blowers - A conditioning unit can allow the blower to be easily translated from a first operable position in the conditioning unit to a second operable position external to the conditioning unit. The translation of the blower does not require the disconnection of the blower and, accordingly, does not require that the blower be disconnected and reconnected to the control system. Such capability can facilitate the installation of the conditioning unit into a variety of applications and allows the purchaser to customize the blower location based on the desired performance. The ability to customize the installation of the conditioning unit without requiring disconnection and reconnection of the blower can reduce the cost and expense associated with the installation into differing applications. | 05-21-2009 |
20090136334 | Bearing and Shaft Wheel Assembly Balancing Techniques and Equipment for Turbochargers - An exemplary clamp for clamping a bearing cartridge and shaft subassembly of a turbocharger includes an upper portion, a lower portion where the upper portion and the lower portion form a bore having a bore diameter sized to clamp a bearing cartridge and a fluid passage defined in part by the upper portion, the lower portion or the upper portion and the lower portion where the fluid passage includes an opening to the bore. Various other exemplary devices, systems, methods, etc., are also disclosed. | 05-28-2009 |
20090155042 | MULTI FUNCTIONAL PUMP FOR PUMPING MOLTEN METAL - The present invention features a multi-functional pump for pumping molten metal, which includes a base that is submerged in molten metal having at least two impeller chambers. The base includes one or more inlet openings and one or more outlet openings. Each outlet opening leads from one of the impeller chambers. The invention enables the impeller to be moved to a position to rotate in either impeller chamber or while straddling impeller chambers. This enables the pump to have the versatility to operate in a circulation mode; a transfer mode; two or more circulation modes; two or more transfer modes; and a combination of transfer and circulation modes. The impeller chambers can be stacked over each other and the impeller can be moved vertically in and between impeller chambers. Inventive vaned or barrel type impellers can be used to facilitate pumping while straddling impeller chambers, in view of an elongated bearing member on the impeller that maintains position relative to a bearing ring attached to the base or an inlet protector sleeve. The multifunctional pump of the invention enables infinite adjustment of the impeller using a programmable logic controller that results in positioning of the impeller at any of various locations in the base to achieve any desired output. The inventive pump is ideally suited for use in die casting and scrap submergence applications. Also featured is a method of operating the multifunctional pump of the present invention. | 06-18-2009 |
20090162186 | Method and apparatus for vibration-based automatic condition monitoring of a wind turbine - Method and apparatus for vibration-based automatic condition monitoring of a wind turbine, comprising the steps of: determining a set of vibration measurement values of the wind turbine; calculating a frequency spectrum of the set of vibration measurement values; calculating a cepstrum of the frequency spectrum; selecting at least one quefrency in the cepstrum, and detecting an alarm condition based upon an amplitude of the cepstrum at the selected quefrency, and a wind turbine therefor. | 06-25-2009 |
20090180858 | Method to Prevent Brinelling Wear of Slot and Pin Assembly - A method to prevent brinelling wear of a slot and pin assembly of an adjustable inlet guide vane mechanism includes: providing a compressor having the adjustable inlet guide vane mechanism including a control ring with a plurality of tapered slots positioned around a circumference of the control ring; providing a plurality of tapered pin/lever arm assemblies each comprising a tapered pin having a tapered body with a first threaded end and a second end, a lever arm extending perpendicularly from the second end of the tapered body of the tapered pin and a vane coupled to an end of the lever arm; positioning the tapered pin of the tapered pin/lever arm assembly within each of the plurality of tapered slots such that the first threaded end of the tapered body of the tapered pin extends through the tapered slot; positioning a washer and spring over the first threaded end of the tapered pin of each of the tapered pin/lever arm assemblies; and securing the tapered pin of each of the tapered pin/lever arm assemblies within each of the tapered slots by coupling a nut to the first threaded end of the tapered pin of each of the tapered pin/lever arm assemblies. The tapered body of the tapered pin of each of the tapered pin/lever arm assemblies and each of the plurality of tapered slots are shaped to ensure contact between the tapered body of the tapered pin and the tapered slot thereby preventing brinelling wear. | 07-16-2009 |
20090185893 | Radial inner diameter metering plate - A nozzle assembly for directing cooling fluid in a vane comprising a hollow airfoil containing at least two cooling chambers. The chambers are separated by a generally radial rib. A metering plate mount is attached to the rib. A metering plate, having at least one aperture for tuning the cooling fluid flow within the airfoil, is adjacent the metering plate mount. | 07-23-2009 |
20090185894 | Turbine Casing - The turbine casing as described herein may include a first section flange, a second section flange, the first section flange and the second section flange meeting at a joint, and a heat sink positioned about the joint. | 07-23-2009 |
20090196730 | Gas turbine with a compressor with self-healing abradable coating - A gas turbine with a compressor includes at least one row of blades, with the blades having a free end each, with a self-healing abradable coating being provided adjacent to the free end of the blades on an annular casing area and/or an annular drum area. | 08-06-2009 |
20090196731 | METHOD AND APPARATUS FOR STARTING SUPERSONIC COMPRESSORS - A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated. | 08-06-2009 |
20090196732 | Turbomachine, in Particular a Gas Turbine - The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The aim of said invention is to develop a device and a method for the turbo-machine making it possible to reduce the size of a radial split of the turbo-machine in order to obtain greater degree of efficiency. The inventive turbo-machine comprises a rotor rotationally mounted in the case of the turbo-machine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbo-machine rotor by heating fluid flowing there-through are also disclosed. | 08-06-2009 |
20090202337 | METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger. | 08-13-2009 |
20090220329 | ROTOR AND NOZZLE ASSEMBLY FOR A RADIAL TURBINE AND METHOD OF OPERATION - A rotor for a radial flow turbine has an impulse chamber ( | 09-03-2009 |
20090238675 | AIRFOIL THERMAL MANAGEMENT WITH MICROCIRCUIT COOLING - A turbine engine component, such as a turbine engine blade, has an airfoil portion with a pressure side wall and a suction side wall, a plurality of ribs extending between the pressure side wall and the suction side wall, and a plurality of supply cavities located between the ribs. The component further has an arrangement for cooling the airfoil portion. The cooling arrangement comprises a first cooling circuit embedded within the suction side wall for convectively cooling the suction side wall, a second cooling circuit embedded within the pressure side wall for cooling the pressure side wall, and a third passageway for increasing a temperature of at least one of the ribs by conduction. | 09-24-2009 |
20090245997 | METHOD AND DEVICE TO AVOID TURBO INSTABILITY IN A GAS TURBINE ENGINE | 10-01-2009 |
20090280002 | Method and system for determining gas turbine tip clearance - A system for sensing at least one physical characteristic associated with an engine including a turbine having a plurality of blades turning inside a casing, the system including: a pressure sensor coupled substantially adjacent to the casing and including at least one output; a port in the turbine casing for communicating a pressure indicative of a clearance between the blades and casing to the pressure sensor; a cooling cavity substantially surrounding the pressure sensor; and, an inlet for receiving fluid from the engine and feeding the fluid to the cooling cavity to cool the pressure sensor; wherein, the pressure sensor output is indicative of the clearance between the blades and casing. | 11-12-2009 |
20090290971 | SEAL MONITORING AND CONTROL SYSTEM - A seal monitoring and control system for a gas lubricated non-contacting seal includes various sensors providing signals to a programmable logic control system. The control system is disposed to determine a presence of an anomalous operating condition of the seal, for example, based on phase, relative position of rotor to stator or other signals in combination provided by the various sensors to provide an output signal, which in one embodiment performs at least one mitigating process to correct the anomalous operating condition by adjusting at least one operating parameter of the seal. | 11-26-2009 |
20090297330 | Blade clearance arrangement - Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap adjustment systems have been relatively course. By provision of a winding through which a specific electrical current is passed in order to create electro-magnetic force for displacement of an armature associated with a seal forming part of the casing it is possible to adjust the gap between that seal and a tip part of a rotating blade assembly. Normally a blade gap monitoring technique is used in association with specific operational requirements with respect to the gap by the control in order to determine the electrical current presented to the winding. As a fail-safe measure a permanent magnet or bias or some other form can be provided to ensure displacement to a fail-safe position with an adequate blade gap clearance for continued operation should there be power failure or an excess electrical current presented to the winding. | 12-03-2009 |
20090297331 | TURBOMACHINE CASING INCLUDING A DEVICE FOR PREVENTING INSTABILITY DURING CONTACT BETWEEN THE CASING AND THE ROTOR - The invention relates to a cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel, the casing including a device for preventing instability during contact between the casing and the bladed wheel. In characteristic manner, said device comprises a succession of elements disposed around the circumference of the casing, and presenting between two adjacent elements, different stiffnesses, the number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan. | 12-03-2009 |
20090297332 | Wind Diverter - Apparatuses and methods are provided for a wind diverter at least partially encircling a wind turbine support column to direct the wind from an area around a wind turbine to the rotor blades of the wind turbine. The wind diverter may also reduce turbulence and increases the laminar flow of the airstream delivered to the rotor blades. Additionally, the wind diverter increases both the volume of air and the velocity of the airstream reaching the rotor so as to increase the rotor speed. Increasing the rotor speed increases the energy available to the wind turbine. Energy increases as the cube of the rotor speed and the increased energy produces an increase in the power generated by the wind turbine. The wind diverter also allows a wind turbine to begin producing energy at lower initial wind speeds due to the concentration of air. | 12-03-2009 |
20090304492 | Blower systems and methods having multiple outlets - A blower system comprising a housing and a fan assembly. The housing defines a housing chamber, at least one inlet opening, a primary outlet opening, and a secondary outlet opening. The fan assembly is mounted within the housing chamber. Operation of the fan assembly draws air into the housing chamber through the at least one inlet opening and forces air out of the housing chamber through at least one of the primary outlet opening and the secondary outlet opening. | 12-10-2009 |
20090304493 | Axially oriented shingle face seal for turbine rotor and related method - An axial seal arrangement is provided between a rotor and a stator. The rotor is provided with a first disk having a substantially flat sealing face surface. The stator is provided with a second annular disk surrounding the rotor, supporting proximate ends of a plurality of axially extending, flexible, compliant seal elements arranged in an annular array of plural, circumferentially-overlapping radial layers to thereby provide a tortuous path for radially outward leakage flow. | 12-10-2009 |
20090304494 | Counter-vortex paired film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall for providing film cooling to the exterior face of the wall, and a second film cooling passage extending through the wall adjacent to the first film cooling passage for providing film cooling to the exterior face of the wall. The first film passage includes a first vortex-generating structure for inducing a vortex in a first rotational direction in a cooling fluid passing therethrough, and the second film passage includes a second vortex-generating structure for inducing a vortex in a second rotational direction in a cooling fluid passing therethrough. The first and second rotational directions are substantially opposite one another. | 12-10-2009 |
20090317227 | AIRFOIL EMBODYING MIXED LOADING CONVENTIONS - A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications. | 12-24-2009 |
20090317228 | APPARATUS AND METHOD FOR CONTROLLING A BLADE TIP CLEARANCE FOR A COMPRESSOR - An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained. | 12-24-2009 |
20090317229 | INTEGRATED ACTUATOR MODULE FOR GAS TURBINE ENGINE - An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing. | 12-24-2009 |
20090317230 | TURBINE SYSTEM FOR UTILIZING THE ENERGY OF OCEANIC WAVES - A turbine system for the utilization of the energy of oceanic waves includes: a chamber that is provided with an opening at its lower end and at its upper end respectively; a duct that is open at both ends for guiding a stream of air, the lower end of the chamber being designated to be submerged in ocean water, and the opening of the upper end being connected with one of the ends of the duct; an energy unit that is mounted coaxial to such and surrounded by the duct; and a device for cleaning the rotor blades of deposits or for preventing the formation of deposits on the rotor blades. | 12-24-2009 |
20090324381 | AIR BEARING TURBO COOLING AIR FLOW REGULATING DEVICE - A cooling air flow regulating device for controlling the flow of cooling air to an air bearing may comprise a housing with a piston and a spring disposed within. When the pressure of the cooling air is high, the piston is forced out of the path of the cooling air and into an open position. As the pressure of the cooling air decreases, the spring forces the piston back into the path of the cooling air, effectively blocking the flow of cooling air to the air bearing. The cooling air flow regulating device of the present invention may be useful for controlling the cooling of air bearings in turbochargers of turbocharged engine, where at low engine speed, cooling air is not required for air bearings. Methods for using the cooling air flow regulating device of the present invention are also provided. | 12-31-2009 |
20090324382 | Torque-based sensor and control method for varying gas-liquid fractions of fluids for turbomachines - A torque-based sensor and control method for detecting varying gas-liquid fractions of a fluid entering a turbomachine that operates a fluid of varying liquid phases and compositions and using information about the actual gas-liquid fraction to set a control algorithm so that it can change the torque and therefore the rotation speed of the turbomachine to operate at safer conditions or conditions with higher efficiency or higher power output. | 12-31-2009 |
20100003121 | VARIABLE AREA FAN NOZZLE FOR ACCOMMODATING A FOREIGN OBJECT STRIKE EVENT - A gas turbine engine system includes a fan ( | 01-07-2010 |
20100008755 | METHOD OF EXTENDING TUBING LIFE OF A PERISTALTIC PUMP - A method is provided for extending useful life of tubing of a peristaltic pump. The method can comprise switching inlet and discharge hoses between respective inlet and outlet ends of the tubing of the peristaltic pump, and reversing a direction of rotation of a rotor of the peristaltic pump. In implementations of methods disclosed herein, the useful life of the tubing of a peristaltic pump can be approximately doubled. | 01-14-2010 |
20100028126 | APPARATUS AND METHOD FOR CONTROLLING A ROTARY MACHINE USING PRESSURIZED GAS - An apparatus and method for controlling rotating bladed machinery by using a source of pressurized gas is disclosed. The source of pressurized gas, such as air, imparts braking torque on a turbomachinery component through the use of one or more impinging orifices or jets. The orientation of the jets is such that the transfer of momentum from the pressurized gas results in a force substantially opposite the direction of rotation of the turbomachinery component. This transfer of momentum from the pressurized gas allows for a controlling torque to be applied to the turbomachinery component without the need of mechanical and/or electrical devices applying torque to the rotating shaft. | 02-04-2010 |
20100028127 | TURBINE ENGINE LUBRICATION METHOD AND SYSTEM - A method and a system for lubricating a turbomachine including an oil tank, an oil feed pump, an oil/air separator, and at least two enclosures closed by air flow rate seals, each including a low outlet and housing shaft-supporting rolling bearings. The method injects oil from the tank into the enclosures by the pump to lubricate the bearings, introduces compressed air at a low flow rate into the enclosures via the seals to pressurize the enclosures, recuperates all of the air and the oil introduced into the enclosures via their low outlet, uses gravity and the pressurization of the enclosures to convey the oil/air mixture as recovered in this way to the oil/air separator, separates the oil and the air of the mixture by the oil/air separator, returns the oil to the tank, and exhausts the air to outside the turbomachine. | 02-04-2010 |
20100028128 | COMPONENT WITH DIAGONALLY EXTENDING RECESSES IN THE SURFACE AND PROCESS FOR OPERATING A TURBINE - The invention is related to a component of a turbine machine with diagonally extending recesses in the surface of the component. Thermally stressed components of a turbine machine can be protected against excessive heat input by active cooling or by applying thermal insulation layers. The invention increases the effect by providing diagonally extending slots in the surface of the component. | 02-04-2010 |
20100034634 | ACOUSTIC VISCOUS DAMPER FOR CENTRIFUGAL GAS COMPRESSOR - An acoustic viscous damper for a compressor including a porous liner located within the discharge duct, the porous liner having a plurality of holes for passage of a purge working fluid therethrough into the discharge duct. | 02-11-2010 |
20100034635 | Predictive Model Based Control System for Heavy Duty Gas Turbines - A system for controlling the clearance between a turbine blade and the turbine casing that includes an impingement cooling manifold attached to a turbine casing, a temperature sensing device for determining the temperature of the turbine casing, a blower, a control system logic for determining the setting temperature of the casing, and a controller for controlling the blower, wherein the blower forces air onto the impingement cooling manifold to cool the casing towards the setting temperature and control the clearance. | 02-11-2010 |
20100040453 | APPARATUS AND METHOD FOR CONTROLLING A COMPRESSOR - A compressor comprises a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the compressor further comprising at least one plasma actuator for suppressing rotating stall inception of the compressor, the at least one plasma actuator being mounted adjacent to the blade tips. | 02-18-2010 |
20100054909 | VARIABLE TURBO SUPERCHARGER AND METHOD OF DRIVING THE SOME - A hydraulic servo drive device for driving a swing mechanism of a variable geometry turbocharger includes a servo piston connected to a driveshaft of the swing mechanism and a pilot spool that is accommodated in a center hole of the servo piston and slides by pilot pressure. A first hydraulic chamber to and from which pressure oil flows are provided in a housing. The servo piston separately includes a pressure port for introducing pressure oil from an outside, a first piston port for intercommunicating the center hole and the first hydraulic chamber, a second piston port for intercommunicating the center hole and the second hydraulic chamber, and a return port for exiting pressure oil. | 03-04-2010 |
20100061836 | Process for producing a turbine blade or vane with an oxide on a metallic layer, use of such a turbine blade or vane, a turbine and a method for operating a turbine - A process for producing a component of a gas turbine having a substrate with a metallic layer is provided. The metallic layer is a MCrAlX layer which is treated at temperatures elevated above the operating temperature, by at least 50° C., so that the oxidation and corrosion behavior are improved. In particular a MCrAlX of the type, NiCoCrAlX is used. | 03-11-2010 |
20100068028 | REDUCED TIP CLEARANCE LOSSES IN AXIAL FLOW FANS - An axial fan assembly including a casing wall with a forward facing step formed therein and a fan rotor with blade tips, each having an aft facing step which radially overlaps the casing step so as to reduce the clearance backflow loss in the assembly. A vane is attached to the suction side of each of the blade tips with the vane having an aft facing step which radially overlaps the casing forward facing step to promote further reduction of clearance backflow. Variations on the invention include the option of an additional inlet bellmouth piece that further restricts the clearance flow and wedges integral to the casing step to improved flow stability. | 03-18-2010 |
20100068029 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 03-18-2010 |
20100074725 | METHOD FOR CONTROLLING A TURPOCOMPRESSOR - Method for controlling a turbocompressor, whereby a compressed air line ( | 03-25-2010 |
20100086393 | TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind/Water Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind/water turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass fluid flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 04-08-2010 |
20100092275 | HOUSEHOLD APPLIANCE INCLUDING A FAN SPEED CONTROLLER - A household appliance including a fan speed controller, and a method of controlling fan speed of a household appliance, are provided. The system includes a fan speed controller that cut a voltage to the fan motor, measures an electromotive force (EMF) of the fan motor at a predetermined time after the cutting of the voltage to the fan motor, and compares the measured electromotive force (EMF) to a table. | 04-15-2010 |
20100104415 | RISERLESS TRANSFER PUMP AND MIXER/PRE-MELTER FOR MOLTEN METAL APPLICATIONS - A pump for processing molten metal having an enlarged tubular body which houses a centrifugal pump at its bottom end. The bottom end has a parabolic shape which receives the ejected molten metal from the impeller and forms a vortex within the tubular body. The pump is controlled to cause the vortex to climb up the inner wall of the body up to and out of an outlet formed in the upper end of the body. A radial vane impeller is formed in the back plate of the impeller. When the impeller is rotated, solid particles introduced into the body are accelerated radially by the back plate impeller into the vortex. | 04-29-2010 |
20100111666 | Method for fan control according to the position of a device and device implementing the procedure - The present invention relates to a control method for the operation of a fan equipping an electronic device. A determination step detects the vertical or horizontal position of the electronic device. The fan is not started up during the powering up of the device while the device is in a vertical position. The flow of air produced by the “fireplace” effect in the device in a vertical position suffices to ensure correct ventilation. According to an improvement the device has a sensor measuring the internal temperature of the device, whatever the position of the device, the fan being started up from a determined temperature. The present invention relates also to a device implementing the method. | 05-06-2010 |
20100111667 | RING FAN AND SHROUD AIR GUIDE SYSTEM - A ring fan and shroud guide system which includes a rotating fan member with a conical outer ring and a cylindrical shroud member overlapping at least a portion of the outer ring. A plurality of guide vanes are provided in the shroud which minimize the tangential velocity component of the air flow entering the tip-gap region and provide improved air flow through the system. The guide vanes can have a curved configuration. | 05-06-2010 |
20100129192 | COMPRESSION METHOD AND MEANS - The invention is a compression method having characteristics of smooth compression and internal cooling of the gas. Embodiments of the invention employ a cylindrical chamber and an orbiting rotor to create a moving duct or chamber whose walls converge, relative to a static gas packet drawn into the moving duct, at a ‘pinch point’. Preferably the closing speed of the walls is subsonic and the speed of the pinch point is supersonic. This enables high pressure to co-exist, at the narrowing end of the duct, with low pressure elsewhere in the duct, because of the pressure information barrier produced by the supersonic advance of the pinch point. The invention also discloses means for adjusting the running clearance between the cylinder and the rotor, and means for counterbalancing the rotor. | 05-27-2010 |
20100129193 | SYSTEM AND METHOD FOR EXTRACTING POWER FROM FLUID USING A TESLA-TYPE BLADELESS TURBINE - Smooth, preferably variable-sweep fluid collection device surfaces disposed into opposition with wind, river, surf, ocean or tidal currents generate enhanced velocity fluid flows at length driven into onboard work-extracting disc turbines at advantageous angles of attack. Keyed to shafts turning freely through optionally extendable volutes, disc turbines comprising a dense population of smooth, axially fixed or adjustably spaced discs conducting preferably laminar flow between adjacent elements develop significant torque through boundary layer adhesion and viscous shear-stress between fluid layers. Exhaust of disc turbine throughput into divergent channels drafting into external currents of initially higher than ambient velocity and lower pressure may reduce turbine discharge backpressure, rapidly clear system throughput, and allow normally disadvantageous drag to be utilized to develop greater work generation. Gainfully turning with, instead of at odds to natural or anthropogenic currents provided, disc turbines utilized as disclosed may provide unprecedented renewable energy from fluids in motion. | 05-27-2010 |
20100135765 | PUMPS - A pump assembly and components therefor including an impeller which has flow inducer elements on an inner surface of a front shroud thereof, a flow directing device or strainer having passageways for delivering material to the impeller and at least one flow circulating passageway and a pump casing having an intake section with flow distribution vanes in the region of a feed opening adjacent the intake section. | 06-03-2010 |
20100135766 | KINETIC HYDROPOWER GENERATION SYSTEM AND INTAKE THEREFORE - A kinetic hydropower generation system has a turbine and a generator coupled to the turbine. An underwater intake nozzle assembly is fluidly coupled to the turbine. For one embodiment, an underwater tower nozzle may be fluidly coupled between the turbine and the underwater intake nozzle assembly. The underwater intake nozzle assembly may include a collector and a converging nozzle. | 06-03-2010 |
20100135767 | Variable and Centrifugal Flywheel and Centrifugal Clutch - A flywheel is attached to a shaft of a turbine. As the shaft rotates, the flywheel swings outwards away from the shaft and regulates the angular velocity of the rotating shaft. In an embodiment, there are multiple flywheels attached to the shaft. In another embodiment there is a first flywheel that controls a second flywheel. | 06-03-2010 |
20100143090 | COOLING SYSTEM AND METHOD FOR A TURBOMACHINE - An embodiment of the present invention provides a cooling system for a flame detection system of a turbomachine. An embodiment of the present invention may provide a control system for the operation of the cooling system. The control system may be configured to automatically and/or continuously monitor the cooling system to determine whether the position of the at least one valve should be changed. | 06-10-2010 |
20100143091 | VACUUM GENERATOR SEAL - A vacuum generator seal can comprise an upstream annular cavity adjacent to the upstream side of the bearing, a downstream annular cavity adjacent to the downstream side of the bearing, and at least one drain slot positioned on the upstream side of the bearing housing. The vacuum generator seal can include a retainer that at least partially defines the upstream annular cavity. The retainer may be in contact with the bearing housing and may have a tight clearance with the impeller hub. The retainer along with a supply of grease packed within the annular cavities can seal the bearing; and the drain slot can direct water and waste away from the bearing and towards the scroll. | 06-10-2010 |
20100143092 | Power-Generating Turbine in a Rotor-Stator Arrangement - A rotor blade for a horizontal axis wind turbine is provided. The rotor blade includes a fixing section for fixing the rotor blade to a rotary shaft of a rotor of the horizontal axis wind turbine. Furthermore, the rotor blade includes a geometrically adjusted section with a root end. The rotor blade extends from the fixing section to the root end. A section of the root end of the geometrically adjusted section and a section of a guide panel of a stator of the horizontal axis wind turbine closest to the root end are substantially coplanar. | 06-10-2010 |
20100172738 | Method of Matching Thermal Response Rates Between A Stator and a Rotor and Fluidic Thermal Switch for Use Therewith - A turbine power generation system with thermal response rate matching provided by one or more fluidic thermal switches and a method for mitigating restart pinch during a hot restart. The turbine power generating system includes a stator and a rotor situated within the casing of the stator. Auxiliary heat is provided to the stator casing during shutdown operations from a heat source via one or more fluidic thermal switch which are configured to provide localized heating to portions of the stator casing subject to restart pinch. The fluidic thermal switch includes two solid, thermal conductors having fluid contacting elements spatially separated within an insulated vessel. A highly conductive and capacitive fluid is provided to the insulated vessel when localized heating is needed. | 07-08-2010 |
20100178152 | Compressor Clearance Control System Using Turbine Exhaust - The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine. | 07-15-2010 |
20100178153 | Turbine Having Compact Inflow Housing Thanks to Internal Control Valves - A turbine having an inflow housing is provided. The turbine includes an inlet for an inflowing working fluid, wherein the inlet can be closed by a quick closing valve, a plurality of control valves and at least two nozzle groups. The flow of the working fluid is controllable by the inlet into the nozzle groups via the control valves. Furthermore, the inlet can be connected via an inlet line to the first nozzle group, wherein the inlet line is guided through the primary control valve such that the flow of the working fluid along the inlet line can be controlled using the primary control valve. The secondary control valve connects the first nozzle group to the second nozzle group such that the flow of the working fluid from the first nozzle group into the second nozzle group may be controlled using the secondary control valve. | 07-15-2010 |
20100178154 | Method And System For Controlling A Turbocompressor Group - A method for controlling at least two turbocompressors ( | 07-15-2010 |
20100178155 | STEAM TURBINE AND COOLING METHOD THEREOF - A steam turbine includes a casing, a rotor arranged inside the casing so as to extend in an axial direction of the casing, a rotor disk integrally formed with the rotor, a rotor-side implanting portion formed in the rotor disk, a plurality of moving blades arranged on the rotor disk in a circumferential direction of the rotor, and a moving blade-side implanting portion formed in the moving blade, in which the moving blade-side implanting portions of the moving blades are engaged with the rotor-side implanting portions, respectively. A cooling medium flows through a gap formed at least on a blade portion side of the moving blade among gaps formed between the moving blade-side implanting portions and the rotor-side implanting portions. | 07-15-2010 |
20100183423 | Injecting Processing Fluid While Writing Data - An apparatus and associated method is provided for injecting a processing fluid in a device that operably rotates a disc stack. A fluid injector has a nozzle defining an outlet sized to longitudinally span the disc stack to operably direct the processing fluid toward the disc stack. The nozzle also has a flow rate feature that operably directs a first flow rate of the processing fluid from the nozzle into a space adjacent a storage surface of a first disc of the disc stack and that directs a substantially different second flow rate of the processing fluid from the nozzle into another space adjacent a storage surface of a second disc of the disc stack. | 07-22-2010 |
20100183424 | Electrodynamic Control of Blade Clearance Leakage Loss in Turbomachinery Applications - Electrodynamic control of fluid leakage loss is provided. Embodiments utilize electrohydrodynamic (EHD) principles to control and/or reduce leakage flow in turbomachinery. Electrodes can be used to provide a flow actuation mechanism inside the clearance gap for generating discharge. The electrodes can be positioned to have geometric asymmetry. Embodiments provide the electrodes on a turbine blade. The blade can have a DC power that can function as a square pulsed DC wave with the duty cycle equal to the blade passing frequency and the stator can be grounded. In an embodiment, the stator can have the actuator of the electrode-insulator assembly attached to the inside. In one embodiment, the actuators can be arranged just on the stator or casing. The phase and power supply to individual electrodes can be adapted as needed. In one embodiment, the phase can be lagged for accurate control of leakage flow. The control of the power supply to the electrodes can involve a closed control loop that monitors tip gap size. | 07-22-2010 |
20100189542 | TURBINE ARRANGEMENT AND METHOD OF COOLING A SHROUD LOCATED AT THE TIP OF A TURBINE BLADE - A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurised combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud. | 07-29-2010 |
20100196137 | CLOSED-LOOP CONTROL FOR A GAS TURBINE WITH ACTIVELY STABILIZED COMPRESSOR - A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor. | 08-05-2010 |
20100202869 | HUBLESS WINDMILL - Systems, apparatus and methods for generating power from fluid motion, such as wind are provided. The apparatus is a wing-shaped airfoil with cup-shaped indentations that allow the airfoil to harness wind energy throughout a wide range of wind speeds and from different wind directions. The indentations harness wind energy at low wind speeds while the wing-shape generates a lifting force at high wind speeds to harness wind energy. The system comprises one or more of the devices configured in a hollow, generally cylindrical, shape and connected to a ring frame. The system rotates about an axis running through the center of the ring frame. The rotational motion of the system generates electrical power via a generator. The method is a method for generating electrical power from the rotational motion of the system. | 08-12-2010 |
20100202870 | METHOD AND APPARATUS FOR LUBRICATING A THRUST BEARING FOR A ROTATING MACHINE USING PUMPAGE - A fluid machine and method of operating the same includes a pump portion having a pump impeller chamber, a pump inlet and a pump outlet and a turbine portion having a turbine impeller chamber, a turbine inlet and a turbine outlet. A shaft extends between the pump impeller chamber and the turbine impeller chamber. The shaft has a shaft passage therethrough. A turbine impeller is coupled to the impeller end of the shaft disposed within the impeller chamber. The turbine impeller has vanes at least one of which comprises a vane passage therethrough. A thrust bearing is in fluid communication with said vane passage. | 08-12-2010 |
20100202871 | Gearbox For A Wind Turbine, A Method Of Converting Wind Energy And Use Of A Gearbox - A gearbox for a wind turbine. The gearbox includes at least one first epicyclical gear stage, at least one second gear stage, and a torque transferring shaft including a shaft part and a connection part, wherein the torque transferring shaft is adapted for connecting a first gear of the first epicyclical gear stage with a second gear of the second gear stage and wherein the torque transferring shaft is connected to the second gear stage via the connection part to form a torque-transferring connection area between the connection part and the second gear stage and wherein the outer diameter of the shaft part of the torque transferring shaft is smaller than an inner diameter of the connection area between said torque transferring shaft and said second gear stage. | 08-12-2010 |
20100221095 | STEAM TURBINE AND METHOD FOR EXTRACTING MOISTURE FROM A STEAM TURBINE - A steam turbine is disclosed which includes a casing containing a plurality of expansion stages, each including stator and rotor airfoils. Downstream of the stator airfoils of one or more expansion stages, the casing includes a slot arranged to receive moisture that concentrates on an end wall of the stator airfoils and discharge it to the outside. Each end wall has a side portion facing the slot having a variable radial obstruction in a tangential direction, in order to define with the slot a passage through which the moisture may pass that is smaller or closed at the suction side and larger at the pressure side of the stator blades, to at least partially prevent the dry steam from entering the slot at the suction side of the blade. | 09-02-2010 |
20100221096 | COMPUTER SYSTEM AND PROGRAM PRODUCT FOR CONTROLLING VIBRATIONS - The computer programmable system and program product include first program instructions for actively driving a first imbalance mass concentration rotor and a second imbalance mass concentration rotor at a vibration canceling rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a rotating net force vector to inhibit periodic vibrations. The program product includes second program instructions to opposingly orient the first imbalance mass concentration relative to the second imbalance mass concentration during a starting stopping rotation speed less than the vibration canceling rotation frequency. The system includes a fault mode control protocol for controlling a rotation of the rotors during a sensed failure of the rotating assembly vibration control system. | 09-02-2010 |
20100232928 | METHOD OF OPTIMIZING A DUCTED ANTI-TORQUE ROTOR OF A ROTORCRAFT, IN PARTICULAR A HELICOPTER, TO MINIMIZE ACOUSTIC ANNOYANCE, AND A DUCTED ANTI-TORQUE ROTOR OBTAINED THEREBY - The present invention relates to a method of minimizing the noise emitted by a ducted rail rotor anti-torque device at a frequency FE and perceived at a frequency FP, in which method the diameter D, the number of blades b, and the tangential speed U of the rotor are determined so that the perceived frequency FP is less than or equal to the bottom limit frequency FL of a predetermined one-third frequency octave centered on a frequency FC. | 09-16-2010 |
20100232929 | COOLING ARRANGEMENT FOR A TURBINE ENGINE COMPONENT - An example turbine component cooling arrangement includes a film plate having a plurality of film channels extending from film channel entrances on a first side of the film plate to corresponding film channel exits on an opposing second side of the film plate. The arrangement also includes an impingement plate establishing a plurality of impingement channels. The impingement plate is spaced a distance from the film plate. The plurality of impingement channels are configured to direct a fluid across the distance to contact the film plate between adjacent ones of the film channel entrances. In one example, the distance from the film plate to the impingement plate is between two and four times more than diameter of one of the impingement channels. | 09-16-2010 |
20100239409 | Method of Using and Reconstructing a Film-Cooling Augmentation Device for a Turbine Airfoil - A method of using a film-cooling insert for a turbine airfoil is disclosed. The method includes forming an airfoil sidewall having a film-cooling hole that extends between an airfoil cooling circuit and an airfoil surface. The method also includes forming a film-cooling insert and disposing the film-cooling insert in the film-cooling hole. A method of reconstructing a film-cooling insert for a turbine airfoil is also disclosed. The method includes removing a remnant of a film-cooling insert from a film-cooling hole of a turbine airfoil. The method also includes disposing a second film-cooling insert in the film-cooling hole. | 09-23-2010 |
20100239410 | COMPRESSOR - A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between said passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width. | 09-23-2010 |
20100247282 | SYSTEMS, METHODS, AND APPARATUS FOR PASSIVE PURGE FLOW CONTROL IN A TURBINE - Systems, methods and apparatus for passive purge flow control in a turbine are provided. Various embodiments of the invention include providing a path for air to flow to a bore of a rotor with a plurality of stacked wheels. The air flow path includes at least one inlet hole on a rotor structure and a plurality of holes in at least some of the stacked wheels. The method further involves control of air flow to the at least one inlet hole based at least in part on axial deflection between the rotor and an associated stator during the gas turbine operation. Additionally, a portion of the air flowing into the inlet hole is directed through the plurality of holes in the at least some of the stacked wheels to purge the rotor. | 09-30-2010 |
20100247283 | METHOD AND APPARATUS FOR CLEARANCE CONTROL - A system, in certain embodiments, includes a magnetic actuator configured to adjust a radial clearance between a housing and rotary blades via translational movement along a rotational axis. The system includes a controller configured to engage the magnetic actuator to adjust the radial clearance in response to feedback. | 09-30-2010 |
20100247284 | AIRFLOW INFLUENCING AIRFOIL FEATURE ARRAY - An example gas turbine engine airfoil includes an airfoil wall establishing a cavity that extends axially from an airfoil leading edge portion to an airfoil trailing edge portion and extends radially from an airfoil inner end to an airfoil outer end. The cavity is configured to receive a baffle that is spaced from the airfoil leading edge portion such that an impingement cooling area is established between the airfoil leading edge portion and the baffle when the baffle is received within the cavity. An array of nonuniformly distributed features is disposed on the airfoil wall within the impingement cooling area. The features are configured to influence airflow within the impingement cooling area. | 09-30-2010 |
20100247285 | Systems and Methods for Providing Compressor Extraction Cooling - Embodiments of methods and apparatus for providing compressor extraction cooling are provided. According to one example embodiment, a method for providing compressor extraction cooling in a gas turbine comprising a compressor and a turbine section can be provided. The method can include providing a cooling medium. The method can include extracting air from a compressor associated with a gas turbine. The method can also include introducing the cooling medium to the compressor extraction air, wherein the compressor extraction air is cooled by the cooling medium prior to or during introduction to the turbine section. | 09-30-2010 |
20100247286 | FEEDING FILM COOLING HOLES FROM SEAL SLOTS - A cooling arrangement for a first stage nozzle of a turbine includes a slot formed in a forward face of the first stage nozzle, the slot opening in a direction facing a combustor transition piece and adapted to receive a flange portion of a seal extending between the first stage nozzle and the transition piece. The slot has a closed end formed with at least one cooling cavity provided with at least one cooling passageway extending between the cavity and an external surface of the first stage nozzle. | 09-30-2010 |
20100247287 | NOZZLE ADJUSTING MECHANISM AND METHOD - Method and nozzle adjustment mechanism for adjusting a flow of a fluid. The nozzle adjustment mechanism includes a fixed ring; at least a vane connected to the fixed ring by a pivot pin and configured to rotate with the pivot pin; an adjusting ring rotatably connected to the fixed ring and configured to rotate around a longitudinal axis of the nozzle adjustment mechanism; and a connection mechanism connecting the at least a vane to the adjusting ring and configured to move the at least a vane when the adjusting ring is rotated, the connection mechanism including a lever component and a link component connected to each other. The lever component is connected to the at least a vane and the link component is connected to the adjusting ring. | 09-30-2010 |
20100247288 | FLUID ELASTOMERIC DAMPER ASSEMBLY INCLUDING INTERNAL PUMPING MECHANISM AND VOLUME COMPENSATOR - Rotary wing system with a rotating blade rotating about a rotation axis. The system includes a fluid damper with a damper fluid for controlling a troublesome motion. The fluid damper has an inboard end and an outboard end, the damper inboard end attached to a first rotary wing system inboard member proximate the rotation axis and the outboard end attached to a second rotary wing system outboard member distal from the rotation axis. The fluid damper contains a damper fluid volume in at least a first working chamber which is worked by a relative motion between said first rotary wing system inboard member and said second rotary wing system outboard member to control the troublesome motion. The damper includes a volume compensator channel in fluid communication with the damper fluid, the volume compensator channel including a centrifugal force mass member movable along a volume compensating length of the volume compensating channel, wherein a rotation about the rotation axis forces the centrifugal force mass member towards an outboard end of the volume compensating channel and pushes damper fluid from the volume compensator channel towards the at least first working chamber. | 09-30-2010 |
20100254797 | ENDWALL WITH LEADING-EDGE HUMP - An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped area forward the airfoil leading edge portion. | 10-07-2010 |
20100260591 | Spanwise split variable guide vane and related method - Accordingly, in one aspect, the invention relates to a variable guide vane for an axial flow compressor comprising: a first radially outer vane section; and a second radially inner vane section; the first and second vane sections angularly adjustable relative to each other about a longitudinal radial axis of the vane. | 10-14-2010 |
20100260592 | GUIDED WIND KITE FOR INCREASED WIND TURBINE POWER OUTPUT - A wind turbine system includes a kite positioned upstream to a turbine to direct wind to the turbine, thereby increasing revolutions per minutes and power output of the turbine. | 10-14-2010 |
20100260593 | FLUID TURBINE DEVICES AND METHODS RELATED TO FLUID TURBINE DEVICES - Fluid turbine devices and methods related to fluid turbine devices are disclosed herein. One example method includes deflecting a first portion of a fluid flow from a return path of at least a portion of a vertical blade assembly, while permitting a second portion of the fluid flow to enter a drive path of the vertical blade assembly. One example fluid turbine device includes a vertical blade assembly having multiple blades and a shroud rotatable relative to the vertical blade assembly. The shroud includes a leading edge portion for deflecting a first portion of a fluid flow from entering a return path of at least a portion of the vertical blade assembly and a portion defining multiple openings configured to permit fluid from within a compartment defined by the vertical blade assembly to exhaust out of the return path. | 10-14-2010 |
20100266382 | WIND TURBINE WITH BOUNDARY LAYER CONTROL - The invention relates to a wind turbine comprising a rotor with a hub and turbine blades, and further comprising a boundary layer control system for the turbine blades. A plurality of pressure chambers is located in the blade distributed over the length of the blade. Each pressure chamber is in communication with the outside of the blade through one or more corresponding openings in the outer surface of the turbine blade. Furthermore a suction channel and a blow channel extend inside the blade for supplying an underpressure and an overpressure respectively to the pressure chamber, each pressure chamber being connected to at least one of said channels through an air passage in which an actively operable valve is located. The valve is connected to a control unit for selectively bringing the pressure chamber into communication with or close it off from said channel(s) so as to blow air out of the pressure chamber or suck air into the pressure chamber through the corresponding opening(s) in the blade surface. | 10-21-2010 |
20100278628 | Turbine with variable number of nozzles - A gas turbine generally exhibits a substantial deterioration in efficiency against fluctuation of gas flow rate. A variable nozzle turbine is a solution for this disadvantage; however, it has also another disadvantage of low efficiency under partial load conditions and a large number of heat-resistant moving components. A variable nozzle number turbine according to this invention overcomes these disadvantages. The turbine includes nozzles for injecting gas to rotor blades. The nozzles include inlet ports circumferentially arranged so as to be grouped into a group and an opening and closing valve disposed thereover so as to be commonly functioned therefore. This arrangement realizes a gas turbine with no deterioration of efficiency against fluctuation of gas inflow rate by only one heat-resistant moving component additionally installed. The variable nozzle number turbine according to this invention also realizes a turbine compressor with no surge limit when used as a regenerator. These turbines further realizes a small-sized gas turbine with improved fuel economy under partial load conditions and a turbocharger for regenerating electric power as well as improving efficiency of a displacement engine used therewith. It is to be noted that the inventor is ready for grant of working license. | 11-04-2010 |
20100278629 | Vertical Multi-Phased Wind Turbine System - A rotational axis multi-phased wind turbine power generating system is disclosed. A differential pressure is created by utilizing the prevailing wind, and air from the prevailing wind is directed into air blades for the creation of power. Optimally, the air blades directly utilize the prevailing wind in combination with the created differential pressure to create power. An adjustable air scoop, adjustable exit drag curtain or barrier, orienting systems, and air flow directing dampers are disclosed. | 11-04-2010 |
20100284780 | Method of Operating a Compressor - A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode. | 11-11-2010 |
20100284781 | MITIGATING MECHANICAL VIBRATIONS CAUSED BY A FAN IN A COMPUTER SYSTEM - One embodiment provides a system that mitigates vibrations caused by cooling fans in a computer system. More specifically, the system includes a cooling fan mechanically coupled to the chassis of the computer system, wherein vibrations generated by the cooling fan are coupled to the chassis. The system also includes an actuation mechanism that creates a relative displacement between the cooling fan and the chassis when a control signal is applied to the actuation mechanism. The system additionally includes a detection mechanism which detects the relative displacement and generates a feedback signal which represents the relative displacement. The system further includes a control signal generation mechanism which converts the feedback signal into the control signal, which is subsequently applied to the actuation mechanism. When the control signal is applied to the actuation mechanism, the relative displacement between the cooling fan and the chassis vibrationally decouples the cooling fan from the chassis. | 11-11-2010 |
20100284782 | STEAM TURBINE, SYSTEM, AND METHOD OF OPERATION - Embodiments of the invention relate generally to steam turbines, steam turbine systems, and methods for their operation and, more particularly, to high-pressure-intermediate-pressure (HPIP) steam turbine configurations having pressure drop-limited seals and exhibiting reduced mid-packing and/or end-packing leakage. One embodiment of the invention provides a combined high-pressure-intermediate-pressure (HPIP) steam turbine comprising: a high-pressure section; an intermediate-pressure section sharing a common rotor with the high-pressure section; at least one packing ring disposed along a length of the rotor and between the high-pressure section and the intermediate-pressure section; and at least one conduit having a first end disposed adjacent a packing ring and a second end disposed adjacent a steampath stage of the high-pressure section. | 11-11-2010 |
20100284783 | Diffuser of natural aromas for refrigerated environments - A diffuser of natural aromas for refrigerated environments includes a dome designed to build up aromas, and houses a cartridge containing coffee as a natural base product, which is covered by a waterproofed mesh to protect the substance from moisture. The dome is coupled to a base that hosts an isolated battery compartment. Windows cut in the base are covered with a dehumidifying net allowing refrigerated and dried air to penetrate the base's inner surface. An electronic fan connected to the battery compartment is mounted on an overhang inside the base to convey air from the refrigerated environment through and outside the dome, creating an airflow cycle. A method of providing a way to neutralize unpleasant odors within refrigerated environments by diffusing natural aromas and a method of providing beneficial effects to a subject when natural aromas are inhaled may be implemented using the above described diffuser. | 11-11-2010 |
20100296910 | THERMAL SYSTEM FOR A WORKING MEMBER OF A POWER PLANT - A working member for a power plant is disclosed herein. The working member includes a body defining at least one working surface of the working member. The at least one working surface is operable to contact a working fluid. The body also includes at least one inner surface opposite the at least one working surface. The working member also includes an interior chamber defined within at least part of the body proximate to the at least one working surface. The working member also includes at least one inlet to the interior chamber. The working member also includes at least one outlet from the interior chamber. The working member also includes a quantity of open-cell foam positioned in the interior chamber between the inlet and the outlet. The quantity of open-cell foam fills less than all of the interior chamber such that at least one empty space is defined in the interior chamber between the at least one inner surface and the quantity of open-cell foam. | 11-25-2010 |
20100296911 | Active Casing Alignment Control System And Method - A gas turbine with an active clearance control system includes a plurality of actuators circumferentially spaced between an inner shroud and an outer casing. The actuators are configured to eccentrically displace the shroud relative to the outer casing. A plurality of sensors circumferentially spaced around the shroud detect a parameter that is indicative of an eccentricity between the rotor and shroud as the rotor rotates within the shroud. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the shroud to compensate for eccentricities detected between the rotor and shroud. | 11-25-2010 |
20100296912 | Active Rotor Alignment Control System And Method - A rotating machine, such as a gas turbine, includes an active rotor alignment clearance control system wherein a plurality of actuators are circumferentially spaced around at least one rotor shaft bearing. The actuators are configured to eccentrically displace the bearing, and thus the rotor shaft, relative to stationary outer casing structure. A plurality of sensors are circumferentially spaced around a component of the casing structure, such as an inner shroud, and measure a parameter indicative of an eccentricity, such as blade tip clearance between the rotor blades and the structure, as the rotor rotates within the structure. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the rotor by moving the shaft bearing to compensate for eccentricities detected between the rotor and casing structure. | 11-25-2010 |
20100303604 | SYSTEM AND METHOD TO REDUCE ACOUSTIC SIGNATURE USING PROFILED STAGE DESIGN - To reduce noise and thereby increase turbine efficiency, the end walls and airfoils of a turbine are designed to reduce or eliminate radial pressure gradients on rotor blades and their incipient secondary flow vortices which may noisily excite downstream blade and vane rows. Instead of generating inefficient noise, the fluid energy may be properly directed into the shaft as efficient work. | 12-02-2010 |
20100303605 | REMOVAL OF MOISTURE FROM PROCESS GAS - Embodiments of the disclosure may provide an exemplary method for operating a compressor system, wherein the method may include cooling a process gas containing water vapor to a first temperature. The water vapor may form a condensate at the first temperature, and cooling the process gas may produce residual heat. At least a portion of the condensate is removed from the process gas, wherein any portion of the condensate that is not removed is a remaining condensate. The remaining condensate may be heated to a second temperature with the residual heat, wherein the remaining condensate in the process gas evaporates at the second temperature. | 12-02-2010 |
20100303606 | TURBOMACHINE COMPRESSOR WHEEL MEMBER - A turbomachine includes a rotor assembly including a wheel member. The wheel member includes a first portion that extends to a second portion through an intermediate portion. The intermediate portion partially defines a first wheel space and a second wheel space. The wheel member further includes a rotor inertia belt member arranged at the second portion. The rotor inertia belt member includes an extraction air cavity. The extraction air cavity includes an inlet, a first plurality of extraction air passages each including an inlet section and an outlet section, the outlet section leading into the first wheel space, and a second plurality of extraction air passages each including an inlet portion and an outlet portion, the outlet portion leading into the second wheel space. | 12-02-2010 |
20100303607 | Turbine Exhaust Diffuser Flow Path with Region of Reduced Total Flow Area - An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub that has an upstream end and a downstream end. The outer boundary has a region in which the outer boundary extends radially inward toward the hub. The region can begin at a point that is substantially aligned with the downstream end of the hub or, alternatively, at a point that is proximately upstream of the downstream end of the hub. The region directs at least a portion of an exhaust flow in the diffuser toward the hub. As a result, the exhaust diffuser system and method can achieve the performance of a long hub system while enjoying the costs of a short hub system. | 12-02-2010 |
20100310353 | ROTOR CASING TREATMENT WITH RECESSED BAFFLES - A compressor rotor casing treatment comprises a plurality of axially spaced-apart circumferential grooves defined in the inner surface of the compressor casing adjacent the tips of the compressor rotor blades. A plurality of circumferentially spaced-apart recessed baffles projects from a bottom surface of each groove to a distance less than a full height of the groove. | 12-09-2010 |
20100310354 | TANDEM SEAL ARRANGEMENT WITH REVERSE FLOW SECONDARY SEAL - A process fluid communication system includes a fluid source in communication with a process seal and a gearbox seal to communicate a pumping medium into a turbomachinery housing and a gearbox housing through the process seal and the gearbox seal. | 12-09-2010 |
20100310355 | MOVING VERTICAL AXIS TURBINE FOIL - A new movable foil for accelerating the fluid hitting the blades of a vertical axis turbine is presented. | 12-09-2010 |
20100316484 | MECHANICAL JOINT FOR A GAS TURBINE ENGINE - A mechanical joint for a gas turbine engine includes:(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together. | 12-16-2010 |
20100322755 | USE OF NON-UNIFORM NOZZLE VANE SPACING TO REDUCE ACOUSTIC SIGNATURE - A stator for a turbomachine. The stator includes a plurality of nozzle vanes, with the distance between each of the plurality of nozzle vanes varying circumferentially around the stator in a repeating pattern configured to distribute a vibration energy over a plurality of side band vibration frequencies around a nominal passing frequency in a rotor. | 12-23-2010 |
20100329835 | AIRFOIL WITH HYBRID DRILLED AND CUTBACK TRAILING EDGE - An apparatus for a gas turbine engine includes an airfoil, a metering opening for metering a cooling fluid, a cutback slot configured to deliver the cooling fluid from the metering opening, and a cooling hole. The airfoil defines a trailing edge, opposite first and second faces, and a mean camber line. The cutback slot is defined along the first face of the airfoil adjacent to the trailing edge and offset from the mean camber line of the airfoil. The cooling hole has an outlet that is located at the trailing edge and substantially aligned with the mean camber line of the airfoil. The cooling hole delivers a portion of the cooling fluid from the metering opening. | 12-30-2010 |
20100329836 | METHOD OF OPERATING A HEATED GUIDE VANE ASSEMBLY - A method of operating a heated guide vane assembly for turbomachinery, the heated guide vane assembly including a plurality of guide vanes each having two major surfaces joined about their periphery by edges and an associated electric heater element secured to at least one major surface of the guide vanes. The method includes the steps of energizing heater elements on at least one of the guide vanes, de-energizing heater elements on at least one of the guide vanes, and energizing heater elements on at least one of the guide vanes which was not energized in the first energizing step. | 12-30-2010 |
20100329837 | SYSTEM AND METHOD FOR ALIGNING TURBINE COMPONENTS - Embodiments include a system having a turbine support key having a set of key segments selectively stackable together in a plurality of combinations to adjust a thickness between turbine supports based solely on a selection of the key segments from the set. | 12-30-2010 |
20100329838 | AERODYNAMIC PERFORMANCE ENHANCEMENTS USING DISCHARGE PLASMA ACTUATORS - The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing. | 12-30-2010 |
20100329839 | Screw Shaft Turbine Compressor and System - Disclosed herein are screw shaft turbine compressors having (i) a compressor section, (ii) a turbine section, (iii) a combustion section coupling to the compressor section and the turbine section, and (iv) a grooved shaft. The grooved shaft can include one or more grooves for providing fuel from the compressor section to the combustion section and for allowing exhaust to leave the combustion section and exit the turbine section. A method for generating different speed to torque ratios on the shaft and a system for generating torque on the shaft are further disclosed. | 12-30-2010 |
20110002769 | CENTRIFUGAL PUMP FOR DE-WATERING - A method of de-watering during intermittent dry running periods with a self-priming centrifugal pump is presented. Centrifugal pumps, as opposed to diaphragm pumps, are advantageous because they are less expensive and can provide greater capacity. The shaft seals are sensitive, however, to frictional heating when water flow is interrupted. In some situations, this fractional heating may desiccate self-priming. The inventive concept provides a continuous stream of pressurized water moving through the pump to cool the seal and sustain priming capability without substantially impairing the ability of the pump to resume wet operation. | 01-06-2011 |
20110002770 | COMPRESSOR - A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises inner and outer tubular walls extending away from the impeller wheel in an upstream direction and defining between them gas flow passage. A bleed passage between the gas flow passage and the impeller wheel is selectively opened and closed by movement of a sliding sleeve in a helical direction. | 01-06-2011 |
20110002771 | ROTOR BLADE OVER-TIP LEAKAGE CONTROL - A system is provided for controlling rotor blade over-tip leakage of a working fluid in rotating machine. The system has a circumferential row of rotor blades, and a circumferential row of seal segments for sealing with the radially outer tips of the rotor blades to reduce over-tip leakage of the working fluid. The seal segments have an inboard abradable layer which is adapted to be abraded by the blade tips to form a wear track for the blade tips. The system further has one or more tip wearing bodies which are adapted to wear down the blade tips. The thickness of the abradable layer and the cold build radial positions of the blade tips, seal segments and tip wearing bodies are arranged such that, during running-in of the machine, a wear track having a uniform radius is formed in the abradable layer by the blade tips, and the tip wearing bodies also wear down the blade tips to provide a uniform blade tip radius. | 01-06-2011 |
20110002772 | CONTROL DEVICE AND METHOD FOR AN AERODYNAMIC BRAKE OF A WIND ENERGY CONVERTER - A wear-free, self-contained control device for an aerodynamic emergency brake of a wind energy converter is presented that comprises multiple components in order to provide a most effective means to control the rotation of a vertical axis wind turbine by a brake, which is able to activate itself without external actuation in malfunction situations and is able to shut down the vertical axis wind turbine. Therefore, a mass element is utilised to store mechanical energy which in turn is used to deploy an aerodynamic braking operation. It also represents a means to control and limit the amount of torque, as absorbed by the turbine in high-wind conditions, and thus provides the ability to harvest electrical/mechanical energy, beyond the normal operational wind speeds of turbines. | 01-06-2011 |
20110008149 | BLOOD PUMP BEARINGS WITH SEPARATED CONTACT SURFACES - Rotary hydrodynamic blood pumps have been used to treat over a thousand patients. The Jarvik 2000 has supported a patient for seven years and uses blood immersed bearings washed by high flow to avoid excessive thrombus formation. This permits the pump to be very simple and small. Nonetheless, the present Jarvik 2000 bearings and all other mechanical blood immersed bearings of the prior art have a supporting structure that predisposes to thrombus adjacent to the bearings. The present invention provides a bearing structure that eliminates this predilection site for thrombus formation, and may provide indefinite thrombus free operation. The rotor of the preferred embodiment includes a tapered hub fabricated of wear resistant material supported by three posts at each end of the rotor, upon which the rotor rotates. Blood washes the unobstructed spaces between the posts to prevent the accumulation of a torus of thrombus that could enlarge excessively. | 01-13-2011 |
20110014028 | COMPRESSOR COOLING FOR TURBINE ENGINES - Systems, apparatuses and methods (“utilities”) for use in “internally” cooling the compressor of a gas turbine engine so as to approximate isothermal compression and thereby increase the power and/or efficiency of the engine. In one arrangement, a “cooling jacket” or heat exchanger having coolant circulating or passing therethrough may be mounted around an outer surface of the compressor to absorb heat or thermal energy generated from the compressor. In another arrangement, the stator blades of the compressor may include passages through which a coolant may be circulated or passed to absorb heat from air passing through the compressor. | 01-20-2011 |
20110020105 | NACELLE FLOW ASSEMBLY - A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume. | 01-27-2011 |
20110020106 | Blade containment structure - The fan duct of a ducted fan gas turbine engine has a fan case lined with a honeycomb structure that acts to absorb the energy of a separated part of a blade. A layer of composite material lining honeycomb structure delaminates/breaks when a separated blade part passes through a further, inner honeycomb liner and hits it. The resulting free end of composite liner wraps round the striking end of the blade part, thus blunting the cutting action of the blade part and spreading the generated forces to the extent that the blade part is de-energised sufficiently to prevent it penetrating the fan case. | 01-27-2011 |
20110027061 | Method For Braking A Rotor Of A Turbine Engine And A Turning Gear For Driving The Rotor Of A Turbine Engine - The invention relates to a method for braking a rotor of a turbine engine, comprising a turning gear, with a drive supplied from an energy source, having an input shaft to which the rotor may be coupled, whereby, during a cooling phase for the turbine, the rotor may be driven by the drive using the coupled input shaft. According to the invention, a method for braking a rotor of a turbine engine can be achieved, in which the rotation of a rotor, caused by the airflow through the turbine, is slowed until the rotor stops, whereby after the end of the cooling phase, the drive drives the rotor in the reverse sense by means of the input shaft in order to brake the same. | 02-03-2011 |
20110027062 | SYSTEM AND METHOD FOR IMPROVED WIND CAPTURE - A system for improved fluid capture comprises a first vertical turbine. A first radial vane support module comprises a first vertical pole and a second vertical pole and is disposed adjacent to the first vertical turbine. The first radial vane support module comprises a first radial vane storage module coupled to the first vertical support pole and the second vertical support pole and the first radial vane storage module comprises a first motor and a first radial vane. The first radial vane comprises a first retractable panel. The first motor couples to the first radial vane and is configured to extend and retract the first radial vane. A first radial vane control module couples to the first motor and is configured to control the operation of the first motor. In one embodiment, a saucer vane module couples to the first vertical turbine. | 02-03-2011 |
20110027063 | SYSTEM AND METHOD FOR ONLINE MONITORING OF CORROSION OF GAS TURBINE COMPONENTS - A system and method capable of performing online corrosion monitoring of a component installed in a gas turbine. A sensing device is located so that electrodes thereof are exposed to an operating environment within the gas turbine section containing the component. The electrodes are formed of a material so that the component and electrodes similarly respond to corrosive agents within the gas turbine section. The electrodes are electrically insulated from each other and each electrode is operable as an anodic electrode or a cathodic electrode, depending on the extent of corrosion thereat, so that each electrode has an electrical potential value, voltages exist across the electrodes, electric currents flow between the electrodes, and the electrical potential/current values correspond to corrosion behaviors at the anodic electrodes. During gas turbine operation, output signals are obtained from the sensing device and indications are provided as to when certain maintenance operations should be performed on the gas turbine. | 02-03-2011 |
20110027064 | SYSTEM AND METHOD FOR MODIFYING ROTOR THRUST - A gas turbine includes a compressor, a turbine downstream of the compressor having stators, and a rotor connecting the compressor to the turbine. The rotor includes rotor cavities. A supply plenum containing a process by-product gas and a control valve is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities. A process for operating a gas turbine having a compressor and a turbine includes connecting the compressor to the turbine by a rotor, creating cavities in the rotor, and injecting a process by-product gas into at least one of the cavities. The process further includes regulating the flow of the process by-product gas into at least one of the cavities according to a pre-programmed parameter. | 02-03-2011 |
20110027065 | AXIAL COMPRESSOR VANE - A gas turbine engine axial compressor vane is disclosed having an aperture capable of flowing a relatively high pressure working fluid to change a direction of a flow vector downstream of the vane. The relatively high pressure working fluid can originate from a compressor discharge. The vane may have any number of apertures. | 02-03-2011 |
20110027066 | METHOD OF CONTROLLING TURBINE EQUIPMENT AND TURBINE EQUIPMENT - To provide a method of controlling a turbine equipment and a turbine equipment capable of carrying out a starting operation of controlling a load applied to a speed reducing portion while complying with a restriction imposed on an apparatus provided at a turbine equipment. The invention is characterized in including a temperature elevating step (S | 02-03-2011 |
20110052367 | SEALING AND COOLING AT THE JOINT BETWEEN SHROUD SEGMENTS - A gas turbine engine shroud includes a plurality of shroud segments disposed circumferentially one adjacent to another to form a full, circumferentially segmented ring about the rotor. The radial seal between each pair of adjacent shroud segments is positioned on the back side of the shroud platform. Cooling underneath the radial seals may be done by conduction heath transfer through the platform of the shroud segments. | 03-03-2011 |
20110052368 | METHOD AND A SYSTEM FOR ADJUSTING ALARM LEVEL OF A COMPONENT IN A WIND TURBINE - A method and a system for adjusting alarm level of a component in a wind turbine is provided. The method comprises defining an alarm level corresponding to an operational parameter of the component in the wind turbine, monitoring the operational parameter of the component, determining whether the operational parameter exceeds the alarm level, thereby triggering an alarm. In the case when the alarm is triggered, the method further comprises inspecting the component to determine whether the alarm level corresponds to a predetermined remaining useful lifetime of the component, and adjusting the alarm level based on the inspection of the component. | 03-03-2011 |
20110058928 | CENTRIFUGAL PUMP WITH THRUST BALANCE HOLES IN DIFFUSER - A centrifugal pump has alternating impellers and diffusers. One or more vent holes extend through one or more vanes of one or more diffusers. In an upthrust condition, high pressure production fluid from an upper impeller is able to pass through the one or more vent holes, and thereby exert force on the preceding impeller. The force exerted on the preceding impeller offsets the upthrust force acting against the preceding impeller. | 03-10-2011 |
20110064559 | METHOD AND APPARATUS FOR CONTROLLING TONAL NOISE FROM SUBSONIC FANS - A method and apparatus for reducing a selected tonal noise generated by a fan operating in a non-uniform flow by locating at least one obstruction in the non-uniform flow such that the at least one obstruction generates a noise that is out of phase with the selected tonal noise. The noise generated by the at least one obstruction interferes with the selected tonal noise, thus reducing the selected tonal noise. It is also contemplated to use additional obstructions to reduce other tonal noises generated by the fan. | 03-17-2011 |
20110064560 | AXIAL TURBINE AND METHOD FOR DISCHARGING A FLOW FROM AN AXIAL TURBINE - An axial turbine ( | 03-17-2011 |
20110070063 | Pressure Regulation Circuit for Turbine Generators - A pressure regulation circuit delivers pressurized fluid into a generator. The circuit includes pressure regulator structure and a primary valve. The pressure regulator structure outputs pressurized fluid at a predetermined output pressure that is greater than a desired operating pressure of the generator and less than a predetermined upper alarm pressure. The primary valve is downstream from the pressure regulator structure and is selectively opened and closed by a controller based on the pressure within the generator. The controller opens the primary valve to allow the pressurized fluid outputted from the pressure regulator structure to flow into the generator upon the pressure within the generator being at or below a predetermined lower limit. The controller closes the primary valve to prevent the pressurized fluid outputted from the pressure regulator structure from flowing into the generator upon the pressure within the generator being at or above a predetermined upper limit. | 03-24-2011 |
20110070064 | System and Method for Accommodating Changing Resource Conditions for a Steam Turbine - A system and method for configuring a steam turbine to accommodate changing resource conditions, such as may be encountered with geothermal wells. A plurality of sets of nozzle/blade assemblies are provided for installation in a diaphragm structure and on a rotor, respectively. As the condition of steam provided to the turbine changes, a different set of nozzle/blade assemblies may be installed to maintain a preferred thermodynamic efficiency for the turbine. | 03-24-2011 |
20110070065 | Wind energy device with increased wind speed feature - Wind energy device is composed of an enlarged main shroud structure with flare feature to capture more on-coming wind energy, and with wind flow swirling vane feature to force the captured wind flow to rotate. A multiple stage coaxial counter rotating fan system with duct feature is attached to the main shroud to boost the wind flow energy captured by the main shroud to increase the air power passing through the fan system. The coaxial counter rotating fan's rotating direction is opposite to the captured wind flow rotating one forced by the wind flow swirling vanes for higher fan efficiency. A multiple blade supply windmill with shroud feature is mounted to the coaxial counter rotating fan system to capture and convert on-coming wind energy and supply the power to drive the coaxial counter rotating fan system to achieve inputting more energy into the wind flow captured by the main shroud through the fan system. A multiple blade main windmill at the coaxial counter rotating fan system's outlet place will capture and convert the boosted air power into mechanical energy to drive an electrical generator at the front of the device through a drive shaft passing through the coaxial counter rotating fan system. Multiple stage coaxial counter rotating fan system is an efficient approach to increase air flow energy passing through the system. The boosted air power through the coaxial counter rotating fan system will significantly increase the wind kinetic energy capacity that will well offset the cost for the components added, then generate low cost wind powered electricity. | 03-24-2011 |
20110070066 | FLUID TURBINE DEVICES AND METHODS RELATED TO FLUID TURBINE DEVICES - Fluid turbine devices and methods related to fluid turbine devices are disclosed herein. One example method includes deflecting a first portion of a fluid flow from a return path of a vertical blade assembly, while permitting a second portion of the fluid flow to enter a drive path of the vertical blade assembly. Another example method related to a fluid flow device includes orienting a shroud relative to a fluid flow to deflect a first portion of a fluid flow from a return path of a vertical blade assembly and to permit a second portion of the fluid flow to enter a drive path of the vertical blade assembly and activating a generator, based on an operating characteristic of the fluid turbine device, to regulate a rotational speed of the vertical blade assembly. | 03-24-2011 |
20110076131 | METHOD FOR DETECTING ROTATING STALL IN A COMPRESSOR - A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall. | 03-31-2011 |
20110081226 | METHOD FOR OPERATING A WIND TURBINE - The present disclosure relates to a method for operating a wind turbine with the steps: detection of the values of predetermined operating parameters by means of suitable sensors, detection of at least one predetermined initial condition, comparison of the detected values to stored values of the operating parameters. The disclosure further relates to a wind turbine for implementing the method. Therefore, the object of the present disclosure is, to be able to adapt the operation of a wind turbine to changes using a method of the type named above, such that when the detected parameter values deviate from the stored parameter values, as a function of the initial condition, either the stored parameter values are adapted to the detected parameter values or the operation of the wind turbine is influenced as a function of the detected parameter values. In this way, the disclosure is based on the knowledge that, from a pragmatic view, the formation of ice on a rotor blade is also a (temporary, meteorologically-related) change to the rotor blade shape. From this it follows that the formation of ice on the rotor blades always leads to a change of the aerodynamic profile and thus to a negative effect of the output of the wind turbine. However, deviations from this shape and thus deviations in the magnitude of the generated output also result just from manufacturing-dependent deviations of the rotor blades from the predetermined optimum shape and from gradual soiling of the rotor blades during operation. | 04-07-2011 |
20110085885 | VARIABLE VANE ACTUATION SYSTEM - A variable vane actuation system is disclosed herein. The variable vane actuation system includes a first vane having a first vane axis. The variable vane actuation system also includes an actuator operably engaged with the first vane to selectively pivot the first vane about the first vane axis. The variable vane actuation system also includes a ring member operably connected with the first vane. The ring member is disposed for pivoting movement about a centerline axis transverse to the first vane axis. The variable vane actuation system also includes a second vane having a second vane axis spaced from the first vane axis about the centerline axis. The second vane is operably connected with the ring member. Forces moving the second vane are generated by the actuator and transmitted first through the first vane and then through the ring member before being applied to the second vane. | 04-14-2011 |
20110085886 | SYSTEM AND METHOD FOR COOLING STEAM TURBINE ROTORS - A steam turbine includes a rotor having a plurality of early stages and a stator portion surrounding a portion of the rotor and arranged such that a leakage region exists between the stator portion and the rotor and having a cooling steam channel that passes cooling steam from one portion of the stator portion to the leakage region. The turbine also includes at least one cooling steam transmission channel axially displaced about the rotor that receives the cooling steam from the leakage region and provides it to at least a portion of the early stages. | 04-14-2011 |
20110085887 | HIGH TEMPERATURE RADIALLY FED AXIAL STEAM TURBINE - The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced. | 04-14-2011 |
20110091310 | THERMOMECHANICAL PART CONSTITUTING A BODY OF REVOLUTION ABOUT A LONGITUDINAL AXIS AND INCLUDING AT LEAST ONE ABRADABLE RING FOR A SEALING LABYRINTH - The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly. | 04-21-2011 |
20110097188 | STRUCTURE AND METHOD FOR IMPROVING FILM COOLING USING SHALLOW TRENCH WITH HOLES ORIENTED ALONG LENGTH OF TRENCH - A turbine airfoil includes a plurality of shallow trenches. Each trench includes a plurality of film holes disposed within and located along the lengthwise direction of the trench and angled through an airfoil substrate in the lengthwise direction of the trench. | 04-28-2011 |
20110103930 | Valve Sequencing System and Method for Controlling Turbomachine Acoustic Signature - A system and method for controlling the acoustic signature of a turbomachine having a plurality of valves wherein an operating load is identified and an arc of admission across a plurality of nozzles is associated therewith. A valve sequencing scheme is selected and implemented to activate the arc of admission for a particular operating load so as to minimize valve noise by adjusting valves simultaneously rather than consecutively. | 05-05-2011 |
20110103931 | GAS TURBINE COMPRESSOR - A gas turbine compressor is disclosed. The compressor includes a compressor housing, guide vanes, rotor blades, and valve-controlled blow-in openings for stabilizing the compressor flow by air that is blown in. The air flow is detected by pressure sensors and the valves are controlled as a function thereof. | 05-05-2011 |
20110110758 | GAS TURBINE COMPRESSOR AND METHOD OF OPERATION - The present application provides a compressor for a gas turbine. The compressor may include a number of rotor wheels positioned about a compressor aft section having a low alloy material, a number of inlet guide vanes positioned about a compressor inlet section, and a wet compression system positioned about the compressor inlet section. | 05-12-2011 |
20110110759 | METHOD AND SYSTEM FOR REDUCING THE IMPACT ON THE PERFORMANCE OF A TURBOMACHINE OPERATING AN EXTRACTION SYSTEM - A method and system for increasing the efficiency of a turbomachine having an extraction system is provided. The extraction system may have multiple extraction ports from which the working fluid of the turbomachine is extracted to meet extraction load requirements of an independent process. The method and system may enable a control system to optimally determine the which extraction ports to draw the working fluid from for meeting the extraction load requirement. The optimal location may be determined by utilizing the data on the load requirement, where the extraction load requirement may be operationally distinct from the turbomachine load. | 05-12-2011 |
20110110760 | METHOD AND SYSTEM FOR INCREASING AN EFFICIENCY OF A PRESSURIZED MACHINE - A method and system for regulating the pressure of steam in a Steam Seal Header (SSH) for a pressurized machine is provided. In the SSH, the pressure of steam may be regulated according to the operating status of the pressurized machine. The variable pressure SSH system may maintain a pressure packing of the pressurized machine within an optimized pressure range. | 05-12-2011 |
20110116906 | AIRFOIL COMPONENT WEAR INDICATOR - An example airfoil assembly includes an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side. The assembly further includes a first protective sheath, an indicator sheath, and a second protective sheath. The first protective sheath has an outer side and an inner side that forms a cavity for receiving at least a portion of the airfoil body. The inner side being bonded to the leading edge of the airfoil body. A portion of the indicator sheath is positioned forward the first sheath relative to the leading edge of the airfoil. A portion of the second protective sheath is positioned forward the indicator sheath relative to the leading edge of the airfoil. | 05-19-2011 |
20110129326 | FUEL PUMP WITH DUAL OUTLET PUMP - An outlet plate of an impeller pump is provided, the outlet plate having an outlet port disposed in the outlet plate, the outlet port being defined by a first outlet port and a second outlet port each extending through the outlet plate; a separator wall located in the outlet port, the separator wall separating an inlet of the first outlet port from an inlet of the second outlet port; and a groove located only on a first surface of the outlet plate, the groove having a first distal end and a second distal end, the first distal end terminating at the first outlet port, wherein the separator separates the groove from the second outlet port. | 06-02-2011 |
20110129327 | BALL BEARING AND PUMP FOR CRYOGENIC USE - A ball bearing for a cryogenic application including an inner ring and an outer ring positioned around the inner ring. The inner ring and the outer ring define a raceway therebetween. The ball bearing includes a plurality of rolling balls disposed in the raceway and a slug separator positioned between and slidingly engaging each of adjacent pairs the rolling balls. The slug separator defines an exterior surface thereon, which has a recess extending at least partially into the slug separator. The recess is configured to flow cryogenic fluid therethrough. | 06-02-2011 |
20110129328 | PLASMA SENSORS AND RELATED METHODS - Plasma sensors, systems and related methods are described. An example method for predicting an event includes providing a carrier signal across two electrodes and forming a plasma between the two electrodes. The example method also includes measuring a modulated signal from the plasma, manipulating the modulated signal to produce a value and comparing the value to a threshold. Finally, the example method includes determining the likelihood of the event based on the comparison. | 06-02-2011 |
20110135441 | Compressor Performance Adjustment System - A compressor performance adjustment system includes a compressor chassis defining an inlet passageway, a diffuser passageway coupled to the inlet passageway, and a return passageway extending from the diffuser passageway. At least one inlet vane is located in the inlet passageway. At least one diffuser vane is located in the diffuser passageway. At least one return vane is moveably coupled to the compressor chassis and located in the return passageway. The return vanes may be adjusted without disassembling the compressor chassis in order to adjust the flow incident on compressor components and adjust the performance of a compressor. | 06-09-2011 |
20110135442 | SYSTEM, DEVICE, AND METHOD FOR ACOUSTIC AND VISUAL MONITORING OF A WIND TURBINE - A method for monitoring a wind turbine. A monitoring signal, including an audio signal and/or an image signal, is received from a monitoring device. Operating data are calculated based on the received monitoring signal. An operating condition and/or a deviation is determined by comparing the operating data to baseline data. | 06-09-2011 |
20110135443 | System and method for collecting, augmenting and converting wind power - A system, apparatus, and method for collecting and concentrating an airstream for converting into mechanical or electrical energy, includes an elongated housing structure, including an airstream inlet chamber, a central chamber, and an airstream outlet chamber, and an ancillary airstream injector sub-system. | 06-09-2011 |
20110142592 | SUPERSONIC COMPRESSOR ROTOR - The present invention provides a supersonic compressor comprising a supersonic compressor rotor comprising a clockable rotor disk allowing restriction or opening of portions of a fluid flow channel of the rotor in order to enhance performance of the rotor during different operational stages, for example rotor start-up or steady state. The supersonic compressor rotor comprises a first rotor disk, a second rotor disk and a third rotor disk which share a common axis of rotation. The first and second rotor disks are rotatably coupled, and the third rotor disk is disposed between them. The third rotor disk is independently rotatable relative to said first and second disks, and comprises a raised surface structure for restricting or opening a portion of the flow channel defined by the rotor disks and at least two vanes. The flow channel comprises a supersonic compression ramp and encompasses the raised surface structure. | 06-16-2011 |
20110142593 | METHOD AND SYSTEM FOR VALIDATING WIND TURBINE - A method of validating a wind turbine including a rotor includes intentionally inducing a loading imbalance to the rotor. The method also includes measuring the loading imbalance induced to the rotor, transmitting a signal representative of the measured loading imbalance to a calibration module, and at least one of detecting an error and calibrating at least one component of the wind turbine based on the signal. | 06-16-2011 |
20110150626 | METHOD AND SYSTEM FOR DETECTING A CRACK ON A TURBOMACHINE BLADE - Embodiments of the present invention may provide real-time monitoring of a compressor section to determine the possibility of a crack forming on a rotating blade. The present invention does not require the shutdown of the machine. The present invention may be configured to automatically raise an alarm if the acoustic signature of the compressor changes in way that may be consistent with the cracking of a blade. | 06-23-2011 |
20110150627 | METHOD OF OPERATING A FAN SYSTEM - A method of operating a fan system is described comprising the steps of pressurizing an airflow in a forward fan stage to generate a pressurized flow, directing a first portion of the pressurized airflow towards a tip-fan of an aft fan stage, and directing a second portion of the pressurized airflow towards a circumferential row of air-turbine blades of the aft fan stage to drive the aft fan stage. | 06-23-2011 |
20110150628 | FLUID ENERGY MACHINE - A fluid energy machine is provided. The fluid energy machine includes a housing having a motor, an impeller, at least two radial bearings, and a shaft which extends along a shaft longitudinal axis and which supports the impeller and a rotor of the motor wherein the shaft is mounted in the radial bearings. The motor includes a stator which at least partially surrounds the rotor in the region of the motor. A gap which extends in the circumferential direction along the shaft longitudinal axis is formed between the rotor and stator and between the rotor and the radial bearings, which gap is at least partially filled with fluid. The motor is embodied as a bearing and is connected to a controller which activates the motor so that forces acting radially with respect to a shaft longitudinal axis can be exerted in addition to torques for driving the fluid energy machine. | 06-23-2011 |
20110158786 | METHOD FOR OPERATING STEAM TURBINE WITH TRANSIENT ELEVATED BACK PRESSURE - A method and control system for implementing a transient exhaust pressure protection logic to avoid a turbine exhaust vacuum trip due to a short duration turbine exhaust pressure transient caused by a large reduction in turbine flow coupled with a transient increase in exhaust pressure, which specifically occurs during full load rejections. When full load rejection conditions are sensed by power load unbalance and confirmed by secondary means, normal alarm settings and trip settings for turbine exhaust pressure are blocked for a delay period while transient operating limits are in place. | 06-30-2011 |
20110158787 | WIND TURBINE - Wind turbine systems and methods are provided. The wind turbine system includes a plurality of coaxial, counter-rotating turbine assemblies. First and second shroud assemblies define a generally spherical volume containing the first and second turbine assemblies. The first and second shroud assemblies each include a shroud member that can selectively shield or expose portions of the respective turbine assemblies to the wind by changing the rotational position of the shroud members about the system axis. The turbine assemblies are interconnected to a generator for the production of electrical power. | 06-30-2011 |
20110158788 | A SECTIONAL BLADE - The invention provides a sectional blade for a wind turbine. The blade comprises at least a first blade portion and a second blade portion extending in opposite directions from a joint. The first blade portion and the second blade portion are structurally connected by at least one spar bridge extending into both blade portions to facilitate joining of said blade portions. | 06-30-2011 |
20110164957 | Method and Apparatus for Double Flow Turbine First Stage Cooling - A cooling path is defined through a double-flow steam turbine. The steam turbine includes a generator end and a turbine end and a double-flow tub diaphragm disposed axially between the generator end and the turbine end. A first stage of the steam turbine includes a plurality of first stage nozzles and a plurality of first stage buckets, and a steam path is defined from an inlet region, through the turbine end, to a steam outlet. The cooling path includes cooling holes in the tub diaphragm and root radial seals permitting steam flow beneath the tub diaphragm and around the first stage nozzles and back into the steam path before the first stage buckets. | 07-07-2011 |
20110164958 | Centrifugal reverse flow disk turbine and method to obtain rotational power thereby - A centrifugal reverse flow disk turbine for power generation, comprising; a) a turbine shaft; b) a disk rotor disposed on said turbine shaft; c) a housing, having said turbine shaft and said disk rotor, bearings, seal devices, and at least one jet nozzle means; d) a plurality of radially engraved channel for transporting working fluid from entering ports, placed axially near said turbine shaft; e) a plurality of said channels having two curvatures; first curvature has a small radius, and concaved pertinent to rotational direction of said rotor, starting from the entering port to middle of its flow path, and the second curvature has a large radius, convexed pertinent to rotational direction of said rotor, positioned near the peripheral of said rotor; a plurality of a buket attached at every flow channel, directing against nozzle disposed on said housing, thereby deriving impinging counter supersonic flow. | 07-07-2011 |
20110176907 | MULTI-PIECE TURBOCHARGER BEARING - An exemplary multi-piece bearing for a turbocharger includes a cylindrical piece that has a coefficient of thermal expansion, opposing ends and an outer surface and an inner surface that extend between the opposing ends where the outer surface includes one or more lubricant openings; an end piece that has a different coefficient of thermal expansion and a face where the face includes one or more lubricant openings; and lubricant passages formed by the cylindrical piece and the end piece for passage of lubricant between the one or more lubricant openings of the outer surface of the cylindrical piece and the one or more lubricant openings of the face of the end piece. As described herein, such an exemplary multi-piece bearing can, upon selection of coefficients of thermal expansion, help maintain axial clearances between various components during operation of a turbocharger. Other exemplary bearings, arrangements and methods are also disclosed. | 07-21-2011 |
20110176908 | Method and apparatus for efficiently generating and extracting power from an air flow to do useful work - This invention relates to a clean, efficient, substantially isentropic method and apparatus for transforming the internal energy of a mass flow of a fluid, such as air, into increased flow kinetic energy and then efficiently transferring this additional kinetic energy to a power take-off means for doing useful work. The acceleration of the air flow is accomplished by passing the air flow through a set of converging nozzles which generate thrust; the nozzle thrust is then transformed into torque which turns a rotor which is coupled to a power take-off means. The method and apparatus can be made to be self-sustaining. | 07-21-2011 |
20110188986 | System and method for improving wind turbine efficiency by adjusting blade pitch in response to localized wind speed - A wind turbine for generating electrical power, the turbine having a rotor assembly comprising a hub, a rim and a plurality of blade members extending between the hub and rim, and at least two anemometers mounted at stationary locations relative to the rotor assembly or on the rotor assembly itself, wherein the pitch of individual blade members is adjustable in response to differences in wind speed detected by the anemometers as the rotor assembly rotates. | 08-04-2011 |
20110188987 | REGULATABLE COOLANT PUMP AND METHOD FOR ITS REGULATION - A regulatable coolant pump and a method for regulation of this regulatable coolant pump for internal combustion engines, which is driven by way of a pulley actives a valve slide using an electromagnetically activated piston pump equipped with a return spring in the form of a pressure spring. The pump implements a “pump feed” using many small “partial lifts.” A “leakage volume stream” that flows opposite to the “pumped volume stream” is superimposed on the “pumped volume stream” via the arrangement of circular apertures both in the inlet valve membrane of the working piston and in the outlet valve membrane so that the valve slide can be moved in defined manner and in a very robust and reliable manner, with low drive power via the defined superimposition of these two volume streams. | 08-04-2011 |
20110188988 | PLAIN BEARING FOR A WIND TURBINE BLADE AND METHOD OF OPERATING A WIND TURBINE HAVING SUCH A PLAIN BEARING - A plain bearing assembly for mounting a blade to a hub of a wind turbine includes an outer member mountable to one of the blade or hub, and an inner member mountable to the other of the blade or hub and movable relative to the outer member. The plain bearing further includes fluid cavities associated with one of the outer or inner member and arranged to confront the other of the outer or inner member. The fluid cavities are coupled to a pressure source for establishing a pressurized fluid film between the inner and outer members. A method includes monitoring at least one parameter of the fluid film, comparing the at least one parameter to a threshold criteria, and altering a dynamic state of the wind turbine and/or altering the state of the blade bearing assembly if the threshold criteria is exceeded. | 08-04-2011 |
20110188989 | EXHAUST EDUCTOR SYSTEM WITH A RECIRCULATION BAFFLE - An exhaust eductor system includes a primary exhaust nozzle configured to transport an active flow stream; and a mixing duct at least partially surrounding the primary exhaust nozzle and configured to transport a passive flow stream that is entrained by mixing with the active flow stream from the primary exhaust nozzle. The mixing duct has an interior, and a baffle on the interior of the mixing duct is configured to prevent the mixed flow streams from exiting the mixing duct. | 08-04-2011 |
20110188990 | BENKATINA HYDROELECTRIC TURBINE: ALTERATIONS OF IN-PIPE TURBINES - New in-pipe hydroelectric turbine devices, systems, and methods offer the potential for less costly and greater energy output in many applications. | 08-04-2011 |
20110194926 | Submersible Pump for Operation In Sandy Environments, Diffuser Assembly, And Related Methods - Submersible pumps, diffuser assemblies, and related methods for pumping a fluid having a substantial sand content, are provided. A diffuser assembly for a submersible pump can include anti-swirl ribs forming sand dams positioned on an upper surface of the diffuser bowl floor at an acute angle to guide trapped between the bottom shroud of an impeller and the diffuser bowl to the inner surface of the diffuser bowl outer wall and back into the production fluid stream. The diffuser assembly can also include sand jump ramps each separately positioned adjacent the outer peripheral surface of one of the sand dams and positioned adjacent a separate portion of the inner surface of the diffuser bowl outer wall to further enhance deflection of sand back into the production fluid stream. | 08-11-2011 |
20110200421 | Exhaust Diffuser - An exhaust diffuser including an outer flow guide surface and an inner flow guide surface defining an inlet, a first collection chute having an outlet in fluid communication with the inlet, the first collection chute operative to diffuse a flow of a fluid, a second collection chute having an outlet in fluid communication with the inlet, the second collection chute operative to diffuse the flow of the fluid, and the outer flow guide surface and the inner flow guide surface are operative to guide and direct the flow of the fluid to the first collection chute and the second collection chute. | 08-18-2011 |
20110200422 | MULTI-LOBE SEMI-FLOATING JOURNAL BEARING - An exemplary turbocharger assembly includes a housing with a through bore having a central axis extending between a compressor end and a turbine end of the housing and a bearing, configured for receipt by the through bore, where the bearing includes an inner journal configured to rotatably support a turbocharger shaft and where the inner journal includes a central axis, an axial length, a lubricant opening, an axially confined lubricant well, a lubricant ramp, and a lubricant channel that spans the axial length of the inner journal. Various other exemplary devices, systems, methods, etc., are also disclosed. | 08-18-2011 |
20110200423 | VACUUM PUMP - A differentially pumped vacuum system including apparatus having at least first and second chambers; and a vacuum pump for differentially pumping fluid from the chambers to generate a first pressure above 0.1 mbar in the first chamber and a second pressure lower than the first pressure in the second chamber, the pump having at least first and second pump inlets each for receiving fluid from a respective pressure chamber and a plurality of pumping stages positioned relative to the inlets so that fluid received from the first chamber passes through fewer pumping stages than fluid from the second chamber, the inlets being attached to the apparatus such that at least 99% of the fluid mass pumped from the apparatus passes through at least one of the pumping stages of the pump. | 08-18-2011 |
20110200424 | COUNTER-ROTATING GEARBOX FOR TIP TURBINE ENGINE - A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased. | 08-18-2011 |
20110211940 | SYSTEM AND METHOD FOR INSPECTION OF STATOR VANES - Embodiments of the invention include an inspection system to inspect internal components of a compressor of a gas turbine engine. The inspection system includes an image recording assembly having one or more image recording devices, light sources, storage devices, and power supplies. The image recording assembly may be inserted into a compressor without removal of the compressor housing or disassembly of the compressor. The image recording assembly may be removably coupled to a rotary component of the compressor, e.g., a rotor blade, and used to record images of stationary components, e.g., stator vanes, of the compressor. The images may be inspected to identify wear and/or defects in the stationary components, e.g., stator vanes | 09-01-2011 |
20110217155 | COOLING GAS TURBINE COMPONENTS WITH SEAL SLOT CHANNELS - A segment of a component for use in a gas turbine includes a leading edge; a trailing edge; a pair of opposed lateral sides between the leading and trailing edges; and a seal slot provided in each lateral side. The seal slot includes a surface having a channel extending in an axial direction defined from the leading edge to the trailing edge, at least one inlet to the channel, and at least one outlet from the channel. The at least one outlet is spaced downstream from the at least one inlet in the axial direction. The segment may be an inner shroud segment or a nozzle segment. | 09-08-2011 |
20110223003 | OIL COOLED RUNNER - An oil cooled runner, for a rotary seal between an engine case and a shaft rotationally mounted to the case, includes an annular runner ring having a platform with a radially outer seal engagement surface and a radially inner surface, and an oil distributor having a radially inner portion in communication with a source of liquid lubricant and an outer lubricant casting cone with a rim disposed radially inwardly from the inner surface of the platform. | 09-15-2011 |
20110229300 | APPARATUS AND METHOD FOR INDIVIDUAL PITCH CONTROL IN WIND TURBINES - In a method for blade load reduction control of a rotor of a wind turbine, the rotor includes a plurality of blades, and a pitch angle of each blade is controllable by an actuator. The method includes measuring mechanical load parameters on the rotor, providing control for a collective pitch blade setting based on a rotor speed; providing individual pitch control including transforming the mechanical load parameters from a rotational reference frame to a mechanical load on the rotor in a fixed reference frame; determining from the mechanical load two multi-blade pitches; correcting the multi-blade pitches to corrected multi-blade pitches using actuator limitations; inversely transforming the corrected multi-blade pitches to an individual pitch deviation for each blade in the rotational reference frame; adding up for each blade, the individual pitch deviation to the collective pitch to form an individual pitch; and setting each blade to the respective individual pitch. | 09-22-2011 |
20110229301 | ACTIVE TIP CLEARANCE CONTROL FOR SHROUDED GAS TURBINE BLADES AND RELATED METHOD - A turbine bucket tip clearance control system includes a rotor assembly having a rotor supporting a plurality of axially spaced wheels, each wheel mounting an annular row of buckets, the annular row of buckets on at least one of the plurality of axially-spaced wheels having a radially outer tip shroud provided with at least one seal tooth. A stator assembly includes a radially inwardly facing, axially-stepped surface, formed with radially inner and outer seal surfaces connected by a shoulder. The stator assembly and rotor assembly are moveable axially relative to each other, enabling selective positioning of the at least one seal tooth radially opposite one of the radially inner and outer seal surfaces to thereby selectively alter a clearance gap between the at least one seal tooth and the radially inward facing axially-stepped surface. | 09-22-2011 |
20110229302 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 09-22-2011 |
20110229303 | Method for operating a multistage compressor - A method for operating a multistage compressor is provided. The method includes monitoring the pump limit, wherein at least a first measurement parameter measured during operation is compared to a reference parameter. The reference parameter is characteristic of reaching the surge limit or a specific distance of the operating point from the surge limit. A multistage compressor is also provided. In order to enlarge the operating range without risking safety, it is proposed that each stage to be monitored individually for the onset of the surge. | 09-22-2011 |
20110236177 | Steam Seal System - The present application provides a variable steam seal system for use with a steam turbine. The variable steam seal system may include a seal steam header, a first pressure section, a first pressure seal positioned about the first pressure section, and a flow path through the first pressure seal and extending to the seal steam header. The first pressure seal may include a moveable seal packing ring for varying the flow path through the first pressure seal to the seal steam header. | 09-29-2011 |
20110236178 | BRANCHED AIRFOIL CORE COOLING ARRANGEMENT - An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion. | 09-29-2011 |
20110236179 | SEAL CLEARANCE CONTROL ON NON-COWLED GAS TURBINE ENGINES - A method for controlling turbine blade tip seal clearance on a non-cowled gas turbine engine includes the step of directing a flow of relatively hot, pressurized air in contact with an exterior surface of the engine core casing circumscribing the turbine. The flow of relatively hot, pressurized air may be selectively directed in contact with the exterior surface of the engine core casing circumscribing the turbine when it is desired to expand the turbine shroud radially outward, such as during transient operation of the gas turbine engine. | 09-29-2011 |
20110236180 | GAS DRIVEN ROTATION MOTOR, A TOOL PROVIDED WITH A GAS DRIVEN ROTATION MOTOR AND A METHOD FOR REGULATING SPEED OF A GAS DRIVEN ROTATION MOTOR - A gas driven motor includes a housing, a gas driven rotating member including a rotor and a rotor shaft carrying the rotor and journalled in a first bearing and a second bearing supported in the housing, and a speed governor for controlling a pressure gas inlet flow in response to the rotation speed of the rotating member. The first bearing includes a set of rolling elements, an outer race arranged in the housing and an inner race arranged on a shaft portion of the rotating member, the set of rolling elements being in contact with the races on which the rolling elements roll. The motor further includes a coupling device arranged to couple the speed governor to the rolling elements of the first bearing, thereby transferring the rotary motion from the rolling elements to the speed governor. | 09-29-2011 |
20110236181 | VERTICAL AXIS WIND TURBINE - A vertical axis wind turbine comprises upper and lower rotor blades and upper and lower bearing assemblies. Horizontal members connect the upper rotor blades to the upper bearing assembly and the lower blades connect the upper rotor blades to the lower bearing assembly. The upper rotor blades can be arranged vertically or non-vertically. In non-vertical arrangements, the upper rotor blades can be twisted or swept back in a straight manner. The turbine can be self-supporting with a need for a continuous vertical axis connecting the bearing assemblies. Sweeping jet actuators are incorporated into the rotor blades to deliver oscillating air jets to surfaces of the rotor blades to delay occurrence of dynamic stall. Conduits in the blades can deliver pressurized flow of air to the actuators. The turbine can be supported by a structure that can exerts only horizontal and/or lifting forces on the rotor blade assembly to reduce the load on the lower bearing. | 09-29-2011 |
20110243708 | METHODS, SYSTEMS AND APPARATUS RELATING TO TIP CLEARANCE CALCULATIONS IN TURBINE ENGINES - A method of calculating the tip clearance during operation of a combustion turbine engine that includes the steps of: measuring a cold tip clearance and a cold shell-to-shell distance; while the combustion turbine engine is operating, measuring an operating parameter and measuring a shell-to-shell distance with a proximity sensor; calculating the tip clearance based on the cold tip clearance measurement and the operating parameter measurement; calculating the shell-to-shell distance based on the cold shell-to-shell distance measurement and the operating parameter measurement; comparing the shell-to-shell distance measurement of the proximity sensor with the shell-to-shell distance calculation; and calibrating the calculated tip clearance calculation based on the comparison. | 10-06-2011 |
20110243709 | NON-INTEGRAL PLATFORM AND DAMPER FOR AN AIRFOIL - A section of a gas turbine engine includes a damper which extends from a disk between a first blade and a second blade to provide a dissipating vibratory motion energy in the form of friction heating. | 10-06-2011 |
20110250046 | TURBOFAN ENGINE PERFORMANCE RECOVERY SYSTEM AND METHOD - Methods and apparatus are provided for improving engine performance in a turbofan gas turbine engine following foreign object ingestion in turbofan gas turbine engines that include an intake fan that includes a plurality of fan blades, and that is disposed within and surrounded by a fan case. The occurrence of a foreign object ingestion by the turbofan gas turbine engine is detected and, upon detecting that a foreign object has been ingested, air is bled from a region proximate the blades of the intake fan through a slot in the fan case. | 10-13-2011 |
20110250047 | Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower - Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller. | 10-13-2011 |
20110250048 | Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower - Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller. | 10-13-2011 |
20110250049 | Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower - Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller. | 10-13-2011 |
20110250050 | SINGLE FAN TRAY IN A MIDPLANE ARCHITECTURE - A chassis may include a front section that contains a first electronic circuit board oriented in a first plane, a rear section that contains a second electronic circuit board oriented in a second plane, where the first plane and the second plane are substantially orthogonal, a midplane dividing the front and the rear sections, and a fan tray assembly including a plurality of fans to cool both the first electronic circuit board of the front section and the second electronic circuit board of the rear section. | 10-13-2011 |
20110255951 | Axial Thrust Balanced Impeller For Use With A Downhole Electrical Submersible Pump - An electrical submersible pumping system having a pump, a motor, a shaft connecting the pump and motor. Coaxially stacked rotating impellers and stationary diffusers are coaxially housed within the pump. Radial ports are formed in a hub of the diffusers that direct fluid pressurized by an impeller to a cavity formed on the shroud of the impeller. Axial ports are formed in the shrouds of the impellers that direct fluid from the cavity to a fluid flow passage within the impeller. Strategic placement and sizing of the radial and axial ports balances thrust forces exerted onto the impeller. | 10-20-2011 |
20110255952 | COMPRESSOR GAS FLOW DEFLECTOR AND COMPRESSOR INCORPORATING THE SAME - A turbocharger compressor includes a compressor housing having a housing wall that includes a shroud that defines a central air channel and a compressor inlet in fluid communication with the central channel and an inlet duct. It also includes a compressor wheel configured to draw air into the compressor inlet from the inlet duct and create a main airflow in the central air channel axially toward a compressor outlet. The compressor also includes a bypass channel that extends between an opening in the main channel located between the compressor inlet and compressor outlet proximate the compressor blades and the compressor inlet. The compressor also includes a deflector that includes a deflector surface that is configured to direct a bypass airflow in the bypass channel, and flowing in a direction from the main channel toward the compressor inlet, into the compressor inlet axially and radially inwardly toward the compressor wheel. | 10-20-2011 |
20110255953 | Turbo machine and method to reduce vibration in turbo machines - A turbo machine ( | 10-20-2011 |
20110268554 | SYSTEMS, METHODS, AND APPARATUS FOR CONTROLLING TURBINE GUIDE VANE POSITIONS - Certain embodiments of the invention may include systems, methods, and apparatus for controlling turbine guide vane positions. According to an example embodiment of the invention, a method is provided for controlling at least one turbine guide vane. The method includes receiving a reference signal associated with the at least one turbine guide vane, measuring an actuator position and an angular position associated with the at least one turbine guide vane, generating a deadband signal based at least in part on the angular position, and manipulating the at least one turbine guide vane based at least in part on the deadband signal and the reference signal. | 11-03-2011 |
20110274533 | FLUID TURBINE WITH MOVEABLE FLUID CONTROL MEMBER - A shrouded fluid turbine includes an impeller for generating power from a fluid stream and a shroud surrounding the impeller. The impeller and/or the shroud have a moveable member for controlling power generation in the fluid turbine. The shroud has a plurality of mixing lobes on a trailing edge thereof, the trailing edge having a circular crenellated shape. The power generation is controlled by reducing loads and/or controlling impeller speed. Various moveable components are described for the stator vanes and the rotor blades. | 11-10-2011 |
20110280705 | WATER PUMP AND WATER PUMP SYSTEM AND METHOD - This disclosure relates a water pump, a system for cooling internal combustion engine components including a water pump, and a method for operating an internal combustion engine including a water pump. The water pump, system and method provide protection of the pump impeller during dry pump operation, such as when a watercraft engine is started while the watercraft is out of water, by dispensing fluid from a reservoir to the pump's impeller chamber. The fluid enters the chamber via a controllable flow path and interacts with the impeller and chamber walls to cool and lubricate the impeller. | 11-17-2011 |
20110280706 | Helico-axial pump, a rotor for a helico-axial pump, method for the hydrodynamic journalling of a rotor of a helico-axial pump, as well as a hybrid pump with a rotor for a helico-axial pump - The invention relates to a helico-axial pump ( | 11-17-2011 |
20110286831 | PARTITIONING OF TURBOMACHINE FAULTS - An example method of partitioning turbomachine faults includes using a modeling computer to model a system, to establish a modeled gas path parameter, and to establish a modeled subsystem parameter. The method then determines a gas path condition representing a difference between an actual gas path parameter and the modeled gas path parameter. The method also determines a subsystem condition representing a difference between an actual subsystem parameter and the modeled subsystem parameter. The method diagnoses a sensor failure based on the gas path condition and the subsystem condition. | 11-24-2011 |
20110293399 | HYDROELECTRIC TURBINE WITH PASSIVE BRAKING - This present invention relates to a hydroelectric turbine having a stator and a rotor within the stator on at least one set of bearings, the turbine having a brake which becomes operational following a predetermined level of bearing wear in order to avoid damage to the turbine. | 12-01-2011 |
20110293400 | INSTALLATION FOR CONVERTING HYDRAULIC ENERGY, AND A METHOD OF CONTROLLING SUCH AN INSTALLATION - The invention relates to a unit comprising a hydraulic turbine ( | 12-01-2011 |
20110299971 | GEAR ARRANGEMENT - An example gear arrangement includes a gearbox shaft and a journal shaft. The journal shaft establishes an opening that receives an end portion of the gearbox shaft. The gearbox shaft is configured to rotate the journal shaft. The journal shaft is configured to selectively rotatably couple with another shaft. The journal shaft is allowed to align to the bearing surface while the gearbox shaft allows for misalignment between the accessory and gearbox drive. | 12-08-2011 |
20110299972 | IMPELLER BACKFACE SHROUD FOR USE WITH A GAS TURBINE ENGINE - An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity. | 12-08-2011 |
20110305554 | LIGHT WEIGHT VANELESS COMPRESSOR CONTAINMENT DESIGN - A vaneless compressor containment design has an inner bolt circle with more than three fasteners situated in the vaneless space to cut up tri-hub pieces to smaller pieces prior to reaching an outer bolt circle and its associated flange. This containment design may allow a thinner radial wall thickness for the outermost flange as compared to the conventional design. The thinner radial wall thickness may reduce the weight of the compressor. This weight reduction may be achieved with little or no increase in the compressor space envelope. | 12-15-2011 |
20110305555 | Isentropic method and apparatus for greatly increasing and extracting the power from wind and moving air - This invention employs the isentropic acceleration of a basic air flow, supplied by the wind, through a converging/diverging De Laval Nozzle, to thereby enormously increase the air flow speed and power at the nozzle throat section and to simultaneously lower the pressure there to approximately one-half of ambient pressure. This low throat pressure is then used as a ‘vacuum’ source to activate a high speed isentropic flow of air through a power take-off means consisting of a flow rotor which converts the energy of the accelerating linear air flow through it into rotational energy suitable for take-off to do useful external work at very low cost. The invention can also be mounted on a moving vehicle so that the relative air flow past the vehicle supplies the air flow to produce the high power output at very low cost. | 12-15-2011 |
20110305556 | METHODS AND SYSTEMS FOR VARIABLE GEOMETRY INLETS NOZZLES FOR USE IN TURBOEXPANDERS - A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power. | 12-15-2011 |
20110311347 | Flash Steam Turbine - A flash steam powered flywheel turbine is provided comprising a stator housing with an internal channel for the flash and expansion of steam, the channel having a plurality of jet orifices to direct jets of expanding steam toward a rotary flywheel which is fixed to a rotational shaft within the stator housing. The rotary flywheel. is fitted with a plurality of inlet jet passages generally extending radially inwardly from the peripheral surface of the flywheel and oriented such that the force of expanding and impinging steam causes the flywheel to rotate about its central axis. Each inlet jet passage merges into one or more outlet jet passages oriented generally laterally such that the force of discharging steam causes further rotation in reaction to the discharging steam. The discharging steam is directed against steps or depressions formed on the inner lateral walls of the stator housing to add a jet-propulsion effect. in a clean and renewable manner, rotational energy and power will be generated, and the flywheel turbine and rotational shaft can be used to drive an electricity generator or as a prime mover. | 12-22-2011 |
20110311348 | MULTI-INLET VACUUM PUMP - A multi-inlet vacuum pump includes a first pump device ( | 12-22-2011 |
20110318160 | TURBOEXPANDER AND METHOD FOR USING MOVEABLE INLET GUIDE VANES AT COMPRESSOR INLET - A turboexpander-compressor system includes an expander configured to expand an incoming gas, a first set of moveable inlet guide vanes configured to control a pressure of the incoming gas, a compressor configured to compress a gas received from the expander, a shaft configured to support and rotate an expander impeller and a compressor impeller, a second set of moveable inlet guide vanes attached to the compressor and configured to control a pressure of the gas input into the compressor, and a controller configured to acquire information about a rotating speed of the shaft, a pressure and a temperature of the incoming gas, a pressure and a temperature of the gas output from the expander, and to control the second set of moveable inlet guide vanes to maximize a ratio between the rotating speed of the shaft and a drop of an enthalpy across the expander, in off-design conditions. | 12-29-2011 |
20110318161 | APPARATUS, SYSTEM AND METHOD FOR A WIND TURBINE - A wind turbine apparatus having a plurality of blades, a shaft connecting the blades and a housing for the blades. The housing is configured to provide an operational angle of over approximately 90 degrees. A wind turbine system having at least one wind turbine apparatus with a housing having a top enclosure and a bottom enclosure. The wind turbine system also includes a post pivotally connected to the at least one wind turbine apparatus and an electrical generator operatively connected to the at least one wind turbine apparatus. A method of wind tunneling wind to a wind turbine apparatus, which includes routing wind towards withdrawing blades of a wind turbine apparatus via a top enclosure; and routing wind towards arising blades of a wind turbine apparatus via angled slots provided in a bottom enclosure. | 12-29-2011 |
20120014776 | Method and apparatus for enhancing compressor performance - The present invention provides a non-axisymmetric flow member disposed in a duct of a gas turbine engine. The flow member narrows the area aft of a vane to reduce the cross sectional area through which a wake from the vane traverses. | 01-19-2012 |
20120014777 | METHOD FOR CONTROLLING A REGULATED-ROTATION-SPEED LOW-PRESSURE CENTRIFUGAL FAN - Method for controlling an automatic stall-prevention of a rotation-speed-regulated centrifugal fan. What is essential in the invention is that the control automatics is controlled by means of the automation system of the process, in which control automatics stalling is detected from a function of the electric current, voltage and frequency going to the motor of the centrifugal fan. | 01-19-2012 |
20120014778 | Sealing Device for Steam Turbines and Method for Controlling Sealing Device - Subject: To provide a sealing structure, and control method therefor, which improve sealing performance between a rotating region and a fixed region, prevent fins from being damaged, and prevent increases in the amount of steam leakage from any clearances newly formed by further abrasion of an abradable material. | 01-19-2012 |
20120020768 | COOLED CONSTRUCTIONAL ELEMENT FOR A GAS TURBINE - A cooled constructional element for a gas turbine includes a wall having a front and a rear side. The front side is configured to be thermally loaded during operation of the turbine, and the rear side has a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element. A device is configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement. | 01-26-2012 |
20120027564 | Method for the pressure regulation of a barrier fluid and a pumping device for a method of this kind - A method for the pressure regulation of a barrier fluid in a pumping device ( | 02-02-2012 |
20120027565 | SYSTEM AND METHOD FOR CONTROLLING LEAK STEAM TO STEAM SEAL HEADER FOR IMPROVING STEAM TURBINE PERFORMANCE - A turbine system is provided wherein during self-sealing operating conditions, excess leakoff steam is restricted from being dumped to a steam seal header and is diverted into the working steam flow path, hence increasing net output and efficiency for the turbine system. A related method is also provided. | 02-02-2012 |
20120027566 | METHOD AND SYSTEM FOR OPERATING A WIND TURBINE - A method, system and computer program product for operating a wind turbine is disclosed. For operating the wind turbine a set of operational data points are sensed via a sensing module. The set of operational data points may include bending stress values. Based on the bending stress values, a load scenario indicator value may be computed. Further, based on the set of operational data points a loading threshold value may be obtained. At least one operating parameter of the wind turbine is changed if the load scenario indicator value exceeds the loading threshold. | 02-02-2012 |
20120027567 | MECHANICALLY-COUPLED TURBOMACHINERY CONFIGURATIONS AND COOLING METHODS FOR HERMETICALLY-SEALED HIGH-TEMPERATURE OPERATION - The present invention provides a hermetically sealed turbomachine, such as a motor-driven blower and a turbine driven generator, capable of reliable high-temperature operation, especially for large sized turbomachines. The hot blower, compressor or turbine end of the turbomachine is separated from the cooler electric motor, generator or alternator end of the turbomachine by a compliant mechanical coupling and a thermal choke assembly, providing reliable high-temperature operation. The turbomachine housing is also hermetically sealed, providing control over the process gas within the machine housing, and permitting an internal cooling method within the turbomachine, whereby a small amount of process gas itself is used within the turbomachine for providing cooling of the rotating shafts, the axial fan, radial fan, or turbine impeller, the bearings and the electric motor, generator or alternator disposed within the turbomachine housing. The cooling method can be aided by a heat exchanger operatively communicating with the turbomachine. | 02-02-2012 |
20120027568 | LOW-PRESSURE STEAM TURBINE AND METHOD FOR OPERATING THEREOF - The disclosure relates to a multi-stage low-pressure steam turbine and a method for operating thereof. The steam turbine includes a last stage in which the leading edge of each vane of the last stage is skewed so as to form a W shaped K-distribution across the span of the vanes. This shape allows for efficient last stage operation at low last stage exit velocities. The disclosure includes a method for operating such a steam turbine at a last stage exit velocity between 125 m/s and 150 m/s. | 02-02-2012 |
20120027569 | ROTATING MACHINE WITH SHAFT SEALING ARRANGEMENT - A rotating machine comprising such as an axial power turbine or a turbocharger has a housing with a bearing cavity and a chamber separated by a first wall. A shaft is rotatable about an axis in the bearing cavity, extends through an opening in the first wall and is mounted for rotation on a bearing assembly provided in the bearing cavity. An oil sealing arrangement including an oil diffuser device is arranged on the shaft for displacing oil away from the shaft as it rotates. This restricts the flow of oil to the opening. The oil diffuser device defines a diffuser passage between the bearing assembly and the first wall, the passage extending outwardly of the axis. | 02-02-2012 |
20120034064 | CONTOURED AXIAL-RADIAL EXHAUST DIFFUSER - In accordance with one embodiment, a system includes a gas turbine diffuser. The gas turbine diffuser includes an axial diffuser section including a first duct portion having an axial flow path along a centerline of the gas turbine diffuser. The gas turbine diffuser also includes an axial-radial diffuser section coupled to the axial diffuser section, wherein the axial-radial diffuser section includes a second duct portion having a curved flow path along the centerline from the axial flow path to a radial flow path and the axial-radial diffuser section excludes any turning vane in the second duct portion. | 02-09-2012 |
20120039701 | Closed Cycle Brayton Cycle System and Method - Method and unit for generating energy with improved efficiency. A Brayton cycle unit includes a multistage compressor configured to compress a flowing medium; a first heat exchanger fluidly connected to the multistage compressor and configured to transfer heat from a working medium passing the first heat exchanger to the compressed flowing medium; an expander fluidly connected to the first heat exchanger and configured to expand the heated compressed flowing medium for producing a rotation of a shaft of the expander; and a second heat exchanger fluidly connected between the expander and the compressor and configured to remove heat from the expanded flowing medium. A path of the flowing medium through the unit is closed. At least one inter-cooler mechanism between first and second stages of the multistage compressor is configured to cool the flowing medium to a predetermined temperature. | 02-16-2012 |
20120039702 | COMPRESSOR - A compressor has a housing defining a gas inlet flow path and a gas outlet and a rotatable impeller wheel between the gas inlet flow path and the gas outlet. The housing has an inner wall defining a surface located in close proximity to radially outer edges of impeller wheel vanes that sweep across said surface as the impeller wheel rotates. At least one opening is provided in the inner wall at the surface. A port is provided in the compressor housing in gas communication with the at least one opening and for diverting gas in a direction away from the gas inlet flow path during relatively low gas flow rate conditions. A gas displacement device such as a pump is disposed outside of the gas inlet flow path and connected to said port, the pump being operable to remove gas selectively through the at least opening and the port in a direction away from said gas inlet flow path. | 02-16-2012 |
20120045312 | VANE CARRIER ASSEMBLY - A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed. | 02-23-2012 |
20120057958 | CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor ( | 03-08-2012 |
20120063879 | ENERGY EFFICIENT IPS BLOWER ASSEMBLY - According to the invention a method and apparatus relating to a blower that is used in an environment of particle contaminated air, as with a helicopter engine, is disclosed. The blower has a power input, a fan, a power output attaching to the fan, and a clutch disposed between the power input and the power output whereby the power input may be selectively coupled to the power output to move the fan to vent the particle contaminated air. The clutch, which may be electrically, mechanically or hydraulically engaged, is activated by a user, a particle or altitude sensor, or by a full authority digital electronic controller (“FADEC”). | 03-15-2012 |
20120063880 | ROTOR ASSEMBLY - A rotor assembly is disclosed herein. The rotor assembly includes a hub disposed for rotation about an axis of rotation. The rotor assembly also includes at least one blade fixed with the hub for concurrent rotation with the hub. The at least one blade extends along a height axis radially outward from the hub with a root portion proximate to the hub at a first end of the height axis and an airfoil portion extending radially inward from a second end of the height axis opposite the first end. The rotor assembly also includes a sheath extending at least partially around the root portion. The sheath is pivotally engaged with the at least one blade to pivot about the height axis and allowed to weathervane to reduce noise. | 03-15-2012 |
20120063881 | ABRADABLE BUCKET SHROUD - The present application provides an abradable bucket shroud for use with a bucket tip so as to limit a leakage flow therethrough and reduce heat loads thereon. The abradable bucket shroud may include a base and a number of ridges positioned thereon. The ridges may be made from an abradable material. The ridges may form a pattern. The ridges may have a number of curves with at least a first curve and a second curve and with the second curve having a reverse camber shape. | 03-15-2012 |
20120063882 | Internally-cooled centrifugal compressor with cooling jacket formed in the diaphragm - An internally-cooled centrifugal compressor ( | 03-15-2012 |
20120063883 | METHODS AND DEVICES FOR LOW SPEED LOW TORQUE TESTING OF A ROTOR IN A TURBOMACHINERY - Methods and devices for performing a low torque low speed test to determine whether a rotor of a turbomachinery is free to rotate are provided. A method includes automatically applying a torque to the rotor, the torque gradually increasing up to a predetermined torque value. The method further includes monitoring the speed of the rotor while the torque is gradually increased. The method also includes outputting an indication that the rotor is free to rotate after the speed of the rotor becomes positive, or outputting an indication that the rotor is locked when the speed of the rotor remains zero and the applied torque has reached the predetermined torque value. | 03-15-2012 |
20120063884 | CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor ( | 03-15-2012 |
20120063885 | FLUID CHANNELING DEVICE FOR BACK-TO-BACK COMPRESSORS - A fluid channeling device including a channeling body, an axial transfer channel, and a radial outlet channel. The channeling body includes first and second annular body sections spaced axially apart and a tubular body section extending between the first and second body sections. The axial transfer channel is defined axially through the channeling body, and is configured to fluidly couple a first compression assembly with a second compression assembly. The radial outlet channel is defined radially through the channeling body and is configured to fluidly couple the second compression assembly with an outlet. | 03-15-2012 |
20120070266 | TURBO-MACHINE TEMPERATURE CONTROL - A method, system, and computer program for turbo-machine temperature control is presented. The method includes: receiving an exhaust temperature (T | 03-22-2012 |
20120070267 | Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor - There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row. | 03-22-2012 |
20120076634 | Turbine Blade Tip Shroud for Use with a Tip Clearance Control System - The present application provides a tip clearance control system for reducing an airflow through a turbo machine. The tip clearance control system may include a casing shroud and a tip shroud positioned within the casing shroud. The tip shroud may include a first step at a leading edge and a second step adjacent to the first step. The casing shroud and the tip shroud may define a first cavity therebetween downstream of the second step. | 03-29-2012 |
20120076635 | NACELLE WITH POROUS SURFACES - A fan nacelle for a gas turbine engine includes a leading edge region with a flow path between an intake region in a nacelle outer surface and an exhaust region in a nacelle inner surface to locally modify a flow around the leading edge region during a predefined off-design condition. | 03-29-2012 |
20120076636 | Controlled Angular Acceleration for Air Moving Devices - Various methods related to air moving devices in electronic systems are disclosed. Various electronic systems including controlled air moving devices are also disclosed. Thus, in one method of controlling an air moving device in an electronic system, the air moving device is operable to accelerate between rotational speeds at a maximum angular acceleration. The method includes limiting an angular acceleration of the air moving device to a first acceleration limit less than the maximum angular acceleration when changing the air moving device from a first rotational speed to a second rotational speed. | 03-29-2012 |
20120087775 | Turbine Bucket Shroud Tail - The present application provides an axial flow turbine. The axial flow turbine may include a stator casing and a turbine bucket positioned about the stator casing. A tip shroud may be positioned on the turbine bucket. A shroud tail may be attached to the tip shroud at a downstream end of the tip shroud. | 04-12-2012 |
20120093627 | METHOD FOR SITE SPECIFIC ENERGY CAPTURE OPTIMIZATION THROUGH MODULAR ROTOR BLADE TIP EXTENSION - A power generating system wherein a turbine ( | 04-19-2012 |
20120093628 | FLUID PUMP CHANGEABLE IN DIAMETER, IN PARTICULAR FOR MEDICAL APPLICATION - The invention relates to a fluid pump device, in particular for the medical application, with a compressible pump housing ( | 04-19-2012 |
20120099960 | SYSTEM AND METHOD FOR COOLING A NOZZLE - A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. The nozzle further includes apertures through at least one of the center body or shroud, a plenum in fluid communication with the apertures, and a louvers proximate to the apertures and connected to at least one of the center body or shroud. A method for cooling a nozzle includes flowing a cooling medium through a plenum inside a center body of the nozzle and flowing the cooling medium through apertures in the center body. The method further includes redirecting the cooling medium with louvers to flow the cooling medium across a surface of the center body. | 04-26-2012 |
20120107085 | Housing and Mass Airflow Rate Control System for a Wind Turbine - The present invention provides control for airflow to a wind turbine that allows a wind turbine to operate cost effectively and efficiently in a wide range of speeds and a variety of ambient conditions. A system has a housing, a wind turbine assembly located within an interior space of the housing, and at least one moveable shutter or deflector. The wind turbine assembly includes a shaft, a plurality of air foils or turbine blades, and a plurality of spars supporting the plurality of air foils or turbine blades rotatably around the shaft. At least one movable shutter or deflector is coupled to the housing and adjustably positioned relative to the open sides of the housing to be able to move between different positions to partially or fully cover each open side depending upon the wind speed of the ambient wind. | 05-03-2012 |
20120107086 | MOTOR ASSISTED FINE PITCH STARTUP RAM AIR TURBINE - A startup assistance apparatus for a fine pitch Ram Air Turbine (RAT) is provided and includes a generator to provide motive power to the RAT when operating in a first mode and to generate electricity from RAT operation when operating in a second mode and a control unit, including a speed sensing unit configured to sense an operating condition of the generator and a controller operably coupled to the generator and configured to control the generator to operate in the first or the second mode based on the sensed operating condition. | 05-03-2012 |
20120107087 | METHOD FOR VARYING THE GEOMETRY OF A MID-TURBINE FRAME - A method for varying the geometry of a mid-turbine frame includes detecting a strain in a mid-turbine frame with a piezoelectric material; applying a deformation voltage to the piezoelectric material as a function of the detected strain; deforming the piezoelectric material to actuate an actuation plate; and repositioning an engine casing through the actuation of the actuation plate. | 05-03-2012 |
20120107088 | DEVICE AND METHOD FOR POSITIONING VARIABLE-GEOMETRY EQUIPMENT FOR A TURBOMACHINE, USING A RELATIVE-MEASUREMENT JACK - A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop. | 05-03-2012 |
20120107089 | Fluid Flow Control System Having a Moving Fluid Expander Providing Flow Control and Conversion of Fluid Energy into Other Useful Energy Forms - A fluid flow control system for controlling flow of a primary fluid to a downstream flow-inducing device includes a moving fluid expander with variable expansion ratio and variable speed arranged to receive the flow of the primary fluid and to expand the primary fluid, resulting in a reduction in temperature of the primary fluid. The system further includes an optional heat exchanger arranged to receive the reduced-temperature primary fluid as well as a higher-temperature secondary fluid and to cause varying degrees of heat exchange between the primary and secondary fluids such that the secondary fluid is cooled by the primary fluid. The primary fluid is discharged from the heat exchanger and is supplied to the flow-inducing device. | 05-03-2012 |
20120114458 | SHROUD LEAKAGE COVER - A method and system for improving performance of a compressor section of a gas turbine by diverting leakage air flowing from high pressure downstream of a stator vane assembly to low pressure upstream of the stator vane assembly from disrupting design flow patterns at a leading edge of stator vanes. A cover is provided at a forward face of an inner shroud assembly to prevent the leakage air from impinging on the leading edge. The cover may be provided at an outlet channel of a flow diverter mounted on the forward face of the inner shroud assembly. | 05-10-2012 |
20120114459 | Axial compressor and associated operating method - An axial compressor for compressing a flow medium is provided and includes compressor stator blades, which fastened on a stator blade carrier, and compressor rotor blades, which are fastened on a compressor disk of a compressor shaft, wherein two consecutive compressor disks enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space. A cooling medium feed duct leads through a stator blade carrier and a compressor stator blade, and is arranged upstream of the last compressor disk, which cooling medium feed duct, at the tip end of the compressor stator blade facing the compressor shaft, via a discharge opening arranged there, opens into the hollow space, wherein this hollow space, via a cooling medium transfer passage which is led through the subsequent compressor disks, is connected to the rear hollow space. | 05-10-2012 |
20120121373 | Cranking Pad Interlock - A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing. | 05-17-2012 |
20120121374 | Rotor Coupling Guard - The present application provides a rotor coupling guard for use with removing a flow of air about a rotor coupling of a turbo-machine. The rotor coupling guard may include an inner cover with a number of apertures surrounding the rotor coupling and an outer cover surrounding the inner cover. Rotation of the rotor coupling forces the flow of air through the apertures in the inner cover and away from the rotor coupling. | 05-17-2012 |
20120121375 | VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes. | 05-17-2012 |
20120121376 | METHOD OF CONTROLLING A COMPRESSOR AND APPARATUS THEREFOR - The present invention relates to a method of controlling a compressor and an apparatus therefor, the method, comprising at least the steps of: (a) providing a compressor feed stream ( | 05-17-2012 |
20120121377 | GAS TURBINE ARRANGEMENT AND METHOD FOR OPERATING A GAS TURBINE ARRANGEMENT - A gas turbine arrangement and a method of operating are provided. The turbine includes an annulus, axially delimited between a rotor unit, and at least one stationary component. Cooling medium outlet openings, lead into the annulus, from the stationary component. The cooling medium flows into cooling medium inlet openings, in the rotor unit in a flow direction, which propagates through the annulus. At least one inner cavity, radially to the annulus, is delimited by the rotor unit and by the stationary component. The inner cavity is pressurized with a purging gas, and is fluidically connected to the annulus. The stationary component and the rotor unit include a constriction by which the inner cavity is separated from the radially outer annulus and via which the inner cavity is fluidically connected to the radially outer annulus. Flow guides, fastened on the stationary component on one side, project into the constriction. | 05-17-2012 |
20120121378 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine and a compressor hub driven by the first shaft. The compressor hub is within a compressor section of the gas turbine engine. An epicyclic gear train is driven by the first shaft. A common attachment point secures the first shaft and the compressor hub to the second shaft. | 05-17-2012 |
20120128463 | SYSTEM AND METHOD FOR MANAGING THERMAL ISSUES IN ONE OR MORE INDUSTRIAL PROCESSES - The present invention generally relates to a system that enables one to both: (i) address various thermal management issues (e.g., inlet air cooling) in gas turbines, gas turbine engines, industrial process equipment and/or internal combustion engines; and (ii) yield a supercritical fluid-based heat engine. In one embodiment, the present invention utilizes at least one working fluid selected from ammonia, carbon dioxide, nitrogen, or other suitable working fluid medium. In another embodiment, the present invention utilizes carbon dioxide or ammonia as a working fluid to achieve a system that enables one to address inlet cooling issues in a gas turbine, internal combustion engine or other industrial application while also yielding a supercritical fluid based heat engine as a second cycle using the waste heat from the gas turbine and/or internal combustion engine to create a combined power cycle. | 05-24-2012 |
20120141248 | ACTIVE FAN FLUTTER CONTROL - A flutter control system for a turbomachine fan includes a plurality of fan case sensors located at a fan case of the turbomachine and configured to sense passing of blade tips of a fan of the turbomachine. A controller is operably connected to the plurality of fan case sensors. A variable fan area nozzle actuator is operably connected to the controller, such that the variable fan area nozzle actuator urges a change in fan nozzle area in response to data from the plurality of fan case sensors indicating flutter or near flutter conditions. A method of flutter control for a turbomachine fan includes sensing a blade tip passing of a plurality of fan blades. Data from a plurality of fan case sensors is compared to a threshold and a fan exit area is changed based on the comparison to dampen flutter of the plurality of fan blades. | 06-07-2012 |
20120141249 | FLUID FLOW CONTROL PROVIDING INCREASED ENERGY EXTRACTION - Systems and methods configured to control ambient fluid flow for increased energy extraction using a turbine are disclosed. In various examples, a system can include a convergent nozzle configured to receive and accelerate an ambient flow of fluid and a turbine including one or more rotor blades. The convergent nozzle can include a configuration having a ratio of a nozzle inlet area to a nozzle outlet area between about 1.5:1 to about 10:1, inclusive. An interior nozzle surface can include one or more contours aligned with a direction of the ambient flow of fluid. The convergent nozzle can include apertures in a region near a nozzle outlet. The apertures can be selectively controlled to draw additional fluid flow into the accelerated flow to avoid excessive stress on turbine components. The rotor blades can have a length equal to or slightly greater than a radius of the nozzle outlet. | 06-07-2012 |
20120141250 | WIND TURBINE SHROUD - A shroud for a wind turbine and a method for modifying performance of a wind turbine are disclosed. The wind turbine includes a rotor mounted to a nacelle, the rotor including a plurality of rotor blades and defining an outer diameter. The shroud is positioned downstream of the rotor in an air flow direction, and has an inner diameter of less than the outer diameter of the rotor. | 06-07-2012 |
20120141251 | METHOD AND DEVICE FOR PREDICTING THE INSTABILITY OF AN AXIAL COMPRESSOR - The present invention relates to a method and device for predicting the instability of an axial compressor, which is applicable to the aerospace and industrial field, specifically to the field of one- or multi-stage axial compressors. The invention relates to a method and a device for predicting the instability of an axial compressor which allows protecting said compressor from the instabilities of devices of this type. The present invention could be used in all those products requiring the use of said compressors, such as aircraft engines, turbofans, turboshafts, or turboprops in the aerospace field, gas turbines in the energy field, air conditioning systems in the civil field, and gas compression systems in the chemical or oil industry. | 06-07-2012 |
20120141252 | Wind Turbine - A wind driven turbine device is disclosed that includes a housing having an air inlet and an air outlet, a turbine rotor having a plurality of radially distributed turbine rotor blades mounted in the housing for rotation in direct response to atmospheric wind to thereby generate rotary power, a baffle arrangement is also provided for directing wind through the housing from the air inlet to contact the turbine rotor blades from a plurality of angles as internal driving wind. | 06-07-2012 |
20120141253 | TURBOMACHINE - A turbomachine is disclosed. The turbomachine includes a housing and a guide blade ring. An outer shroud of the guide blade ring is divided into segments by joints, where the outer shroud is fastened to the housing by a first fastening element for absorbing axial force and a second fastening element independent of the first fastening element for absorbing circumferential force. The first fastening element and the second fastening elements enable play in a radial direction for the segments of the outer shroud. | 06-07-2012 |
20120148382 | METHOD AND APPARATUS FOR THE MODEL-BASED MONITORING OF A TURBOMACHINE - The method for the model-based monitoring of a turbomachine by means of a monitoring unit which receives relevant process parameters of the turbomachine, carries out calculations on the basis of these parameters and, as a result, determines one or more state values, by means of which the state of the turbomachine can be assessed, the calculations of the state values being carried out on the basis of one or more physical models of at least one subsystem of the turbomachine, wherein the at least one subsystem is an axial bearing of the turbomachine, and the one or more state values are selected from the axial thrust force, the axial bearing load and the axial shaft attitude. | 06-14-2012 |
20120156004 | METHOD FOR SHUTTING DOWN A TURBOMACHINE - A method for increasing the operational flexibility of a turbomachine during a shutdown phase is provided. The turbomachine may include a first section, a second section, and a rotor disposed within the first section and the second section. The method may determine an allowable range of a physical parameter associated with the first section and/or the second section. The method may modulate a first valve and/or a second valve to allow steam flow into the first section and the second section respectively, wherein the modulation is based on the allowable range of the physical parameter. In addition, the physical parameter allows the method to independently apportion steam flow between the first section and the second section of the turbomachine, during the shutdown phase. | 06-21-2012 |
20120156005 | BUFFER AIR FOR A LABYRINTH SEAL - A method of providing buffer air to a labyrinth seal includes operating a multi-stage compressor system having an earlier stage and a later stage such that the air pressure at the later stage is higher than the air pressure at the earlier stage. The method may further include selectively directing compressed air from one of the earlier stage or the later stage to the seal based on a parameter indicative of air pressure within the compressor system. | 06-21-2012 |
20120163955 | SYSTEM AND METHOD TO ELIMINATE A HARD RUB AND OPTIMIZE A PURGE FLOW IN A GAS TURBINE - A system and method to eliminate hard rub and optimize a purge flow in a gas turbine is provided. The gas turbine includes a stator configured to guide a flow of an incoming gas. The gas turbine also includes a rotor configured to expand the incoming gas and extract kinetic energy from the incoming gas. The gas turbine further includes a purge flow bled from a compressor and configured to reduce a temperature of a wheel space by limiting ingestion of the incoming gas. The gas turbine also includes an angel wing disposed between the rotor and the stator and configured to act as a sealing surface between the rotor and the stator. The gas turbine further includes a fan blade disposed on a surface of the angel wing at an axial position and configured to generate a recirculation zone of the purge flow, wherein the recirculation zone is reduces a volume of successive purge flows entering the wheel space. | 06-28-2012 |
20120171010 | REMOVABLE STEAM INLET ASSEMBLY FOR STEAM TURBINE - A removable steam inlet assembly and lifting fixture for a steam turbine are provided to facilitate lifting of the upper exhaust hood of the steam turbine. The removable steam inlet assembly is detached from the steam inlet of the turbine inner casing for the lift and mounted to the upper exhaust hood with a lifting fixture. Detaching and removal of the steam inlet assembly substantially lowers the clearance height for the lift, allowing lower turbine building height with significant cost savings. | 07-05-2012 |
20120177476 | TURBOCHARGER OPERATING SYSTEM AND METHOD FOR AN INTERNAL COMBUSTION ENGINE - A method of operating a turbocharger apparatus on an internal combustion engine, having a first oil circuit and a second oil circuit, includes steps of sensing a plurality of engine operating parameters via a plurality of sensors associated with the internal combustion engine; providing oil to the engine from the first oil circuit at a first pressure level; controlling operation of the second oil circuit for said engine via an electronic control unit, based on the sensed engine operating parameters; and applying a variable hydraulic preload to said first and second bearing assemblies via the operation of the second oil circuit, wherein oil from the second oil circuit is provided at a second pressure level which is different from the first pressure level. A system usable for carrying out such method is also described. | 07-12-2012 |
20120183385 | METHOD FOR PREVENTING SURGE IN A DYNAMIC COMPRESSOR USING ADAPTIVE PREVENTER CONTROL SYSTEM AND ADAPTIVE SAFETY MARGIN - A method of preventing surge in a dynamic compressor is disclosed. The method includes providing an anti-surge valve having an adjustable opening for increasing the flow through a dynamic compressor. The next step is sensing process conditions in the dynamic control to determine a compressor load variable. A control system estimates a process disturbance model using the compressor load variable. The control system then adjusts a safety margin using a rate limited response and initiates a closed loop response using process feedback based on the process disturbance model. The control system adjusts the opening of the anti-surge valve according to the safety margin and closed loop response. | 07-19-2012 |
20120183386 | COOLED GAS TURBINE ENGINE MEMBER - A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer. | 07-19-2012 |
20120189424 | MATEFACE COOLING FEATHER SEAL ASSEMBLY - A feather seal assembly includes a seal having a directional passage to direct an airflow generally non-perpendicular to the seal. | 07-26-2012 |
20120189425 | SYSTEM AND METHOD FOR REDUCING CORROSION IN A COMPRESSOR - A system for reducing corrosion in a compressor includes a compressor blade having a corrosion potential. A sensor connected to the compressor blade generates a signal reflective of the corrosion potential. A power supply connected to the compressor blade at an electrical connection produces an electrical potential at the electrical connection. An electrolyte coats at least a portion of the sensor and the electrical connection. A method for reducing corrosion in a compressor includes sensing a corrosion potential of a compressor blade and generating a signal reflective of the corrosion potential. The method further includes generating an electrical potential at an electrical connection on the compressor blade and flowing an electrolyte over at least a portion of the compressor blade and the electrical connection. | 07-26-2012 |
20120189426 | BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT - An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member. An example blade outer air seal assembly includes a blade outer air seal assembly having an inwardly facing surface. A blade path portion of the inwardly facing surface is axially aligned with a tip of a rotating blade. A peripheral portion of the inwardly facing surface is located axially in front of the blade path portion, axially behind the blade path portion, or both. The blade outer air seal assembly establishes cooling paths that terminate at a plurality of apertures established within the inwardly facing surface. The plurality of apertures are locate exclusively within the blade path portion. | 07-26-2012 |
20120189427 | GAS TURBINE ENGINE FLOW PATH MEMBER - A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction. | 07-26-2012 |
20120195736 | Plasma Actuation Systems to Produce Swirling Flows - The present application provides a plasma actuation system for a turbo-machinery device. The plasma actuation system may include an end wall, a number of end wall actuators positioned about the end wall, and a blade positioned adjacent to the end wall. The end wall actuators are oriented to produce a swirling flow between the end wall and the blade. | 08-02-2012 |
20120201650 | PASSIVE COOLING SYSTEM FOR A TURBOMACHINE - A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket. | 08-09-2012 |
20120201651 | CONTROL UNIT AND A METHOD FOR CONTROLLING BLADE TIP CLEARANCE - A method and system for controlling clearance between the tips of blades of a turbine rotor in a gas turbine airplane engine and a turbine ring of a casing surrounding the blades. A valve is controlled to act on a flow rate and/or a temperature of air directed against the casing. The valve is of the on/off type for switching between an open state and a closed state in a determined reaction time, the valve control module including a corrector for determining a first binary control signal that can take a first value corresponding to an open state and a second value corresponding to a closed state of the valve. The corrector includes a time-delay module for determining a binary control signal, with the duration between two successive changes of state in the control signal being not less than the reaction time of the valve. | 08-09-2012 |
20120207583 | CASE WITH BALLISTIC LINER - A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case. | 08-16-2012 |
20120219398 | METHOD OF DETECTING AND CONTROLLING STALL IN AN AXIAL FAN - A method of detecting stall in an axial fan through acoustical measurements in air the air flow, includes measuring the sound emanating from the flow adjacent the fan, preparing a visual representation of the sound, comparing the visual representation with a library of fixed visual representations derived from a plurality of tests representative of the performance of the fan under a range of operating parameters, selecting the fixed visual representation most closely matching the visual representation of the said sound, and deriving a control signal from the selected fixed visual representation. The visual representations are formed by a symmetrised dot pattern (SDP) technique. | 08-30-2012 |
20120219399 | ELECTRIC DEVICE - An electric device has a casing with an air-inlet and an air-outlet, a main unit disposed inside the casing, a first temperature sensor for detecting the temperature inside the casing, a second temperature sensor for detecting the temperature outside the casing, an electric fan, and a control unit. The control unit rotates the electric fan at the time of the low-temperature startup such that the temperature detected by the first temperature sensor is lower than a preset first threshold value, while the temperature detected by the second temperature sensor is higher than the temperature detected by the first temperature sensor. | 08-30-2012 |
20120230810 | SHROUNDED WIND TURBINE CONFIGURATION WITH NOZZLE AUGMENTED DIFFUSER - Disclosed are a system, a method and an apparatus of diffuser nozzle augmented wind turbine. In one embodiment, a method includes attaching a nozzle with a streamlined opening to a diffuser to direct an air flow into a wind turbine. In addition, the method includes increasing a wind speed approaching a set of turbine blades within a shrouded wind turbine configuration. The method also includes recirculating the air within the shroud configuration to increase an output power generated through the wind turbine. The system is composed of diffuser and nozzle integrated and non-integrated with and without a flange. In one embodiment, a method includes increasing a pressure differential of a wind turbine. | 09-13-2012 |
20120237332 | FLUID-COOLING DEVICE FOR A TURBINE ENGINE PROPULSIVE UNIT - The invention relates to a fluid cooling device ( | 09-20-2012 |
20120243970 | ARRANGEMENT AND METHOD FOR CLOSED FLOW COOLING OF A GAS TURBINE ENGINE COMPONENT - An arrangement for cooling a gas turbine engine component includes a gas turbine engine component provided with at least one cooling channel through which a cooling medium is intended to flow during operation of the arrangement, a feeding system configured to supply cooling medium to the cooling channel, a cooling channel inlet, and a cooling channel outlet. The feeding system is arranged in flow communication with both the inlet and the outlet of the cooling channel such as to form a closed flow system. A gas turbine engine provided with such a component and a method for cooling such a component are also provided. | 09-27-2012 |
20120251290 | ASPIRATING FACE SEAL, AND A RELATED METHOD THEREOF - An aspirating face seal includes a primary seal, a secondary seal, and a biasing device. The primary seal includes a first seal component and a second seal component. The first seal component is configured to be coupled to a rotor and rotatable with the rotor. The secondary seal includes a plurality of flexible elements and configured to be disposed between the second seal component and a stator housing. A biasing device is coupled to the second seal component such that the second seal component is biased along an axial direction away from the first seal component during a non-operating condition. | 10-04-2012 |
20120251291 | STATOR-ROTOR ASSEMBLIES WITH FEATURES FOR ENHANCED CONTAINMENT OF GAS FLOW, AND RELATED PROCESSES - A stator-rotor assembly is described, including at least one interface region and a gap between a surface of the stator and a surface of the rotor. The stator is a nozzle or vane that includes circumferential endwalls. Each endwall includes at least one leading edge and one trailing edge, relative to a hot gas flow path. A trailing edge of at least one of the endwalls includes a pattern of cavities that are capable of impeding the entry of hot gas into a wheelspace region that adjoins the gap between the stator and the rotor. The cavities can also be formed on various sections of the rotor. The stator-rotor assembly can be incorporated into various turbomachines, such as gas turbine engines. Related processes are also described. | 10-04-2012 |
20120251292 | METHOD AND ARRANGEMENT FOR ESTIMATING FLOW RATE OF PUMP - A method and arrangement for determining the flow rate (Q) produced by a pump, when the pump is controlled with a frequency converter, which produces estimates for rotational speed and torque of the pump, and the characteristic curves of the pump are known. The method includes determining the shape of a QH curve of the pump, dividing the QH curve into two or more regions depending on the shape of the QH curve, determining on which region of the QH curve the pump is operating, and determining the flow rate (Q) of the pump using the determined operating region of the characteristic curve. | 10-04-2012 |
20120257954 | METHOD FOR COOLING TURBINE STATORS AND COOLING SYSTEM FOR IMPLEMENTING SAID METHOD - A method and system for cooling turbine engine turbines, the system includes: at least one pair of parts to be cooled, the pair including a stator upstream from the rotor valve, and a sealing ring mounting a downstream movable blade rotor that is adjacent to the stator; a turbine casing; and an outlet path. The system further includes: at least one opening in the casing facing at least one part to be cooled; and an air circuit producing a forced convection in connection with the parts and at least one downstream outlet in the path so as to draw in and transport an ambient air flow. | 10-11-2012 |
20120263571 | VARIABLE VANE FOR GAS TURBINE ENGINE - A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button. | 10-18-2012 |
20120263572 | TURBINE FOR CONVERTING ENERGY AND METHOD FOR OPERATING THE SAME - A turbine and a method for converting energy are provided, wherein an angular position of an exit of a cooling duct in the casing depends on angular positions of a downstream edge | 10-18-2012 |
20120269612 | TURBINE INLET CASING WITH INTEGRAL BEARING HOUSING - The present application provides a compressor inlet casing. The compressor inlet casing may include an inner bellmouth and a bearing housing. The bearing housing may include an integrally cast first half connected to the inner bellmouth and a cavity positioned between the inner bellmouth and the integrally cast first half of the bearing housing. | 10-25-2012 |
20120275898 | Blade Clearance Control Using High-CTE and Low-CTE Ring Members - An engine has a blade stage and a circumferential array of blade outer air seal segments. A support ring carries the blade outer air seal segments. The support ring has a low-CTE member and a high-CTE member intervening between the blade outer air seal segments and the low-CTE member. | 11-01-2012 |
20120275899 | AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS - The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning. | 11-01-2012 |
20120282078 | BEARING ASSEMBLY WITH DAMPING FEATURES - A turbocharger bearing assembly can include a compressor side bearing; a turbine side bearing; and a spacer configured to axially space the compressor side bearing and the turbine side bearing where the spacer includes lubricant passages to direct lubricant to spacer-bearing interfaces and where the spacer optionally includes a spring disposed in a central through bore to load the bearings. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 11-08-2012 |
20120282079 | REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR - In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor. | 11-08-2012 |
20120288357 | VERTICAL MULTI-PHASED WIND TURBINE SYSTEM - A rotational axis multi-phased wind turbine power generating system is disclosed. A differential pressure is created by utilizing the prevailing wind, and air from the prevailing wind is directed into air blades for the creation of power. Optimally, the air blades directly utilize the prevailing wind in combination with the created differential pressure to create power. An adjustable air scoop, adjustable exit drag curtain or barrier, orienting systems, and air flow directing dampers are disclosed. | 11-15-2012 |
20120294703 | DIFFUSER DIVIDER - A diffuser divider shaped as disc with a central axis, a leading edge disposed at an inner radius about the central axis, a trailing edge disposed at an outer radius about the central axis, an upper surface disposed between the leading edge and the trailing edge, a lower surface disposed between the leading edge and the trailing edge and one or more mounting features configured to mount the disc in a diffuser section configured to receive air compressed by two compressor wheel faces and to direct the compressed air to a volute. Such a divider can define throats in a diffuser section of a compressor assembly. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 11-22-2012 |
20120301267 | CONDUCTING UNIT, AND CONDUCTING METHODS - The invention relates to a delivering unit for gas, comprising a compressor ( | 11-29-2012 |
20120301268 | Supersonic Cooling With Pulsed Inlet and Bypass Loop - A supersonic cooling system operates by pumping liquid without the need of a condenser. An inlet of the system may be pulsed to reduce energy required of a pump and to increase the cooling power of the system. The supersonic cooling system utilizes a compression wave in the generation of the cooling effect. The formation of the compression wave may be assisted by a resonance chamber. An evaporator of the cooling system operates in the critical flow regime. | 11-29-2012 |
20120301269 | CLEARANCE CONTROL WITH CERAMIC MATRIX COMPOSITE ROTOR ASSEMBLY FOR A GAS TURBINE ENGINE - A gas turbine engine includes a CMC static structure and a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure. | 11-29-2012 |
20120301270 | SUPERSONIC COMPRESSOR STARTUP SUPPORT SYSTEM - A supersonic compressor includes a fluid inlet, fluid outlet, and a fluid conduit extending therebetween with a supersonic compressor rotor disposed therein. The supersonic compressor rotor includes a first endwall and a plurality of vanes coupled thereto. Each pair of the vanes defines a fluid flow channel. The fluid flow channel defines a flow channel inlet opening and a flow channel outlet opening and includes a throat portion. The supersonic compressor rotor also includes a second endwall and at least one axially translatable fluid control device positioned adjacent to the rotor. The axially translatable fluid control device is configured to obstruct the throat portion and includes at least one axially translatable protrusion insertable into at least a portion of the throat portion. | 11-29-2012 |
20120301271 | SUPERSONIC COMPRESSOR ROTOR AND METHOD OF COMPRESSING A FLUID - A supersonic compressor rotor. The supersonic compressor rotor includes a substantially cylindrical disk body that includes an upstream surface, a downstream surface, and a radially outer surface that extends generally axially between the upstream surface and the downstream surface. The disk body defines a centerline axis. A plurality of vanes are coupled to the radially outer surface. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends generally axially between an inlet opening and an outlet opening. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is selectively positionable at a first position, at a second position, and at any position therebetween. | 11-29-2012 |
20120301272 | VORTEX REDUCER - The present disclosure relates to a vortex reducer ( | 11-29-2012 |
20120315125 | TURBINE BLADES WITH MIXED BLADE LOADING - An unevenly loaded turbine blade is disclosed including a first region configured for extracting power from a fluid flow and a second region configured for adding power to the fluid flow. The power extracted from the fluid flow is typically greater than the power added to the fluid flow resulting in a net power extracted for the blades. The addition of power to the fluid flow advantageously results in localized injections of high velocity fluid flow which provide distributed mixing of wake and tip vortices along the length of the blade. | 12-13-2012 |
20120321437 | TURBINE SEAL SYSTEM - A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage including a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage including a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal extending axially between the first and second turbine stages. The interstage seal is configured to be installed or removed while the first and second wheels remain in place in the respective first and second turbine stages. | 12-20-2012 |
20120321438 | COMPRESSOR UNIT AND A METHOD TO PROCESS A WORKING FLUID - A compressor unit for processing a working fluid comprising a compressor inside a housing to compress the working fluid wherein a collection chamber is fluidly coupled with a working fluid inlet of said housing. | 12-20-2012 |
20120321439 | Eddy Current Damper and Method - An apparatus for supporting a shaft of a turbomachine. The apparatus may include a magnetic bearing to support the shaft during a normal operation of the turbomachine, and an auxiliary bearing to support the shaft during a drop event. The apparatus may also include a disk coupled to the shaft and comprising a substantially non-ferrous, conductive material, and a magnetic assembly disposed proximal the disk, the magnetic assembly configured to magnetically engage the disk to damp vibrations during the drop event, to apply a circumferential braking force on the disk during the drop event, or both. | 12-20-2012 |
20120328409 | SYSTEMS AND METHODS FOR COOLING HIGH PRESSURE AND INTERMEDIATE PRESSURE SECTIONS OF A STEAM TURBINE - The present application provides a section cooling system for a steam turbine to limit a leakage flow therethrough. The section cooling system may include a first pressure flow extraction from a first section to a shaft packing location between the first section and a second section and a rotor aperture extending towards the first section. The first pressure flow extraction diverts the leakage flow from the first section into the rotor aperture so as to limit the leakage flow to the second section. | 12-27-2012 |
20120328410 | SURGE ESTIMATOR - A method of correcting surge control parameters that includes providing a dynamic compressor having a compressor, driver, surge valve, and control system. The control system establishes surge control parameters such as surge detection lines, surge limit lines, and then detects the onset of a surge in the dynamic compressor. When the surge is detected the control system measures variables of the dynamic compressor such as fluid pressure, fluid speed, power, speed and valve position and based on these variables the control system automatically corrects the surge control parameters based on these variables at the time of the onset of the surge is detected. Advisory information is provided by control system to user for corrective actions to prevent surge. | 12-27-2012 |
20120328411 | MULTI-STAGE TURBOCHARGER SYSTEM WITH EXHAUST CONTROL VALVE - A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports. | 12-27-2012 |
20130004290 | Turbo-Machinery With Flow Deflector System - The present application provides a turbo-machine. The turbo-machine may include a number of buckets, a number of nozzles, and a flow deflector system. The flow deflector system may include a bucket deflector and a nozzle deflector so as to limit leakage flow losses therethrough. | 01-03-2013 |
20130004291 | Turbomachine Fluid-Conduit Housing Coupling System and Method - A shroud portion of a fluid-conduit housing provides for concentrically shrouding a portion of bladed rotor operatively coupled to a rotor shaft rotationally supported by at least one bearing operatively coupled to the centerbody. An internal cylindrical surface at an end of the fluid-conduit housing mates with a corresponding external cylindrical surface on a corresponding side of the centerbody. The fluid-conduit housing is operatively coupled to the centerbody with a plurality of radial pins, wherein each radial pin slideably engages with at least one of a corresponding radial bore in the fluid-conduit housing or a corresponding radial bore in the centerbody so as to provide for substantially maintaining the concentricity of the shroud portion of the fluid-conduit housing relative to the bladed rotor regardless of a thermal expansion of the fluid-conduit housing relative to the centerbody. | 01-03-2013 |
20130004292 | CONTROL STRATEGY FOR DECREASING RESONANCE IN A TURBOCHARGER - A method for operation of an engine including a turbocharger system is provided. The method includes adjusting turbocharger rotational acceleration or deceleration in response to one or more resonant frequencies. Additionally in some examples, the method may further include increasing turbocharger rotation in response to one or more resonant frequencies during a first condition, and increasing turbocharger deceleration in response to one or more resonant frequencies during a second condition, the second condition different from the first condition. In this way, it is possible to enhance the useful life cycle of the turbocharger and associated engine by limiting the operating time in a resonant frequency band. | 01-03-2013 |
20130017057 | BLADE OUTER AIR SEAL ASSEMBLYAANM Lagueux; KenAACI BerlinAAST CTAACO USAAGP Lagueux; Ken Berlin CT US - An example blade outer air seal assembly includes a blade outer air seal that is biased toward a second part. The blade outer air seal and the second part move together radially during operation. Radial inward movement of the blade outer air seal is limited exclusively by the second part during operation. | 01-17-2013 |
20130017058 | BLADE OUTER AIR SEAL HAVING PARTIAL COATINGAANM Joe; Christopher R.AACI WethersfieldAAST CTAACO USAAGP Joe; Christopher R. Wethersfield CT USAANM Lutjen; Paul M.AACI KennebunkportAAST MIAACO USAAGP Lutjen; Paul M. Kennebunkport MI USAANM Mongillo, JR.; Dominic J.AACI West HartfordAAST CTAACO USAAGP Mongillo, JR.; Dominic J. West Hartford CT US - A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating. | 01-17-2013 |
20130017059 | HOLE FOR ROTATING COMPONENT COOLING SYSTEMAANM Wu; Charles C.AACI GlastonburyAAST CTAACO USAAGP Wu; Charles C. Glastonbury CT USAANM McCusker; Kevin N.AACI West HartfordAAST CTAACO USAAGP McCusker; Kevin N. West Hartford CT USAANM Turner; Mark S.AACI HartfordAAST CTAACO USAAGP Turner; Mark S. Hartford CT US - A rotor for a gas turbine engine comprises an annular body and a plurality of holes. The annular body is configured to rotate in a circumferential direction about an axis extending through a center of the annular body. The annular body comprises an outer diameter surface and an inner diameter surface. The plurality of holes extends through the annular body. Each of the holes comprises an elongate profile in the circumferential direction, and a side wall extending between the outer diameter surface and the inner diameter surface. The side wall is slanted in the circumferential direction. | 01-17-2013 |
20130017060 | TIP CLEARANCE CONTROL FOR TURBINE BLADESAANM BOSWELL; John H.AACI DerbyAACO GBAAGP BOSWELL; John H. Derby GBAANM TIBBOTT; IanAACI LichfieldAACO GBAAGP TIBBOTT; Ian Lichfield GB - An arrangement for heating and cooling a turbine casing of a gas turbine engine, the arrangement comprising an inboard duct, adjacent to an inboard surface of the turbine casing, an outboard facing wall of the inboard duct having a plurality of impingement holes opening towards the inboard surface of the casing, through which temperature control fluid can pass from within the inboard duct to impinge upon the inboard surface of the turbine casing. | 01-17-2013 |
20130017061 | TURBOCHARGER VANE | 01-17-2013 |
20130022442 | SYSTEM AND METHOD FOR OPERATING A TURBINE - A system for operating a turbine includes a rotating component and a non-rotating component separated from the rotating component by a clearance. A first actuator is connected to the non-rotating component, and the first actuator comprises a shape-memory alloy. A method for operating a turbine includes sensing a parameter reflective of a clearance between a non-rotating component and a rotating component and generating a parameter signal reflective of the clearance. The method further includes generating a control signal to at least one actuator based on the parameter signal and moving at least a portion of the non-rotating component relative to the rotating component to change the clearance. | 01-24-2013 |
20130022443 | FAN MOTOR COOLING - An example fan assembly impeller moves air along a secondary flow path when driven by a motor. The motor also drives a fan rotor to move air along a primary flow path of the fan assembly. Air moving along the primary flow path moves in a first direction. Air moving along the secondary flow path moves in a second direction opposite the first direction. An example fan shroud communicates air used to cool a motor into a primary flow path of a fan assembly. The shroud communicates the air into the primary flow path so that the flow of air is at least partially aligned with air moving through the primary flow path of the fan assembly. | 01-24-2013 |
20130022444 | LOW PRESSURE TURBINE EXHAUST DIFFUSER WITH TURBULATORS - A turbine exhaust diffuser for use adjacent a last stage row of buckets fixed to a turbine rotor includes an annular inner diffuser ring and an annular outer diffuser ring defining a flow path for steam exiting a last stage row of buckets in a first substantially axial direction at a diffuser inlet, and turning substantially ninety degrees to a diffuser outlet. The outer diffuser ring has a curved steam guide surface extending between the diffuser inlet and the diffuser outlet including a first portion extending away from the diffuser inlet and a second portion extending to said diffuser outlet, the second portion shaped to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in a second opposite axial direction. The second portion is also provided with a plurality of turbulators to minimize flow separation along the steam guide surface. | 01-24-2013 |
20130022445 | System for Reducing Compressor Oil Consumption - An air induction system for a power source including a first compressor and a second compressor is disclosed. The air induction system includes an air feed passageway that directs compressed air from the second compressor to an area between a compressor wheel and a center housing in the first compressor to reduce oil consumption in the first compressor. | 01-24-2013 |
20130022446 | FLUIDIC DAMPENING FILM SUPPLY METHOD FOR A GUIDING BEARING OF A TURBINE ENGINE SHAFT - A fluidic dampening film supply method for a guiding bearing of a turbine engine shaft, said turbine engine being known to vibrate according to at least one given vibratory mode, said turbine engine being adapted to enter in resonance at a given resonance speed (w | 01-24-2013 |
20130022447 | CENTRIFUGAL PUMP FOR DE-WATERING - A method of de-watering during intermittent dry running periods with a self-priming centrifugal pump is presented. Centrifugal pumps, as opposed to diaphragm pumps, are advantageous because they are less expensive and can provide greater capacity. The shaft seals are sensitive, however, to frictional heating when water flow is interrupted. In some situations, this fractional heating may desiccate self-priming. The inventive concept provides a continuous stream of pressurized water moving through the pump to cool the seal and sustain priming capability without substantially impairing the ability of the pump to resume wet operation. | 01-24-2013 |
20130028704 | BLADE OUTER AIR SEAL WITH PASSAGE JOINED CAVITIES - A blade outer air seal assembly includes a body that defines a first cavity separated from a second cavity by a circumferential rib. The circumferential rib includes at least one passage which provides communication between the first cavity and the second cavity. | 01-31-2013 |
20130028705 | GAS TURBINE ENGINE ACTIVE CLEARANCE CONTROL - An active clearance control system utilizes a working fluid stream to control radial thermal growth and thereby a clearance between turbine blades and a corresponding shroud of a gas turbine engine. Conduits disposed about a turbine case and proximate to pads defined within the turbine case include a flow surface parallel to the pads. The pads are an area of increased thickness in the turbine case that receives impingement flow from the conduits. Grooves within the pads further increase impingement cooling flow effectiveness. The increased thickness of the pads provides the thermal mass desired to effect thermal expansion and contraction responsive to the cooling airflow. | 01-31-2013 |
20130028706 | METHOD AND APPARATUS FOR ADJUSTING IMPELLER/RING CLEARANCE IN A PUMP - In a pump arrangement, each adjusting screw has first and second end portions, a third intermediate raised portion, and a fourth portion to allow each adjusting screw to be rotated clockwise/counterclockwise. Each first end portion passes through a suction liner aperture so left-handed threads couple to a respective left-handed seal ring aperture. Each second portion passes through a suction half casing aperture so the fourth portion can be accessed to allow clockwise/counterclockwise rotation of each adjusting screw. Each adjusting screw rotates clockwise and moves until the third portion pushes against the suction half casing, so the screw stops moving and the seal ring moves away from the suction liner as the screw is rotated clockwise, or rotates counterclockwise and moves until the third portion pushes against the suction liner, so the screw stops moving and the seal ring moves towards the suction liner as the screw is rotated counterclockwise. | 01-31-2013 |
20130028707 | METHOD FOR INJECTING WATER INTO A MULTISTAGE AXIAL COMPRESSOR OF A GAS TURBINE - A method is disclosed for injecting water into a multistage axial compressor of a gas turbine. With low equipment cost, a significant power enhancement can be achieved, even under changing boundary conditions, by water being injected at a plurality of points along the axial compressor, and by the injected water mass flow being controlled at the individual injection points in accordance with ambient conditions and operating parameters of the gas turbine in such a way that an evened-out loading in the individual stages of the axial compressor can be created. | 01-31-2013 |
20130034423 | SYSTEM AND METHOD FOR PASSIVELY CONTROLLING CLEARANCE IN A GAS TURBINE ENGINE - A system for passively controlling clearance in a turbine engine comprises a static assembly arranged circumferentially about an engine rotor assembly and defining a gap between a tip end of the rotor assembly and an adjacent inner surface of the static assembly. The static assembly includes a gap control member that defines the inner surface, is exposed to the engine working fluid, and comprises a shape memory material selected and preconditioned to deform in a pre-selected manner in response to a temperature of the engine working fluid. Alternatively, airfoil blades of the rotor assembly include a gap control member. A method for passively controlling clearance in a turbine engine comprises assembling the engine so as to define an initial set of build clearances, operating the engine to observe running clearances, configuring a gap control member comprising a shape memory material and re-assembling the engine with the gap control member. | 02-07-2013 |
20130034424 | TIP CLEARANCE CONTROL DEVICE - A tip clearance control device adapted to control the clearance of a rotating aerofoil structure with a surrounding casing portion, and a method of controlling the tip clearance of a rotating aerofoil structure with a surrounding casing portion. The device includes a member operatively connected to the casing portion; the member having at least a first configuration in which the casing portion is at a first radial position and a second configuration in which the casing portion is at a second radial position, wherein the configuration of the member is controlled by magnetic flux in a magnetic circuit which includes at least one ferromagnetic element including ferromagnetic material, where the configuration of the member is responsive to the temperature of the ferromagnetic element. | 02-07-2013 |
20130034425 | METHOD FOR ADAPTING THE AIR FLOW OF A TURBINE ENGINE HAVING A CENTRIFUGAL COMPRESSOR AND DIFFUSER FOR IMPLEMENTING SAME - A method for maintaining efficiency and duty of a turbine engine compressor to reduce specific consumption, while guaranteeing a high enough pumping margin with partial load. The method adapts airflow to a variable demand for flow or mechanical or electric power in a centrifugal compressor of a turbine engine. The method includes diffusing the airflow through a first annular blade ring having variable pitch blades, radially bordered by a second annular blade ring having a same number of fixed pitch blades with an equivalent extension, guiding the radial extension diffusion by coupling the blades of the two blade rings. According to the method, each blade of the first blade ring is spun off-axis. | 02-07-2013 |
20130039735 | VARIABLE VANE ACTUATION SYSTEM AND METHOD - A variable vane actuation system and method is disclosed herein. The variable vane actuation system includes a first ring member disposed for pivoting movement about a centerline axis. The first ring member is operably connected with at least one vane such that the at least one vane pivots in response to the pivoting movement of the first ring member. The variable vane actuation system also includes a first pin engaged with the first ring member. The variable vane actuation system also includes a ring moving device operably engaged with the first pin to move the first ring member about the centerline axis. The ring moving device includes at least one plate having a first slot and an actuator operable to move the at least one plate. The first pin is received in the first slot and is a cam follower to a cam defined at least in part by a surface of the first slot. | 02-14-2013 |
20130039736 | Variable Stator Vane Control System - The present application provides a variable stator vane control system. The variable stator vane control system may include a variable stator vane positioned by an actuator and a trimmer motor, a resolver to determine a position of the variable stator vane, and a controller in communication with the resolver, the actuator, and the trimmer motor to prevent over travel of the variable stator vane. | 02-14-2013 |
20130039737 | METHOD FOR CONTROLLING A COMPRESSOR - A method for controlling a compressor that includes a compressor element, whereby during a transition from full load or partial load to zero load, a process A is followed that involves: (1) reducing the inlet pressure; and (2) reducing the speed and/or the drive torque. During a transition from zero load to part load or full load, a process B is followed that involves: (3) increasing of the speed or drive; and (4) increasing the inlet pressure. | 02-14-2013 |
20130045076 | COMPRESSOR CONTROL METHOD AND SYSTEM - A compressor control method includes providing variable aerodynamic sizing of fluid flow through a compressor at multiple operating points of the compressor. A head is determined for an operating point, based on a process input at that operating point. Further, for that operating point, a control pressure number is determined as a function aerodynamic flow sizing at that operating point. The control pressure number is determined a function of the head divided by the square of a tip speed of the impeller of the compressor. An operating speed setpoint is determined based on the determined head and control pressure number. | 02-21-2013 |
20130045077 | PNEUMATIC COMPOSITE HAVING MASS BALANCING - The invention relates to a blower device for delivering at least one medium, comprising a blower having a housing with an inlet and an outlet, a nozzle, which is fluidically connected and arranged on the housing such that at least one medium can flow there through, wherein the nozzle is designed to effect a negative pressure on the at least one medium at least in some sections, at least one sensor, wherein the sensor is arranged in the effective region of the nozzle and designed to measure at least parameters of the at least one medium which are required to determine the mass of the at least one medium. | 02-21-2013 |
20130045078 | BEARING ASSEMBLY FOR A VERTICAL TURBINE PUMP - A bearing assembly for supporting a drive shaft of a pump is structured with a cylindrical body having an internal cavity filled with a lubricant, a sealing element arrangement positioned at one or both ends of the cylindrical body and a pressure equalization element that functions to equalize the pressure differential that exists between an area within the cylindrical body and outside of the cylindrical body to improve the operating life of the sealing arrangement and the bearing assembly. | 02-21-2013 |
20130051972 | BLADE OUTER AIR SEAL WITH MULTI IMPINGEMENT PLATE ASSEMBLY - A multi impingement plate assembly for a Blade Outer Air Seal (BOAS) includes a first impingement plate which defines a multiple of first impingement plate holes and a second impingement plate attached to the first impingement plate. The second impingement plate includes a platform section spaced away from the multiple of first impingement plate holes to define a plate cavity. | 02-28-2013 |
20130051973 | COMPRESSOR DIFFUSER PLATE - A diffuser plate for a centrifugal compressor includes an inner edge disposed at an inner diameter about a central axis; an outer edge disposed at an outer diameter, the outer edge displaced an axial distance from the inner edge; a deformable section that includes a substantially S-shaped cross-section, the deformable section disposed between the inner edge and the outer edge; and a spring constant for forced axial displacement of the outer edge with respect to the inner edge, the spring constant characterized, at least in part, by the deformable section. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 02-28-2013 |
20130051974 | GAS TURBINE ENGINES AND METHODS FOR COOLING COMPONENTS THEREOF WITH MID-IMPELLER BLEED COOLING AIR - Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction. | 02-28-2013 |
20130051975 | AIR TURBINE STARTER AND METHOD FOR VENTING WITHOUT LOSS OF OIL - A clutch assembly includes a shaft, vent plug and oil guide sleeve. The shaft includes an internal cavity, first passages for allowing oil to lubricate clutch components, and second passages for allowing excess oil to drain from the internal cavity. The vent plug has a radial passage in communication with the internal cavity for venting the cavity with an external source of air. The oil guide sleeve directs oil into the internal cavity. A method for lubricating and venting an air turbine starter includes delivering lubricating oil to an internal cavity of a clutch via an oil guide sleeve. The oil guide sleeve prevents oil from exiting the cavity through excess oil drainage passages before it lubricates the clutch components. The method also includes draining excess oil from the cavity through excess oil drainage passages so that excess oil does not substantially impede air flow through a vent plug passage. | 02-28-2013 |
20130051976 | FLOW CONTROL MODULE FOR A TURBOMACHINE - A flow control module for a turbomachine includes an inlet extending to an outlet through a flow passage having at least one side wall. A flow control member is arranged within the flow control module. The flow control member is secured to the at least one side wall between the inlet and the outlet. The flow control member is selectively passively activated to extend into the flow passage to block cooling fluid passing through the flow control module. | 02-28-2013 |
20130051977 | ADJUSTABLE VANE DIFFUSER INSERT FOR ELECTRICAL SUBMERSIBLE PUMP - A pump having an insert between an impeller and diffuser, where the insert includes an annulus that is in communication with fluid flow passages in the impeller and diffuser. The passages and annulus define a fluid flow path through the pump. Vanes are provided in the annulus that can pivot and vary the cross sectional area of the fluid flow path. Regulating the fluid flow path area alters the flow rate where the pump operates at its maximum efficiency. Thus by monitoring flow through the pump, the vanes can be adjusted so the flow rate of maximum efficiency corresponds to the actual flow rate. | 02-28-2013 |
20130058756 | FLOW DISCOURAGER INTEGRATED TURBINE INTER-STAGE U-RING - A gas turbine having rotor discs ( | 03-07-2013 |
20130058757 | PRIMING VALVE SYSTEM FOR PRE-PRIMING CENTRIFUGAL PUMP INTAKES - A priming valve for priming a centrifugal pump includes a valve assembly separating an inlet chamber from an outlet chamber. The inlet chamber is fluidly coupled to an intake for the centrifugal pump and the outlet chamber is fluidly coupled to a priming pump. A control valve is provided to operate the valve assembly in order to fluidly connect the inlet chamber with the outlet chamber. While the valve assembly fluidly connects the inlet chamber with the outlet chamber, the priming pump can operate to replace air in the intake and the centrifugal pump with water. | 03-07-2013 |
20130064638 | Boundary Layer Blowing Using Steam Seal Leakage Flow - A steam turbine includes a final turbine stage, a flow diffuser receiving a main flow from the final turbine stage, a diverging wall in the axial or radial flow diffuser that extends from a diffuser inlet to a diffuser exit, and a centerbody in the axial or radial flow diffuser. An opening is provided in the diverging wall and an opening is provided in the centerbody for fluidically actuating the main flow. The openings are located downstream from the diffuser inlet and upstream from a point where boundary layer separation would occur along the walls in a diffuser without the openings. A plurality of openings are provided in the diverging wall, and an end packing seal is positioned adjacent an end portion of the final turbine stage. An annular manifold collects fluid from leakage flow from the end packing seal and distributes the leakage flow to the openings. | 03-14-2013 |
20130064639 | GAS TURBINE ENGINES WITH IMPROVED TRAILING EDGE COOLING ARRANGEMENTS - An airfoil is provided for a gas turbine engine. The airfoil includes a pressure side wall; a suction side wall; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity. The cooling arrangement includes a first land extending to a first downstream end aft of the pressure side trailing edge, a second land extending to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot, a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, a first pin positioned upstream and indexed to the first passageway, and a second pin positioned upstream and indexed to the second passageway. | 03-14-2013 |
20130064640 | PERFORATED HYDROCRATIC GENERATOR - A hydrocratic device comprises an inner pipe defining a mixing area, an outer pipe, and an annular chamber between the inner and outer pipes. A feed inlet supplies the annular chamber, and a plurality of perforations are formed in the wall of the inner pipe. | 03-14-2013 |
20130064641 | Air Ducting Shroud For Cooling An Air Compressor Pump And Motor - A compressor assembly having an air ducting shroud that can direct a cooling air stream from a fan to components of the compressor assembly, such as a pump assembly. The pump assembly can have at least a pump, a motor and a fan. The compressor can be cooled by providing cooling air to a cylinder head of the pump without the cooling air experiencing choking or substantial cooling flow interference from a cooling of the motor. | 03-14-2013 |
20130064642 | Tank Dampening Device - A compressor assembly having a compressed gas tank having a tank dampening device in the form of a vibration absorption member. The vibration absorption member can provide a pressure to a portion of the compressed gas tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which exerts a force upon the compressed gas tank. A means for controlling the sound level of a compressed gas tank by using a means for absorbing vibration from the compressed gas tank which exerts a pressure on a portion of the compressed gas tank. | 03-14-2013 |
20130064643 | Tank Dampening Device - A compressor assembly that has a compressed air tank having a vibration absorption member. The vibration absorption member can exert a pressure on a portion of the compressed air tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which applies a force against the compressed gas tank. Controlling the sound level of the compressed gas tank is accomplished by absorbing vibration from the compressed gas tank by which exerting a pressure on a portion of the compressed gas tank. | 03-14-2013 |
20130064644 | VARIABLE PARTIAL WIND WALL - A wind power system including a wind turbine affixed to a support tower, and a wind deflector deployable relative to a direction of air flow and configured to control the movement of at least a portion of air flow passing through rotor blades of the wind turbine to reduce wind loads on the components of the wind turbine while maintaining the air flow in an operating power production range. | 03-14-2013 |
20130071226 | METHODS AND SYSTEMS FOR USE IN CHECKING THE POLARITY OF MULTI-COIL SERVOS - A method and system for configuring a valve in a turbine. The method includes transmitting a first signal from a servo to a first coil of an actuator to cause the valve to move to a first position, determining a first magnitude of the valve, and transmitting a second signal from the servo to a second coil of the actuator to cause the valve to move to second position. The method also includes determining a second magnitude of the valve, and comparing the first magnitude to the second magnitude to determine the polarity of wiring coupled between the servo and the actuator. | 03-21-2013 |
20130071227 | BLADE OUTER AIR SEAL ASSEMBLY LEADING EDGE CORE CONFIGURATION - An example blade outer air seal assembly may consist of a blade outer air seal containing channels that communicate cooling air through at least some of the blade outer air seal. The blade outer air seal has at least one circumferentially extending barrier separating the leading channel into a forward portion and an aft portion. Cooling air outlets from the leading channel are exclusively coupled to the aft portion. | 03-21-2013 |
20130071228 | STATIONARY CO-AXIAL MULTI-ROTOR WIND TURBINE SUPPORTED BY CONTINUOUS CENTRAL DRIVESHAFT - Co-axial, multi-rotor wind turbines, producing more power than a single rotor of the same diameter, are made even more powerful by increasing driveshaft length and supporting the driveshaft from more than one point. Sacrificing the ability to aim, for the extra length to support additional rotors, results in a more powerful co-axial multi-rotor turbine, especially useful for areas with a predominantly unidirectional wind resource. Ideally the turbine is placed at an offset angle α (alpha) from the wind direction, which, in combination with proper spacing between rotors, allows fresh wind to reach each rotor, so that all rotors contribute toward rotation of the driveshaft. Placing the driveshaft under tension can raise critical speeds and reduce the number of intermediate supports required. This places the Earth or underlying substrate in compression, making it effectively part of the structure of the turbine, saving cost. Cross-axis and reversible blades may also be incorporated. | 03-21-2013 |
20130084160 | Turbine Shroud Impingement System with Bellows - The present application provides a turbine shroud impingement system. The turbine shroud impingement system may include a turbine shroud segment, an impingement box positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows positioned about the feed tube. | 04-04-2013 |
20130089406 | TURBINE OUTLET FROZEN GAS CAPTURE APPARATUS AND METHOD - A turbine outlet frozen gas capture apparatus is provided and includes an enclosure divided into first and second chambers, the first chamber being receptive of turbine outlet exhaust including frozen gas, a wheel disposed and configured to be rotatable such that frozen gas received in the first chamber is captured and transported into the second chamber and a heater disposed within the second chamber and configured to vaporize the frozen gas transported therein to thereby produce vaporized gas. | 04-11-2013 |
20130089407 | EXTERNALLY THREADED JOURNAL HOUSING - A journal housing including a series of housing threads defined on an outer radial surface. The series of housing threads may be adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing. A shoulder may extend radially-outward from the outer radial surface, and the shoulder may be disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener. | 04-11-2013 |
20130094937 | GAS TURBINE ENGINE OIL BUFFERING - A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment. | 04-18-2013 |
20130094938 | TURBOMACHINE - A turbomachine comprising a housing defining a bearing cavity and a turbine chamber separated by a first wall, a heat shield disposed between the first wall and the turbine wheel, a heat shield cavity defined between the first wall and the heat shield. The shaft extends through a passage defined in part by a first aperture in the wall and a second aperture in the heat shield. A first seal is provided between the shaft and the first aperture. The housing defines a first gas channel communicating with the heat shield cavity for connection to a pressure source for raising pressure within the heat shield cavity. A second channel is provided between the heat shield cavity and the passage, the second channel opening to the passage on the opposite side of the first seal to the bearing assembly. A second seal is provided between the shaft and the second aperture. | 04-18-2013 |
20130101385 | VARIABLE VANE ASSEMBLY FOR A GAS TURBINE ENGINE HAVING AN INCREMENTALLY ROTATABLE BUSHING - A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions. | 04-25-2013 |
20130101386 | DUAL-FLOW STEAM TURBINE WITH STEAM COOLING - A dual flow steam turbine includes coolant passageways which extract coolant steam from the main steam flow paths at locations downstream from the inlet. The coolant passageways conduct the coolant steam through portions of the dual flow steam turbine which are subjected to a high temperature flow. In some cases, the passageways conduct the coolant steam through first stage nozzle boxes and an inlet assembly of the dual flow steam turbine. In some cases, the inlet assembly of the steam turbine includes an annular diaphragm, and a coolant passageway passes through the annular diaphragm to help cool the annular diaphragm. | 04-25-2013 |
20130101387 | SYSTEM AND METHOD FOR INTEGRATING SECTIONS OF A TURBINE - A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average. | 04-25-2013 |
20130101388 | COMPRESSION DEVICE AND METHOD FOR COOLING A COMPRESSION MEDIUM - The invention concerns a compression device fitted with a drive unit;
| 04-25-2013 |
20130101389 | HEAT-DISSIPATING SYSTEM AND CONTROL METHOD THEREOF - The invention provides a heat-dissipating system and a control method thereof. The heat-dissipating system has a plurality of fans and is configured for adjusting rotation-speeds of the fans. The control method includes following steps: obtaining a plurality of rotation-speed values of the fans; computing out a rotation-speed reference value according to the rotation-speed values; when the rotation-speed reference value is greater than a first threshold value, decreasing the rotation-speeds of the fans through a corresponding fan control signal; when the rotation-speed reference value is less than a second threshold value, increasing the rotation-speeds of the fans through the corresponding fan control signal. | 04-25-2013 |
20130101390 | METHOD FOR CONTROLLING A COMPRESSOR ELEMENT OF A SCREW COMPRESSOR - Method for controlling a compressor element of a screw compressor, where the compressor element has a housing with two meshing helical rotors supported in the housing in the axial direction using at least one axial bearing. The method has a process A and/or a process B, where process A has a first step of switching on a first magnet during start-up of the compressor element, such that the magnet exerts a force on the rotor that is directed from an outlet side to an inlet side, and of switching off this first magnet during nominal operation of the compressor element; and where process B has a first step of keeping a second magnet switched off during start-up of the compressor element, and switching on this second magnet during nominal operation of the compressor element, such that this second magnet exerts a force that is directed from the inlet side to the outlet side. | 04-25-2013 |
20130108411 | CUTTER ASSEMBLY AND HIGH VOLUME SUBMERSIBLE SHREDDER PUMP | 05-02-2013 |
20130115042 | DYNAMIC THRUST BALANCING FOR CENTRIFUGAL COMPRESSORS - Systems and methods for dynamically balancing axial loads in centrifugal compressors to reduce residual axial loads on the bearings used therein are described. A sensor or probe detects a parameter associated with the axial load acting on the bearing. Based on the detected parameter, the pressure in a balance chamber is controlled to adjust the compensating axial force generated by a balance drum. | 05-09-2013 |
20130115043 | ROTATIONAL POSITIONING SYSTEM IN A WIND TURBINE - A rotational positioning system in a wind turbine is provided that comprises a driven part (101), a plurality of positioning drives (102) coupled to the driven part (101), a plurality of sensors (111) each arranged to sense a load parameter indicative of the load of the respective positioning drive (102), and a load controller (112, 113, 114, 115) connected to the plurality of sensors (111). The load controller (112, 113, 114, 115) is arranged to determine a load of a respective positioning drive (102) based on the sensed load parameter, to compare said load with an expected load value, and to output a signal (115) indicative of a failure of the respective positioning drive (102) in response to the load being smaller than the expected load value. | 05-09-2013 |
20130115044 | EXHAUST GAS DIFFUSER FOR A GAS TURBINE AND A METHOD FOR OPERATING A GAS TURBINE THAT COMPRISES SUCH AN EXHAUST GAS DIFFUSER - An exhaust gas diffuser for a gas turbine is provided. The diffuser has an annular outer wall for guiding the diffuser flow and in which an annular guiding element is arranged concentrically to the outer wall and influences the diffuser flow. The guiding element has a surface which is radially directed inwards and has a circumferential contour that is convex in the longitudinal section to form a displacement element. The guiding element is axially displaceable between two positions so that the guiding element, when in a first position, allows a flow between the guiding element and outer wall and, when in a second position, largely prohibits a flow between the guiding element and outer wall. The aerodynamic effect of the diffuser is improved and simultaneously optimal adapted for a plurality of operational gas turbine states. | 05-09-2013 |
20130121803 | COMPRESSOR HAVING PURGE CIRCUIT AND METHOD OF PURGING - A compressor having a purge circuit. In one embodiment, the compressor includes: a rotor having a plurality of stages, each of the plurality of stages including a set of radially extending rotor wheels; a working fluid supply path for providing working fluid to each of the plurality of stages for compression by each set of radially extending rotor wheels; a purge circuit for diverting a first portion of the working fluid from an upstream portion of the working fluid supply path to at least one downstream stage of the plurality of stages; and a substantially axial bypass path bypassing the at least one downstream stage, the substantially axial bypass path for diverting a second portion of the working fluid around the at least one downstream stage. | 05-16-2013 |
20130121804 | Fluid Movement System and Method for Determining Impeller Blade Angles for Use Therewith - A fluid movement system that includes an impeller having a blade with a leading edge blade tip angle determined as a function of an increase in mass flow rate due to reinjection of flow from a flow stability device located proximate to the leading edge tip of the blade. In an exemplary method, the leading edge blade tip angle can be determined based on selecting a blade incidence level based on a mass flow gain versus flow coefficient curve. Blade leading edge tip angles determined in accordance with a method of the present invention are typically greater than blade leading edge tip angles determined using traditional methods. The greater blade leading edge tip angles can lead to more robust blades designs. | 05-16-2013 |
20130121805 | HYDRAULIC POWER SPLIT ENGINE WITH ENHANCED TORQUE ASSIST - A power split transmission includes a rotatable input shaft, a rotatable output shaft, and a planetary gear assembly connected between the input shaft and the output shaft. The transmission also includes a first hydraulic unit operable as a pump or a motor, the first hydraulic unit being coupled to the output shaft via the planetary gear assembly; a second hydraulic unit operable as a pump or a motor, the second hydraulic unit being coupled to the output shaft independently of the planetary gear assembly; and a braking mechanism coupled to the input shaft that is selectively engageable to retard rotation of the input shaft in at least one direction. The braking mechanism enables the power split transmission to use both the first hydraulic unit and the second hydraulic unit to provide enhanced torque at the output shaft without damaging a prime mover coupled to the input shaft. | 05-16-2013 |
20130121806 | EXHAUST DIFFUSER FOR A GAS TURBINE, AND METHOD THEREOF - An exhaust diffuser assembly is provided, particularly for a stationary gas turbine. The exhaust diffuser assembly includes a longitudinal axis, a diffuser inlet for receiving a turbine mainflow gas, a diffuser outlet, and a diverging diffuser wall having an adjustable geometry and forming a conduit for flow of the gas therethrough from the diffuser inlet to the diffuser outlet. The diffuser wall has a divergence angle ‘α’ with respect to the longitudinal axis. The diffuser assembly also has a diffuser geometry control device for controlling a recovery of pressure from the gas between the diffuser inlet and the diffuser outlet by adjusting the divergence angle ‘α’ of the diffuser wall to cause a resultant flow field of the gas that is attached to the diffuser wall. | 05-16-2013 |
20130129470 | Systems and Methods for Adjusting Clearances in Turbines - Embodiments of the invention can provide systems and methods for adjusting clearances in a turbine. According to one embodiment of the invention, there is disclosed a turbine system. The system may include one or more turbine blades; a turbine casing encompassing the one or more turbine blades; and a thermoelectric element disposed at least partially about the turbine casing, wherein the thermoelectric element expands or contracts the turbine casing by heating or cooling at least a portion of the turbine casing, thereby adjusting a clearance between the one or more turbine blades and the turbine casing. | 05-23-2013 |
20130129471 | Method and System for Reducing Seal Gas Consumption and Settle-Out Pressure Reduction in High-Pressure Compression Systems - A compressor is disclosed having a shaft seal assembly and system that allows a high-pressure compressor to settle-out at a lower pressure level during shutdown. The seal assembly may be disposed about a portion of the shaft and define a blow-down seal chamber, the seal assembly including one or more gas seals in fluid communication with the blow-down seal chamber. A blow-down line is communicably coupled to the blow-down seal chamber to reference the blow-down seal chamber to a low pressure reference, such as a separate centrifugal compressor, or the like. Referencing the blow-down seal chamber to the low pressure reference reduces the required sealing pressure of the one or more gas seals. A valve may be disposed in the blow-down line and configured to regulate a flow of process gas leakage through the blow-down line. | 05-23-2013 |
20130129472 | WIND TURBINE - Wind turbine systems and methods are provided. The wind turbine system includes a plurality of coaxial, counter-rotating turbine assemblies. First and second shroud assemblies define a generally spherical volume containing the first and second turbine assemblies. The first and second shroud assemblies each include a shroud member that can selectively shield or expose portions of the respective turbine assemblies to the wind by changing the rotational position of the shroud members about the system axis. The turbine assemblies are interconnected to a generator for the production of electrical power. | 05-23-2013 |
20130129473 | AVOIDANCE OF TORSIONAL EXCITATIONS IN CONVERTER-CONTROLLED COMPRESSOR RUNS - A machine has a rotor and includes a converter-controlled drive and a working machine, wherein the drive and the working machine are connected such that a torque is transmitted. A frequency converter is electrically connected to the drive. The frequency converter is embodied such that in a Campbell diagram intersection points are based on the natural torsional frequency of the rotor and V-shaped symmetrical straight lines of the inter-harmonic exciter frequency for output frequencies. The output frequencies are grouped into a plurality of concentration ranges based upon a rotational speed of the machine, wherein each concentration range comprises output frequencies which are close to one another and which respectively have a common output point on the abscissa of the Campbell diagram. Each concentration range defines a blocking range, wherein the machine has an operating rotational speed range which lies outside the blocking ranges. | 05-23-2013 |
20130129474 | WIND POWER PLANT FOUNDATION AND WIND POWER PLANT - There is provided a wind power installation foundation having a reinforcement comprising a plurality of steel bars and radial steel bars and a lower pylon segment having a plurality of holes in the wall of the pylon segment for receiving the bars or radial bars. In addition there is provided a concrete body which covers the reinforcement and the lower portion of the pylon segment. The foundation has a plurality of holders for holding the bars or radial bars of the reinforcement. The holder has an upper bracket for fixing to the pylon segment and a lower foot for receiving the bars or radial bars of the reinforcement. The length of the holder is adapted to be variable. | 05-23-2013 |
20130129475 | Method for operating a pump - A method for operating a switchable pump, which is situated in a motor vehicle and configured to provide a setpoint pressure for a medium, the pump being activated in trailing-throttle operation of the motor vehicle. | 05-23-2013 |
20130129476 | ROTARY MACHINE FOR COMPRESSION AND DECOMPRESSION - A rotary machine for compression and decompression, comprising a disc-shaped rotor having a first rotation axis at right angles to the plane of the rotor and situated in a plane of orientation and a disc-shaped swing element having a second rotation axis. In the orientation plane, the second rotation axis makes an angle with the first rotation axis. Furthermore, a spherical housing is present surrounding the rotor and the swing element and in combination forming four (de-)compression chambers. A connecting body positions the rotor and the swing element in the housing. The rotary machine furthermore comprises a power drive and a mechanical connection delivering power to or taking off power from the rotary machine. In addition, the rotary machine is suitable for the seamless integration of generator components for generating or using electricity. | 05-23-2013 |
20130129477 | METHOD FOR OPERATING A COMPRESSOR - A method for operating a compressor including providing suction pressure measurement, final pressure measurement, throughput measurement is provided. Using a first control characteristic map a target value for a pump surge limiter is determined from one or two of the measurements, and the pump surge limiter compares the target value to the throughput measurement, wherein the pump surge limiter opens a bypass valve when the measured value falls below or exceeds the target value, such that the final pressure is lowered or the flow through the compressor is increased. In the event of failure of a measurement, a further measurement of another physical variable of the compression process, together with a measured variable that did not fail or a modification of the measured variable, is an input variable for a substitute control characteristic map, form which a substitute target value is determined. | 05-23-2013 |
20130136574 | INTAKE ASSEMBLIES FOR WIND-ENERGY CONVERSION SYSTEMS AND METHODS - An intake assembly for a wind-energy conversion system has a substantially vertical converging nozzle, an object extending into the nozzle, and a converging flow passage between the object and the nozzle. For some embodiments, the object may be another nozzle. There may be vanes in one or both nozzles in further embodiments. The object may be configured to move in yet other embodiments. | 05-30-2013 |
20130136575 | METHOD FOR MONITORING THE CLEARANCE OF A KINEMATIC LINK BETWEEN A CONTROL MEMBER AND A RECEIVING MEMBER - The method consists, based on an operating parameter of the turbojet engine, in: | 05-30-2013 |
20130136576 | WIND TURBINE AIR FLOW GUIDE DEVICE - The invention extends to an air flow device for wind turbines which includes a number of flow paths which assist in the movement of air through the air flow device which assists in increasing the efficiency and power output of the wind turbine. The air flow device includes flow passages alongside a central channel which houses the wind turbine. | 05-30-2013 |
20130142615 | Blower Housing - A blower housing has a discharge direction, an axis of rotation, a polar axis that intersects the axis of rotation and is substantially perpendicular to the discharge direction, an angular sweep of increasing fluid flow area, and an axial contraction located at an angularly greater value than the angular sweep. | 06-06-2013 |
20130142616 | Pumping Device - A pump is disclosed, with a casing comprising a substantially circular body having at least two radial inlets, at least one peripheral outlet and a transversal aperture. The casing further comprises a substantially circular impeller mounted within the body for rotation about the aperture. The impeller has a substantially uninterrupted sinusoidal profile. A pumping system and a method of pumping are also disclosed, which use the pump configuration. | 06-06-2013 |
20130142617 | METHOD AND EQUIPMENT FOR DETECTING ROTATING STALL AND COMPRESSOR - A method for detecting rotating stall in a compressor is disclosed herein. The method comprises measuring radial vibration of the rotor relative to the stator and generating a vibration measurement signal, calculating a frequency spectrum of the vibration measurement signal, identifying a plurality of frequency bandwidths of the frequency spectrum, neglecting one first frequency bandwidth of the plurality of frequency bandwidths if the rotation frequency of the rotor falls within the first frequency bandwidth, neglecting at least one second frequency bandwidth of the plurality of frequency bandwidths if the rotation frequency of the rotor falls below the second frequency bandwidth, determining the maximum magnitude of the spectrum in each of the non-neglected frequency bandwidths, and comparing each determined maximum magnitude and a predetermined value. Rotating stall is considered occurring if at least one of the comparisons shows that the corresponding determined maximum magnitude is greater than the predetermined value. | 06-06-2013 |
20130142618 | STEAM TURBINE ARRANGEMENT OF A THREE CASING SUPERCRITICAL STEAM TURBINE - A steam turbine arrangement is provided and includes a first steam turbine with a first steam outlet, wherein the first steam turbine exhibiting a first sealing leakage, a second steam turbine exhibiting a second sealing leakage, and a third steam turbine with a cooling steam inlet, a functional device and a cooling arrangement. The cooling arrangement is coupled to the cooling steam inlet. The cooling arrangement is adapted for guiding a cooling steam to the functional device for cooling purposes. A steam pipe is coupled to the first steam turbine and to the second steam turbine such that a first steam being provided by the first sealing leakage and a second steam being provided by the second sealing leakage is gathered to a cooling steam in the steam pipe. The steam pipe is coupled to the cooling steam inlet such that the cooling steam is injectable to the cooling arrangement. | 06-06-2013 |
20130149098 | FAN BLADE TIP CLEARANCE CONTROL VIA Z-BANDS - An engine has a blade, a casing surrounding the blade, an seal ring, and a passive system for connecting the seal ring to the casing and for accommodating thermal expansion of the seal ring relative to the casing so as to maintain blade tip clearance control. The passive system may include at least one, metallic Z-band extending between the casing and the seal ring. | 06-13-2013 |
20130149099 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE TO REDUCE FAN INSTABILITY - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area to reduce a fan instability. | 06-13-2013 |
20130149100 | GAS TURBINE ENGINE - A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided. | 06-13-2013 |
20130149101 | REDUCED LEAKAGE BALANCE PISTON SEAL - Balance piston assembly, apparatus, and methods are provided. The assembly includes a balance piston coupled to a rotatable shaft and configured to rotate therewith, the balance piston including a first shelf and a second shelf, the first and second shelves being axially-overlapping and radially-offset. The assembly also includes a seal including a first sealing surface configured to seal with the first shelf and a second sealing surface configured to seal with the second shelf. | 06-13-2013 |
20130149102 | TURNING GEAR FOR GAS TURBINE ARRANGEMENTS - An apparatus for driving a load is provided. The apparatus comprises a multiple-shaft gas turbine comprising a high pressure compressor and a high pressure turbine drivingly connected to one another by a first gas turbine shaft and a low pressure compressor and a power turbine drivingly connected to one another by a second gas turbine shaft extending coaxial with the first gas turbine shaft, the high pressure compressor and the high pressure turbine. The apparatus also comprises a load coupling drivingly connecting the power turbine to the load and a dual-speed turning gear with an output shaft drivingly engageable to and disengageable from the load, the dual-speed turning gear comprising a low speed turning motor and a high speed turning motor, wherein the low speed turning motor and the high speed turning motor are configured to selectively drive the load. | 06-13-2013 |
20130156540 | STEAM SEAL HEADER, METHOD OF USING A STEAM SEAL HEADER AND STEAM TURBINE SYSTEM INCORPORATING A STEAM SEAL HEADER - A steam turbine system for use in a power plant includes a steam seal header that collects steam from seals of a high pressure steam turbine and an intermediate pressure steam turbine. The collected steam is provided to seals of a low pressure steam turbine to ensure the seals provide an effective seal for the low pressure steam turbine. Steam from the low pressure steam turbine is also collected in the steam seal header and it is mixed with the steam collected from the high and intermediate pressure seals. The mixed steam is then provided to drive the low pressure steam turbine. | 06-20-2013 |
20130156541 | ACTIVE TURBINE TIP CLEARANCE CONTROL SYSTEM - An active tip clearance control (ATCC) system of a gas turbine engine includes an ejector to selectively drive an air flow passing through the ATCC system. A high pressure air flow as a motive flow of the ejector is controlled by a valve according to engine operation requirements. | 06-20-2013 |
20130156542 | ENERGY-ABSORBING FAN CASE FOR A GAS TURBINE ENGINE - A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis and a plurality of helical ribs adjacent to the fan blade containment section. | 06-20-2013 |
20130156543 | SINGLE SYSTEM WITH INTEGRATED COMPRESSOR AND PUMP AND METHOD - Method and system for compressing a fluid in a gas phase and for pumping the fluid in a dense phase. The system includes a compressor part having an impeller; a compressor part inlet that receives the fluid in the gas phase; a compressor part outlet that provides the fluid in the gas phase; a temperature changing device that changes a phase of the fluid; a pump part having an impeller; a pump part inlet that receives the fluid in the dense phase from the compressor part outlet; a pump part outlet that outputs the fluid in the dense phase from the system; a single bull gear configured to rotate around an axial axis with a predetermined speed; plural pinions contacting the single gear bull and configured to rotate with predetermined speeds, and a pump shaft configured to rotate the at least one impeller of the pump part. | 06-20-2013 |
20130156544 | Compressor Surge Detection - A compressor ( | 06-20-2013 |
20130164114 | ADJUSTABLE CORE TURBOCHARGER - A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands. | 06-27-2013 |
20130164115 | BLEED AIR AND HOT SECTION COMPONENT COOLING AIR SYSTEM AND METHOD - Combined bleed air and hot section component cooling air systems for gas turbine engines and methods of operating combined bleed air and hot section component cooling air systems are disclosed. An example system may include a high-pressure bleed air line receiving high-pressure bleed air; a precooler receiving at least some of the high-pressure bleed air and discharging cooled high-pressure bleed air; a pressure regulator receiving at least some of the cooled high-pressure bleed air and discharging pressure-regulated cooled bleed air to a pneumatic systems supply line; and/or a hot section component cooling air line connected upstream of the first pressure regulator and configured to convey at least some of the cooled high-pressure bleed air to a hot section component for use as hot section component cooling air. | 06-27-2013 |
20130170942 | Multiple Fan Blade Angles in a Single Crossflow Fan - A fan may be provided. The fan may comprise a first plurality of vanes and a second plurality of vanes. The first plurality of vanes may be arranged substantially parallel to an axis of rotation and positioned along a first arc substantially centered on the axis of rotation. Vanes in the first plurality of vanes may be being positioned at a first angle relative to the first arc. The second plurality of vanes may be arranged substantially parallel to the axis of rotation and positioned along a second arc substantially centered on the axis of rotation. Vanes in the second plurality of vanes may be positioned at a second angle relative to the second arc. The first angle may be different than the second angle. | 07-04-2013 |
20130170943 | HYBRID BEARING TURBOMACHINE - A turbomachine includes a housing and a rotatable shaft, where at least a portion of the rotatable shaft is located in the housing. The turbomachine also includes a magnetic thrust bearing that axially positions the rotatable shaft and a radial bearing that centers the rotatable shaft. The turbomachine includes a flexure including a first portion secured to the housing and a second portion axially moveable relative to the first portion. The second portion of the flexure is connected to the radial bearing, and the second portion moves axially to eliminate thrust loads on the radial bearing and allow the magnetic thrust bearing to carry axial loads. | 07-04-2013 |
20130170944 | TURBINE ASSEMBLY AND METHOD FOR REDUCING FLUID FLOW BETWEEN TURBINE COMPONENTS - According to one aspect of the invention, a turbine assembly includes a first bucket with a first slashface and a second bucket including a recess formed in a second slashface of the second bucket, wherein the second slashface is adjacent to the first slashface when the first bucket is positioned adjacent to the second bucket. The turbine assembly also includes a pin configured to be placed in the recess, wherein the pin is magnetically urged toward the first slashface to reduce fluid flow between the first and second buckets. | 07-04-2013 |
20130170945 | FURNACE AIR HANDLER BLOWER WITH ENLARGED BACKWARD CURVED IMPELLER AND ASSOCIATED METHOD OF USE - A blower having a blower housing having a cutoff and a top portion with an air outlet opening, a fan within the blower housing, the fan being adapted for rotation about a fan axis and having an outer diameter with a distance between the outer diameter of the fan and the top portion of the air outlet opening extending along a vertical line between the fan axis and the air outlet opening being less than seventy-five percent of the distance between the outer diameter of the fan and the cutoff of the blower housing extending along a line between the fan axis and the cutoff, and a motor having a stator and a rotor, the rotor being rotatably coupled to the stator for rotation about the fan axis, the rotor and fan being coupled such that the fan rotates with the rotor. | 07-04-2013 |
20130170946 | RISERLESS TRANSFER PUMP AND MIXER/PRE-MELTER FOR MOLTEN METAL APPLICATIONS - A pump for processing molten metal having an enlarged tubular body which houses a centrifugal pump at its bottom end. The bottom end has a concave curved shape whose shape is a function of the particular type of vortex to be created for the application at hand. This curved portion of the body receives the ejected molten metal from the impeller and forms an uplifting axial vortex within the tubular section of the body. The pump is designed to cooperate synergistically with said body such that the uplifting axial vortex to climb up the inner wall of the body up to and out of an outlet formed in the upper end of the body. A radial vane impeller is formed in the back plate of the impeller. When the impeller is rotated, solid particles introduced into the body are accelerated radially by the back plate impeller into the vortex. | 07-04-2013 |
20130170947 | ROTOR BEHAVIOUR DETERMINATION - A method of resolving vibration behaviour of a rotor assembly having a plurality of rotor blades. The method including generating a computational model of the rotor by discretization of the rotor geometry and assigning parameter values representative of a plurality of physical characteristics of the rotor. An artificial parameter feature is applied to each rotor blade such that the parameter values for the artificial parameter feature substantially depart from the physical characteristics of the rotor. A vibration response is calculated for the rotor or blade thereof for the applied artificial parameter features and compared to a predetermined vibration response so as to determine a value of the artificial parameter feature which results in a calculated vibration response that substantially matches the predetermined vibration response. | 07-04-2013 |
20130170948 | TURBOCHARGER BYPASS SYSTEM - A turbocharger bypass system and method for minimizing the occurrence of oil seepage from the bearing housing into the compressor housing as a result of a pressure differential across the bearing housing and the compressor housing. A bypass system with a pressure dependent check valve is connected to the inlet air passage of a turbocharged engine. When the pressure in the inlet air passage drops to below atmosphere or a predetermined level of depression, the check valve opens to allow a flow of atmospheric air into the inlet air passage, thus minimizing or eliminating the pressure differential generated as a result of a vacuum in the inlet air passage during motoring conditions, or when an exhaust valve downstream of the turbocharger is closed, such as during engine braking. The bypass system is applicable to both single stage and dual stage turbocharged internal combustion engines. | 07-04-2013 |
20130170949 | WIND TURBINES AND METHODS FOR CAPTURING WIND ENERGY - Wind turbines and energy capturing assemblies for capturing fluid energy are provided. The wind turbines includes a plurality of helical air foil blades mounted for rotation about an axis, and a cylindrical airfoil mounted along the axis and shaped to direct a flow of fluid, such as, air or water, toward the plurality of helical airfoil blades. Incorporating photovoltaic devices within the turbines can enhance the energy capturing capacity of some turbines. The energy capturing assemblies include a plurality of airfoil blades mounted for rotation about an axis, a structure having an outer surface shaped to direct a flow of fluid toward the plurality of airfoil blades; and an electrical generator operatively connected to the plurality of airfoil blades. The structure may be a building, a residence, a tower, a tank, or a vessel. Methods and devices for capturing fluid energy are also included. | 07-04-2013 |
20130170950 | VARIABLE SHAPE INLET SECTION FOR A NACELLE ASSEMBLY OF A GAS TURBINE ENGINE - A method of improving the aerodynamic performance of an inlet section of a nacelle assembly of a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, (a) sensing an operability condition, (b) adjusting a leading edge of the inlet section in response to the step (a), and (c) adjusting a thickness of the inlet section in response to the step (a). | 07-04-2013 |
20130170951 | LEAD ANGLE VALUE SETTING METHOD, MOTOR DRIVING CONTROL CIRCUIT, AND BRUSHLESS MOTOR - A method for setting a lead-angle value of a motor drive control circuit is disclosed. The motor drive control circuit energizes and drives the windings of a motor with an energizing timing based on a stored lead-angle value. The method includes the steps of: rotating a rotor at a given rpm (step S | 07-04-2013 |
20130177383 | DEVICE AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A device for sealing a gas path in a turbine includes a first shroud segment and a slot in a surface of the first shroud segment. A barrier extends inside the slot, and a bypass channel in the slot provides fluid communication between the barrier and the slot to the gas path in the turbine. A method for sealing a gas path in a turbine includes placing a barrier between a first slot in a first shroud segment and a second slot in a second shroud segment and flowing a fluid between the barrier and the first slot to the gas path in the turbine, wherein the fluid flows through a first bypass channel in the first slot. | 07-11-2013 |
20130177384 | TURBINE NOZZLE COMPARTMENTALIZED COOLING SYSTEM - The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit. | 07-11-2013 |
20130177385 | GAS TURBINE ENGINE FORWARD BEARING COMPARTMENT ARCHITECTURE - A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure. | 07-11-2013 |
20130177386 | TURBINE ASSEMBLY AND METHOD FOR CONTROLLING A TEMPERATURE OF AN ASSEMBLY - According to one aspect of the invention, a turbine assembly includes a first component, a second component circumferentially adjacent to the first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to abut a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first side surface, a second slot formed longitudinally in the second side surface, wherein the first and second slots are configured to receive a sealing member, and a first groove formed in a hot side surface of the first slot, the first groove extending axially from a leading edge to a trailing edge of the first component. | 07-11-2013 |
20130177387 | INTERSEGMENT SPRING "T" SEAL - A spring seal includes a split body portion with a first leg and a second leg that extend away from a plane and a projection portion which extends from the split body portion within the plane. | 07-11-2013 |
20130177388 | STARTUP METHOD FOR LARGE STEAM TURBINES - A method of controlling a steam turbine, having a controller controlling at least the position of a steam inlet valve located in a steam conduit between a steam generator and the turbine to control mass flow into the turbine, includes selecting, before beginning startup, a predefined set of startup sequences of setpoints based on a turbine status at the beginning of startup and/or a startup mode chosen by the operator, the set of startup sequences of setpoints includes parameters controlled and not controlled by the controller; using the controller to control the parameters controlled by the controller so as to progress the turbine from setpoint to setpoint in accordance with predefined set of startup sequences until reaching a release point; and at the release point, delaying moving to the next setpoint until actual setpoint values agree with predefined release point setpoint values for parameters not controlled by the controller. | 07-11-2013 |
20130177389 | TURBOMACHINE COMPONENT TEMPERATURE CONTROL - Apparatus and methods for expanding a process fluid are disclosed. The apparatus includes a casing having an inlet and an outlet, and a component carrier disposed in the casing. The component carrier and the casing defining a cavity therebetween, and the component carrier at least partially defines a process flowpath fluidly communicating with the inlet and the outlet of the casing. The apparatus also includes a rotor disposed at least partially in the component carrier, with the rotor at least partially defining a first expansion stage intersecting the process flowpath. The apparatus also includes a bleed port extending from the process flowpath at a first point of the process flowpath to the cavity, to provide a thermal buffer fluid to the cavity. | 07-11-2013 |
20130177390 | TURBINE ENGINE SHAFT - A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet. | 07-11-2013 |
20130177391 | ELECTROSTATIC CONTROL OF AIR FLOW TO THE INLET OPENING OF AN AXIAL FAN - A method of modifying the airflow to the inlet of an axial fan comprises operating an axial fan to move air longitudinally through an air inlet opening of the axial fan, and, during operation of the axial fan, applying an electrical potential between an emitter and a collector to cause ionic air movement radially outwardly away from a central axis of the axial fan, wherein the radially outward air movement is caused upstream of the axial fan before the air reaches the air inlet opening. | 07-11-2013 |
20130177392 | Aircraft Airflow Modulation System and Method - The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode. | 07-11-2013 |
20130177393 | Hybrid Compressor System and Methods - An apparatus ( | 07-11-2013 |
20130183135 | METHOD AND APPARATUS FOR TURBO-MACHINE NOISE SUPPRESSION - A turbo-machine inlet includes a gas passage having a non-gradual bend prior to an impeller assembly. The non-gradual bend causes a localized shockwave in fluid flowing through the gas passage. | 07-18-2013 |
20130183136 | START SYSTEM FOR GAS TURBINE ENGINES - A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path. | 07-18-2013 |
20130183137 | CENTRIFUGAL PUMP WITH SECONDARY IMPELLER AND DUAL OUTLETS - A fluid pump includes a primary impeller and a secondary impeller disposed on a common drive shaft within a pump housing. The pump housing including a respective diffuser or volute therein for each of the primary impeller and the secondary impeller. A fluid passage is formed within the housing connecting a discharge of the primary impeller to an intake of the secondary impeller. Each of the primary and secondary impellers has a respective outlet port. | 07-18-2013 |
20130189071 | OIL PURGE SYSTEM FOR A MID TURBINE FRAME - An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF. | 07-25-2013 |
20130189072 | SPRING SYSTEM TO REDUCE TURBOCHARGER WASTEGATE RATTLE NOISE - A turbocharger for a motor vehicle. The turbocharger includes a compressor mechanically coupled to a turbine. The wastegate of the turbine includes a valve head matched to a valve seat. The valve head is retained at one end of an actuator arm. A resilient spacer is arranged between the valve head and the actuator arm. The resilient spacer is configured to forcibly separate the valve head from the actuator arm when the valve head is unseated. | 07-25-2013 |
20130189073 | RETROFITTABLE INTERSTAGE ANGLED SEAL - A rotary turbomachine includes a rotor mounting at least one disk having an outer surface and at least one bucket extending radially from said outer surface. A stationary stator component is located adjacent the disk, and a seal plate extends from a portion of the stationary stator component. An angel wing seal extends from the bucket, thereby defining a clearance gap between the seal plate and the angel wing seal. An abradable seal element is disposed on the seal plate, and the abradable seal element and the seal plate are canted at an acute angle relative to a center axis of the rotor extending radially outwardly in a direction toward the angel wing seal. | 07-25-2013 |
20130189074 | MULTIPLE-CAPACITY CENTRIFUGAL COMPRESSOR AND CONTROL METHOD THEREOF - The present disclosure relates to a multiple-capacity centrifugal compressor, which includes a plurality of capacity-control mechanisms. Each of the capacity-control mechanisms includes an inlet guide vane and an outlet diffuser, so that the multiple-capacity centrifugal compressor provides a flexible control strategy. In addition, the present disclosure further provides a method for controlling the multiple-capacity centrifugal compressor that effectively adjusts and controls the capacity-control mechanisms by coarsely adjusting the inlet guide vanes and combined with subsequently adjusting the outlet diffusers. | 07-25-2013 |
20130189075 | APPARATUS AND METHOD FOR CONTROLLING COMPRESSOR - There is disclosed herein a compressor control apparatus, and a compressor control method. According to the present disclosure, the compressor may be operated in an operation mode in which commercial power applied to the compressor does not pass through an alternating current capacitor when the load is in an overload state, thereby preventing the loss of a drive and effectively reducing the copper and core loss of the compressor. Furthermore, according to the present disclosure, the entire power consumption may be reduced due to the loss reduction of a drive, thereby improving the energy efficiency, and reducing the harmonic components for generating the same stroke even when an alternating current (AC) capacitor is provided therein. | 07-25-2013 |
20130195603 | TURBOMACHINE FAN CLUTCH - An exemplary turbomachine clutch assembly includes a clutch that moves from a first position to a second position in response to rotation of a turbomachine fan at a speed greater than a threshold speed. The clutch permits rotation of the turbomachine fan in a first direction whether the clutch is in the first position or the second position. The clutch limits rotation of the turbomachine fan in an opposite, second direction when the clutch is in the first position. | 08-01-2013 |
20130195604 | TURBOMACHINE GEARED ARCHITECTURE SUPPORT ASSEMBLY - An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion. The less compliant portion includes a stop that limits axial movement of a geared architecture within a turbomachine | 08-01-2013 |
20130195605 | Fan Case Rub System, Components, and Their Manufacture - A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades. | 08-01-2013 |
20130195606 | INLET DESIGN FOR A PUMP ASSEMBLY - One embodiment includes an air pump assembly ( | 08-01-2013 |
20130195607 | INLET DESIGN FOR A PUMP ASSEMBLY - One embodiment includes an air pump assembly ( | 08-01-2013 |
20130195608 | DROPLET CATCHER FOR CENTRIFUGAL COMPRESSOR - A liquid droplet catching device installed in a compressor impeller, the device includes an aperture disposed on a surface of the impeller and configured to receive the liquid droplet, and a channel disposed beneath and in fluid communication with the aperture, wherein in the channel is configured to direct the liquid droplet away from the aperture and out of the compressor impeller. | 08-01-2013 |
20130195609 | MID-SPAN GAS BEARING - A centrifugal compressor includes a rotor assembly with a shaft and a plurality of impellers, bearings located at ends of the shaft and configured to support the rotor assembly, a sealing mechanism disposed between the rotor assembly and the bearings, and a gas bearing disposed between the plurality of impellers for supporting the shaft and receiving a working gas from an impeller downstream from a location of the gas bearing. | 08-01-2013 |
20130195610 | NOISE-REDUCED TURBOMACHINE - Turbomachine with an annular main flow duct ( | 08-01-2013 |
20130195611 | Unknown - A method for vibration damping of at least one blade of a turbomachine, wherein initially at least one damping element is arranged on the blade such that it can move in the axial direction, employs a damping element having a larger permeability constant than the blade (μ | 08-01-2013 |
20130195612 | APPARATUS AND METHOD FOR CONTROLLING A COMPRRESSOR - An apparatus and method for controlling a compressor are provided. A motor current flowing in a compressor may be calculated from voltage values of a capacitor without using a sensor, and as a motor current value is calculated by changing voltage values of the capacitor according to voltage values of a drive and performing a definite integral thereon, the motor current value may be resistant to noise, and the compressor may be more stably controlled. | 08-01-2013 |
20130195613 | APPARATUS AND METHOD FOR CONTROLLING A COMPRESSOR - An apparatus and method for controlling a compressor are provided. An input voltage of a commercial power source, a motor voltage of a compressor motor, and a motor current of the compressor motor are detected, based on which voltage values of a capacitor and voltage values of a triac may be calculated. Thus, an additional operational amplifier or a sensor to measure a capacitor voltage is not required, reducing costs. | 08-01-2013 |
20130195614 | TURBOCHARGER CONTROL - A method of controlling a variable geometry turbocharger is provided. A predefined desired boost pressure of a turbocharger is obtained from a memory. A predefined desired mass flow rate in an intake manifold of an engine is obtained from the memory. A theoretical amount of power required by the turbocharger to generate the desired boost pressure and the desired mass flow rate is calculated. An actual mass flow rate in the intake manifold is determined. An actual amount of power required by the turbocharger to generate the desired boost pressure and the actual mass flow rate is calculated. At least one adjustable vane of the turbine of the turbocharger is adjusted to allow the theoretical amount of power required of the turbocharger to generally equal the actual amount of power by adjusting the boost pressure. | 08-01-2013 |
20130195615 | DRIVE SHAFT SYSTEM - A drive shaft system ( | 08-01-2013 |
20130195616 | WAVE-DRIVEN BLOWER AND ELECTRIC MOTOR/GENERATOR - The present invention provides a wave-driven blower and a wave-driven generator. Embodiments can accelerate fluid flows with waves requiring with no or minimal moving parts. The waves driving the flow can be surface-thermal waves on the walls of the device. The velocity of the surface-thermal wave entrains the fluid near the surface and imparts a velocity to the fluid. Other types of waves can generate fluid flow. These other waves can be produced by variations in chemical composition, ionic concentration, chemical potential, total pressure, partial pressure and surface texture. Operating as a generator, the device extracts energy from a flowing fluid to amplify wave motions. The wave motions in turn generate electrical power or some other form of useable power | 08-01-2013 |
20130202401 | Method and Device for variable motion and applications using Interchangeable Heads - A machine for automating manual labor has a motor portion, transmission portion, and a head portion which may all be interchanged with alternates for different applications. The machine is driven by an electric motor that can perform different motions and actions, one at a time or simultaneously, depending on the transmission and head portions. Two such motions are rotary and linear reciprocating motion. Applications include cleaning surfaces, cleaning vessels, mixer, blender, chopper, slicer, shredder, vibrator, massager, semi and fully automatic milk cream maker. | 08-08-2013 |
20130202402 | ARTICULATING SLIDER TRACK - A variable fan nozzle assembly includes a cowl member mounted on a slider track. The slider track may be articulated relative to a support member to slightly modify the position of the cowl member to vary the fan nozzle exit area. At least one 4-bar linkage may be utilized to allow articulation of the slider track responsive to an actuator. A method for varying a fan nozzle exit area includes mounting a first slider track in articulatable relationship with a support member; mounting a first cowl member in slidable relationship with a first slider track such that a fan nozzle is at least partially defined by a surface of the first cowl member; varying the operational position of the first cowl member by articulating the first slider track without sliding the first cowl member with respect to the first slider track to vary the fan nozzle exit area. | 08-08-2013 |
20130202403 | LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE - A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed. | 08-08-2013 |
20130202404 | METHODS AND APPARATUS FOR DEPLOYABLE SWIRL VANES - An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream. | 08-08-2013 |
20130202405 | SELF-LUBRICATED COATING AND METHOD - Coating and method for providing a self-lubricated coating on a substrate. The method includes spraying with an inert gas at least a layer of liquid metal on the substrate; adding a compound to the liquid metal while being sprayed on the substrate; forming a porous layer on the substrate that includes the metal and the compound, where the porous layer has plural pores; heating the porous layer to open the pores; flooding the open pores with a greasing substance such that part of the greasing substance is stored in one or more pores; and cooling the porous layer to close the pores and trap the greasing substance inside the pores. | 08-08-2013 |
20130202406 | GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM - A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic. | 08-08-2013 |
20130202407 | Oscillating Hydrofoil, Turbine, Propulsive System and Method for Transmitting Energy - System and method for converting kinetic energy from a fluid flow into mechanical energy, the method comprising the steps of: a) providing a turbine including first and second hydrofoils, each of the hydrofoils being able to move lin-early in a heaving motion, and being able to oscillate about a spanwise axis in a pitching motion, said heaving and pitching motions being quasi-si-nusoidal, b) coupling the heaving motions of the first and second hydrofoils to the pitching motions of the second and first hydrofoils respectively, with the pitch-heave motion phase being substantially equal to the inter-hydrofoil phase, the heaving motion of one of the hydrofoils thereby driving the pitching motion of the other hydrofoil; and c) transforming the heaving motions of the hydrofoils into a rotational movement of a rotatable shaft, with linear-to-rotary transmission means. | 08-08-2013 |
20130209216 | TURBOMACHINE INCLUDING FLOW IMPROVEMENT SYSTEM - A turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members and a second plurality of airfoil members. A second stage is arranged within the housing relative to the first stage. The second stage includes a third plurality of airfoil members and a fourth plurality of airfoil members. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members. The predetermined clocking is configured and disposed to improve flow characteristics along the flow path. | 08-15-2013 |
20130209217 | PLATFORM SEGMENT FOR SUPPORTING A NOZZLE GUIDE VANE FOR A GAS TURBINE AND NOZZLE GUIDE VANE ARRANGEMENT FOR A GAS TURBINE - A platform segment for supporting a nozzle guide vane for a gas turbine is provided. The platform segment includes a gas passage surface arranged to be in contact with a streaming gas exhausted from a combustor, wherein the streaming gas streams along the gas passage surface in a streaming direction, a cooling surface, opposite to and thermally connected to the gas passage surface and arranged to be in contact with a cooling fluid, a wall protruding from the cooling surface and extending at least partially in the streaming direction, wherein the wall is arranged circumferentially between positions, at which adjacent guide vanes are to be provided, such that cooling fluid is channeled by the wall for cooling a downstream portion of the cooling surface, and a further wall protruding from the cooling surface and extending at least partially in the streaming direction. | 08-15-2013 |
20130209218 | TURBOMACHINE - A method for obtaining an estimate for a process quantity of a turbomachine comprises measuring ( | 08-15-2013 |
20130209219 | FULL-FLOW WASTEWATER SEWER SYSTEMS - A wastewater sewage system is disclosed. The sewage system includes a flow control valve that controls the flow of wastewater through the sewage system such that the sewage pipes in the sewage system are substantially full. | 08-15-2013 |
20130209220 | NOISE REDUCTION CONTROL FOR WIND TURBINES - A method of controlling noise emission from a wind turbine with a rotor blade includes providing wind shear data comprising wind shear values as a function of height over ground, determining an expected noise emission based on the wind shear data and controlling the wind turbine to reduce noise emission from the wind turbine in accordance with the expected noise emission. | 08-15-2013 |
20130209221 | ROTARY DAMPING MECHANISM WITH PIVOTAL VANES - A damping mechanism that includes a housing having fluid disposed therein and an inner circumferential surface, an axle shaft that is rotatable with respect to the housing, and a first vane having a distal end and being pivotally associated with the axle shaft. When the axle shaft rotates in a first direction, the first vane pivots to a deployed position, and when the axle shaft rotates in a second direction, the first vane pivots to a stowed position. A first clearance is defined between the distal end of the first vane and the inner circumferential surface of the housing when the first vane is in the deployed position, and a second clearance is defined between the distal end of the first vane and the inner circumferential surface of the housing when the first vane is in the stowed position. The second clearance is greater than the first clearance. | 08-15-2013 |
20130216351 | MAGNETICALLY-COUPLED DAMPER FOR TURBOMACHINERY - A system, method, and apparatus for damping vibration in a rotor supported by primary bearings are provided. The system includes a magnetic coupling configured to magnetically engage a rotor supported by one or more primary bearings, and a piston coupled to the magnetic coupling. The system also includes a damper engaging the piston and configured to damp the rotor, wherein the damper is substantially non-load bearing. | 08-22-2013 |
20130216352 | EJECTOR AND METHOD - In an aspect of the invention there is provided fluid pump apparatus comprising a plurality of ejectors, the apparatus having at least one motive fluid inlet arranged to supply motive fluid to the apparatus, at least one suction fluid inlet arranged to supply suction fluid to the apparatus and a common discharge outlet from which motive fluid and suction fluid that have passed through the ejectors may be expelled from the apparatus, each ejector having a respective injector portion and a respective diffuser portion, the injector portion being arranged to inject motive fluid from at least one said at least one motive fluid inlet into the diffuser portion thereby to draw suction fluid into the diffuser portion from at least one said at least one suction fluid inlet, the diffuser portion having a Venturi portion, each ejector having a respective flow stabilisation portion downstream of the Venturi portion thereof, the flow stabilisation portion being arranged to stabilise a flow of motive fluid and suction fluid therethrough before the respective flows of fluid through each ejector meet downstream of the ejectors, wherein the flow stabilisation portion comprises a flow stabilisation conduit of substantially constant diameter and a length substantially equal to at least the diameter thereof. | 08-22-2013 |
20130223973 | ACOUSTIC TREATMENT IN AN UNDUCTED AREA OF A GEARED TURBOMACHINE - An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine. | 08-29-2013 |
20130223974 | VARIABLE AREA TURBINE - A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition. | 08-29-2013 |
20130223975 | METHOD AND APPARATUS FOR STARTING SUPERSONIC COMPRESSORS - A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas collector, to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is effectively eliminated. | 08-29-2013 |
20130223976 | METHOD AND APPARATUS FOR LOCAL LOOP CLOSURE - A method and apparatus for local loop closure is provided. The apparatus includes a component for use in a gas turbine engine. The component includes at least one of an actuator and a servo-valve, at least one sensor, and an electronic module comprising controller electronics and memory. The electronic module is configured to receive and process commands for the at least one of an actuator and a servo-valve and queue received commands in an input buffer. | 08-29-2013 |
20130223977 | ACOUSTIC TREATMENT IN AN UNDUCTED AREA OF A GEARED TURBOMACHINE - An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine. | 08-29-2013 |
20130223978 | METHOD AND SYSTEM FOR TUNING A TURBINE USING SECONDARY INJECTION NOZZLES IN NOZZLE RING - A turbine and method of operating the same includes a housing having a volute and an outlet and an impeller rotatable coupled to the housing. The turbine includes a nozzle ring having a plurality of primary nozzles and a plurality of secondary nozzles. The plurality of primary nozzles and the plurality of secondary nozzles direct fluid toward the impeller. An auxiliary valve assembly selectively communicates fluid from the volute to the plurality of secondary nozzles. An actuator is coupled to the valve auxiliary assembly moving the auxiliary valve assembly from a first position communicating fluid from the volute into the secondary nozzles to a second position blocking flow of fluid to the secondary nozzles. | 08-29-2013 |
20130223979 | SYSTEMS AND METHODS FOR SUPPLYING REDUCED PRESSURE AND MEASURING FLOW USING A DISC PUMP SYSTEM - Disc pump systems and methods relate to a disc pump system that includes a first disc pump having a first actuator and a second disc pump having a second actuator. The systems and methods utilize sensors to measure the displacements of the actuators and a processor to determine the pressure differential across each actuator as a function of the measured displacements of the actuators. The disc pumps are fluidly coupled by a known restriction and the processor determines the flow rate of the disc pump system based on the determined pressure differentials across each actuator and the characteristics of the known restriction. | 08-29-2013 |
20130223980 | ACTIVE GRILL SHUTTER VANE DESIGN AND VEHICLE SYSTEM - An integrated assembly includes a vehicle bumper system, and upper and lower air shutter sections with subassembled shutter vanes movable between closed and open positions, an actuator mechanism for moving the shutter members between positions. When in the fully open position, the shutter vanes are aerodynamically designed to minimize air drag, both as air flows past the vanes and also during after-vane airflow (and during after-bumper-beam airflow). When in the fully closed vane position, the vanes seal against each other to provide a highly efficient and leak-resistant air-blocking assembly. | 08-29-2013 |
20130223981 | DEVICE AND METHOD FOR RELIABLY OPERATING A COMPRESSOR AT THE PUMP THRESHOLD - A method is used for determining an operating point of a compressor that includes at least one impeller, compressor blades attached to the impeller, a housing and at least two sensors. The method includes calculating a deflection of the compressor blades. An operating point and spacing of the blades is determined with respect to a surge limit based on the calculating of the deflection by measuring passage times of the compressor blades at a sensor. A signal that is representative of a rotation speed is determined and is associated with the compressor impeller. In a learning or adaptation mode, compressor blade-specific, state-induced and position-induced deviations from an ideal state are determined using compressor blade-specific passage times that are measured and compared with ideal passage times. In a working mode, compressor blade-specific passage times are measured and the compressor blade-specific passage times are corrected using the determined state-induced and position-induced deviations. | 08-29-2013 |
20130230379 | ROTATING TURBOMACHINE COMPONENT HAVING A TIP LEAKAGE FLOW GUIDE - A rotating turbomachine component includes a base portion and an airfoil portion extending from the base portion. The airfoil portion includes a first end connected to the base portion and a tip end portion that is cantilevered from the base portion. A tip leakage flow guide is provided at the tip end portion of the airfoil portion. The tip leakage flow guide includes one or more turning vane members configured and disposed to guide a leakage flow from the tip end portion at a flow angle that substantially coincides with a flow angle of gases flowing downstream from the rotating turbomachine component. | 09-05-2013 |
20130230380 | Rotating Housing Turbine - The invention is a new turbine structure having a housing that rotates. The housing has a sidewall, and turbine blades are attached to a sidewall portion. The turbine may be completely open in the center, allowing space for solids and debris to be directed out of the turbine without jamming the spinning blades/sidewall. The turbine may be placed in a generator for generation of electrical current. | 09-05-2013 |
20130230381 | Device For Monitoring A Pump - A device and a method for monitoring rotating components in centrifugal pumps or systems which comprise centrifugal pumps is provided. The device includes a first unit which is located on or in the component to be monitored having at least one component property sensor, a sensor signal evaluation unit, a transmitting unit for transmitting analysis results to a receiver arranged spatially separate from the monitored component, and a source for supplying power. The device further includes a second unit having a receiver unit, a transmitted signal evaluation unit, and a sensed component property display and/or information communication element. The analysis result transmission from the first unit to the second unit is acoustic. | 09-05-2013 |
20130230382 | MOTOR COOLING SYSTEM - A cooling system provided for a motor powering a compressor in a vapor compression system. The cooling system includes a housing enclosing the motor and a cavity located within the housing. A fluid circuit has a first connection with the housing configured to provide a liquid or two phase cooling fluid to the motor. The two phase cooling fluid is separable into a vapor phase portion and a liquid phase portion. The fluid circuit further has a second connection with the housing to remove cooling fluid in fluid communication with the fluid circuit. The cooling fluid conveyed through the second connection is two phase cooling fluid. The fluid circuit further has a third connection with the housing for receiving and circulating in the cavity the vapor phase portion conveyed through the second connection. | 09-05-2013 |
20130236288 | BLEED NOISE REDUCTION - An assembly for reducing compressor noise includes a compressor and an acoustic shield. The compressor has a rotor with a plurality of blades mounted thereto. Additionally, the compressor has one or more bleed slots therein. The acoustic shield is disposed adjacent to the one more bleed slots and spaced at a distance therefrom. | 09-12-2013 |
20130236289 | TURBINE INTERSTAGE SEAL SYSTEM - A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine. | 09-12-2013 |
20130236290 | SYSTEM AND METHOD FOR TURBOMACHINE MONITORING - A system for monitoring a turbomachine is provided. The system includes a turbomachine component having a variable geometry, a first sensor disposed to sense a condition of the turbomachine component, a second sensor disposed to sense an operational condition of the turbomachine, the operational condition being associated with an operation of the turbomachine component and a controller operably coupled to the first and second sensors, the controller being configured to execute a turbomachine process in accordance with a result of sensing by the second sensor with respect to the operational condition regardless of whether the first sensor detects the condition. | 09-12-2013 |
20130243564 | EXHAUST DIFFUSER FOR TURBINE - An exhaust diffuser for a turbine includes an inlet configured to receive exhaust gas from a last stage bucket of the turbine and an exhaust gas guide surface configured to guide the exhaust gas. A curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70. A method of diffusing exhaust of a turbine includes energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine. | 09-19-2013 |
20130243565 | STEAM TURBINE AND METHOD FOR REMOVING MOISTURE FROM THE STEAM TURBINE - A steam turbine includes an inner casing that at least partially defines the steam flow path, a passage for extending through the inner casing to at least partially define a moisture flow path out of the steam flow path, and a seal operably connected to the passage. The seal has a first position associated with a first set of operating conditions within the steam flow path and a second position associated with a second set of operating conditions within the steam flow path. | 09-19-2013 |
20130243566 | PUMP, PUMP SYSTEM, METHOD OF CONTROLLING PUMP, AND COOLING SYSTEM - A pump includes: an impeller that moves fluid; a housing section, provided adjacent to a channel for the fluid, that communicate with the channel; and a controller that positions the impeller in the channel during a driving of the impeller and houses the impeller in the housing section during a stoppage of driving of the impeller. | 09-19-2013 |
20130243567 | FAN ARRAY FAN SECTION IN AIR-HANDLING SYSTEMS - A fan array fan section in an air-handling system includes a plurality of fan units arranged in a fan array and positioned within an air-handling compartment. One preferred embodiment may include an array controller programmed to operate the plurality of fan units at peak efficiency. The plurality of fan units may be arranged in a true array configuration, a spaced pattern array configuration, a checker board array configuration, rows slightly offset array configuration, columns slightly offset array configuration, or a staggered array configuration. | 09-19-2013 |
20130243568 | Self-Cleaning Cover Plate in a Pump with Radial Flow - The invention relates to a cover plate ( | 09-19-2013 |
20130251499 | ENERGY EXTRACTION DEVICE AND OPERATING METHOD - The invention provides a method of operating an energy extraction device such as a wind turbine comprising a hydraulic pump driven by and applying torque to a rotating shaft, a hydraulic motor driving a load, a high pressure manifold in fluid communication with an outlet of the hydraulic pump and an inlet of the hydraulic motor and being selectively placed in fluid communication with a fluid accumulator, at least one low pressure manifold in fluid communication with an outlet of the hydraulic motor and an inlet of the hydraulic pump, at least one of the hydraulic pump or hydraulic motor is a digital hydraulic machine, characterised by interrupting fluid communication between the fluid accumulator and the high pressure manifold responsive to detection of a fault event. | 09-26-2013 |
20130251500 | GAS TURBINE ENGINE CASE WITH HEATING LAYER AND METHOD - An assembly of a rotor and case for a gas turbine engine comprises a rotor having a plurality of circumferential blades each with a blade tip. A case comprises a structural layer forming an annular body receiving therein the rotor, with a tip clearance being defined between the blade tips and the annular body, and a heating layer connected to the at least one structural layer. The heating layer has a resistivity to heat the structural layer when an electric current passes through the heating layer. An electric power source supplies current to the heating layer, the heating layer configured to in use change the diameter of the annular body to adjust the tip clearance. A method for adjusting a tip clearance between blade tips of a rotor and inner surface of a case in a gas turbine engine is also provided. | 09-26-2013 |
20130251501 | METHOD AND PURGE APPARATUS FOR PREVENTING DEFORMATION OF CHAMBER OF GAS TURBINE, AND GAS TURBINE PROVIDING PURGE APPARATUS - In this method of preventing deformation in a turbine casing of a gas turbine, in a turbine casing | 09-26-2013 |
20130251502 | Method and Apparatus for Sensing of Levitated Rotor Position - A pump with magnetically-levitated rotor includes a position sensor having an eddy-current sensor coil that operates as a resonating element in a low frequency oscillator located within the pump housing. The oscillator is operably interconnected with additional electronics that shift the frequency of the oscillator output signal to a lower frequency. The lower frequency signal is directed to a frequency measurement circuit that provides a value representing a position of the rotor. | 09-26-2013 |
20130251503 | METHOD OF CONTROLLING COMPRESSOR SYSTEM FOR PREVENTING SURGE OCCURRENCE AND COMPRESSOR SYSTEM USING THE SAME - Provided is a method of controlling a compressor system including measuring variables for generating a performance curve of a compressor, calculating changing rates of the variables; comparing the calculated changing rates with preset changing rate variations; and determining a surge control line different from a preset surge control line according to the calculated changing rates if the calculated changing rates are out of ranges of the preset changing rate variations. | 09-26-2013 |
20130251504 | TURBINE BYPASS SYSTEM - A turbine bypass system comprises a bypass path which is selectively operable to deliver hot gases to a gas cooler and a pebble bed positioned in the bypass path upstream of the gas cooler. The pebble bed absorbs heat from the bypass gases and thereby reduces the temperature of the bypass gases prior to delivery of the bypass gases to the gas cooler. | 09-26-2013 |
20130251505 | Ejector Cycle | 09-26-2013 |
20130259638 | TURBOMACHINE THERMAL MANAGEMENT - An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior. | 10-03-2013 |
20130259639 | TURBOMACHINE THERMAL MANAGEMENT - An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture. | 10-03-2013 |
20130259640 | METALLIC SEAL ASSEMBLY, TURBINE COMPONENT, AND METHOD OF REGULATING AIRFLOW IN TURBO-MACHINERY - A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change. | 10-03-2013 |
20130259641 | NACELLE WITH HINGED COWL DOORS ENABLING ACCESS TO THE ENGINE - A nacelle for an engine has outer and inner cowl doors that are independently rotatable about offset hinge lines. A connection device is provided for selectively connecting the outer and inner cowl doors so as to cause them to open simultaneously. The inner cowl door is arranged to rotate by a greater angle than the outer cowl door so as to improve access to the engine for maintenance purposes. | 10-03-2013 |
20130259642 | METHOD AND SYSTEM OF PROVIDING FLUID FLOW FOR A ROTOR - A rotor which comprises at least one blade and at least one fluid routing device that is mechanically connected to one of the blades so that a fluid inlet thereof is placed in a lateral edge of the blade. The fluid routing device has a continuous channel with an inlet facing the opposite direction of rotation of the blades and an outlet. The continuous channel is sized and shaped to conduct fluid passing via the inlet. The fluid routing device includes a flow directing element that is mechanically connected to the outlet so as to direct the conducted fluid to adjust fluid flow in or on the mechanically connected blade. | 10-03-2013 |
20130266416 | COOLING SYSTEM FOR A TURBINE VANE - A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other. | 10-10-2013 |
20130266417 | BEARING COOLING SYSTEM FOR FLEXIBLE SHAFT TURBOMACHINE - A turbomachine having gas cooled bearings may include an axially-oriented, cooling-gas passageway interconnecting first and second bearing chambers. The passageway may include grooves formed at an interface between an aerodynamic component of the turbomachine (e.g., a wheel or impeller) and a portion of a shaft assembly of the turbomachine. | 10-10-2013 |
20130266418 | CLEARANCE CONTROL SYSTEM FOR A GAS TURBINE - A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box. | 10-10-2013 |
20130266419 | ACTIVE FLOW CONTROL INTAKE FOR A GAS TURBINE ENGINE - Intakes of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. An active flow control arrangement for an intake comprises a compressed gas supply pipe, a valve arrangement, a controller, and a compressed gas distribution pipe. The supply pipe is fluidly connects between a compressed gas source and the valve arrangement. The distribution pipe fluidly connects between the valve arrangement and intake surface for supply of compressed gas thereto. The active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow passing through the intake from the inlet surface thereby maintaining stability of the intake air flow to the fan. | 10-10-2013 |
20130272839 | Method And Apparatus For Turbine Clearance Flow Reduction - A method for reducing clearance flow in a channel between a bucket and an enclosure of a turbine. The method includes separating a single flow in the channel into a first flow and a second flow and directing the second flow radially inward toward the bucket so that the second flow rejoins with the first flow to increase total flow onto the bucket. A turbine includes an inner casing, a rotatable shaft positioned axially within the inner casing, a plurality of buckets connected to the shaft, a first tooth projecting radially inward from and connected to the inner casing, wherein the first tooth and at least one bucket form a first fluidic channel therebetween and a second tooth connected to and in parallel with the first tooth form a radial fluidic channel. The axial fluidic channel is in communication with the radial fluidic channel to form a second fluidic channel. | 10-17-2013 |
20130272840 | COMPRESSED GAS SUPPLY UNIT, COMPRESSED GAS SUPPLY APPARATUS AND CONTROL METHOD OF SAID UNIT AND SAID APPARATUS - A compressed gas supply unit includes compressors. Gas discharged from the compressors is stored in a storage tank and then supplied to a gas recipient. The pressure of the storage tank, the operation temperature and the power consumption of each compressor, and the temperature around the compressors are sent to a controller and a monitoring device. A determination unit of the controller determines the presence or absence of the abnormality of the compressor from a difference between the operation temperature of the compressor and the temperature around the compressors. An effective load calculation unit calculates the effective load of each compressor from the power consumption of the compressor and the pressure of the storage tank. The controller controls the compressors based on the calculated effective load such that the loads of the compressors are equalized. An estimation unit estimates maintenance timing from the effective load. | 10-17-2013 |
20130272841 | FLUID TURBINE WITH INTEGRATED PASSIVE YAW - Example embodiments are directed to shrouded fluid turbines that include a turbine shroud and a rotor. The turbine shroud includes a an inlet, an outlet and a plurality of mixer lobes circumferentially spaced about the outlet. The rotor can be disposed within the turbine shroud and downstream of the inlet. The rotor includes a hub and at least one rotor blade engaged with the hub. The shrouded fluid turbines further include a passive yaw system for regulating a yaw of the shrouded fluid turbine. The shrouded fluid turbine defines a center of gravity and a center of pressure. The center of gravity can be offset from the center of pressure. Example embodiments are also directed to methods of yawing a shrouded fluid turbine. | 10-17-2013 |
20130272842 | FLUID TURBINE WITH HYBRID YAW - Example embodiments are directed to shrouded fluid turbines that include a turbine shroud and a rotor. The turbine shroud includes a plurality of mixer elements and the rotor can be disposed within the turbine shroud. The shrouded fluid turbine further includes a hybrid yaw system having a passive yaw system and an active yaw system for regulating a yaw of the shrouded fluid turbine. The hybrid yaw system further includes a torque limiter. Example embodiments are also directed to methods of yawing a shrouded fluid turbine. Example embodiments are further directed to hybrid yaw systems for a shrouded fluid turbine that includes a shrouded fluid turbine assembly rotationally engaged with a tower. The hybrid yaw system includes a passive yaw system and an active yaw system associated with the shrouded fluid turbine. | 10-17-2013 |
20130272843 | INTEGRATED RECIPROCATING PRIMER DRIVE ARRANGEMENT - A pump assembly includes a centrifugal pump having an intake, a discharge, a pump chamber and an impeller to deliver water from the intake to the discharge. A priming system is fluidly coupled to the pump chamber. A drive assembly includes a drive shaft coupled to the priming system and positioned around an impeller shaft coupled to the impeller for selective rotatable coupling of the impeller shaft and the drive shaft. | 10-17-2013 |
20130272844 | SYSTEM AND A METHOD FOR SETTING UP, COMMISSIONING AND OPERATING A WIND POWER PLANT - A system and a method for setting up, commissioning, and operating a wind power plant having a plurality of wind turbine generators (WTGs) operatively connected to a power grid, the system including a reconfigurable power plant controller comprising: a first regulator, a second regulator, and a management system operatively connected to the first and second regulators. The management system comprises a control mode compatibility unit that determines, according to a predefined compatibility table, the compatibility of any new control mode to be selected in one of the regulators with the currently selected control modes, and a control mode prioritization unit that establishes, according to a predefined set of priority rules, the sequence in which the selected control modes are implemented in the regulators. | 10-17-2013 |
20130272845 | AXIAL COMPRESSOR AND CONTROL METHOD THEREOF TO STABILIZE FLUID - A fluid stabilizing control method of an axial compressor is provided, which includes driving to drive the axial impeller, and stall controlling to suppress or prevent an occurrence of a stall that may transpire during rotation of the axial impeller by supplying highly-pressurized compressed air into the casing through a stall controller according to a predetermined time and volume. Accordingly, a stall may be suppressed or prevented, the occurrence of a stall that may transpire when a threshold point is exceeded by an unexpected event during driving in a low-flow high-pressure section on a performance curve, in which efficiency is high. Additionally, since an air injection method for suppressing the stall is properly applied, an amount of power expended for the stall control may be reduced while supply of the high-pressure compressed air is minimized, thereby achieving economically feasible stall control. | 10-17-2013 |
20130280027 | ANTI-VORTEX SHEDDING GENERATOR FOR APU SUPPORT - An assembly for use with a power-producing unit includes an annular case, a hub positioned radially inward of the case, a fluidic flow path defined between the case and the hub, a plurality of support tubes each extending between the case and the hub, and a flow modifying structure positioned on an exterior surface of at least a first one of the support tubes and configured to reduce vortex shedding of a passing fluid. | 10-24-2013 |
20130280028 | THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE - A thermal management system for a gas turbine engine includes a high pressure compressor rotor having a plurality of disks and a shaft; at least one forward cavity formed between a rim of at least one of the disks and the shaft and at least one aft cavity formed between a rim of at least one other of the disks and the shaft; a first flow of cooling air in the at least one forward cavity; and a second flow of cooling air in the at least one aft cavity. | 10-24-2013 |
20130280029 | AXIAL FAN AND CONTROL METHOD THEREOF - An axial fan includes a fan frame, an impeller and a motor. The fan frame has a frame body, a base and plural connecting members. The base is disposed at the center of a side of the frame body. The connecting members connect the frame body to the base. The impeller is accommodated in the frame body and disposed on the base. The impeller has a rotating shaft, a hub and plural blades disposed around the hub. The motor is disposed on the base and connects with the rotating shaft to drive the impeller to rotate. When the impeller rotates forwardly, the airflow is induced to flow through the connecting members, blades, and one side of the frame body away from the base. When the impeller rotates reversely, the airflow is induced to flow through the side of the frame body, blades and connecting members. | 10-24-2013 |
20130280030 | BYPASS FOIL - An apparatus for providing electrical power includes a foil having a leading inlet, at least rotor internal to the foil and downstream from the inlet and a trailing flow separator partially within a trailing chamber. The apparatus also includes leading and trailing edges configured such that fluid flowing through the foil experiences decreased pressure and increased velocity at the trailing edges relative to the leading edges. In a method utilizing the disclosed apparatus within a fluid flow, a first quantity of a high-pressure fluid is passed, at a low velocity, into the leading inlet of the bypass foil. One or more rotors are rotated by the flow and the rotational energy is translated into electrical power with a generator. After turning the rotors, quantity of fluid is ejected, at a high velocity, to the trailing edges of the bypass foil at an area of low fluid pressure. | 10-24-2013 |
20130280031 | THRUST REVERSER - A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser. | 10-24-2013 |
20130280032 | TURBOCHARGER ARRANGEMENT FOR AN INTERNAL COMBUSTION ENGINE - A turbocharger arrangement in an internal combustion engine is provided. The turbocharger arrangement includes a turbocharger housing surrounding a sealed inner space and a shaft extending through the turbocharger housing. The turbocharger arrangement further includes a turbine wheel arranged on the shaft and driving a compressor unit, a bearing arrangement mounting the shaft in the turbocharger housing, an oil supply device lubricating the bearing arrangement, and a pressure changing unit in fluidic communication with the sealed inner space configured to adjust the pressure in the sealed inner space based on engine operating conditions. | 10-24-2013 |
20130280033 | SYSTEMS AND METHODS FOR AVIAN MITIGATION FOR WIND FARMS - A wildlife detection system includes a tracking device, a receiver, and a wildlife deterrent system. The tracking device may be mounted to a wildlife. The receiver is configured to track movement of the tracking device relative to an object of danger to the wildlife. The wildlife deterrent system is configured to reduce risk of danger to the wildlife in response to movement of the wildlife within a predetermined distance from the object of danger as tracked by the receiver. | 10-24-2013 |
20130287542 | TWISTED VARIABLE INLET GUIDE VANE - A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided. | 10-31-2013 |
20130294883 | GAS TURBOMACHINE INCLUDING A COUNTER-FLOW COOLING SYSTEM AND METHOD - A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine and a counter-flow cooling system arranged within the casing. The counter-flow cooling system is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction. | 11-07-2013 |
20130294884 | DEVICE FOR MONITORING THE SEALING OF A ROTORCRAFT TRANSMISSION BOX BY SUCTION - A device for monitoring the sealing state of a casing ( | 11-07-2013 |
20130302136 | NON-AXISYMMETRIC RIM CAVITY FEATURES TO IMPROVE SEALING EFFICIENCIES - Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces. | 11-14-2013 |
20130302137 | Pumps with Improved Drive Shaft/Casing Seals - A pump includes a drive shaft linked to a motor. The drive shaft passes through a seal assembly before passing into the pump chamber. The seal includes an outer seal housing that accommodates a lip seal. A portion of the drive shaft that passes through the seal assembly is coated with PTFE to prolong the working life of the seal assembly. | 11-14-2013 |
20130302138 | VERTICAL AXIS TURBINE - Embodiments relate to a guiding apparatus, a wind turbine system, and methods related thereto. In an embodiment, a guiding apparatus for guiding a flow of a fluid for use with a rotor, the rotor comprising an annular radial vane assembly surrounding a central space which is enclosed save via the vane assembly and being arranged to rotate about a vertical axis, includes a screening for guiding the fluid to circulate substantially about the vertical axis within the central space in the same direction as the rotor during use, wherein the screening comprises an inner guide array concentrically surrounded by the vane assembly. | 11-14-2013 |
20130309060 | Turbocompressor Antisurge Control by Vibration Monitoring - The proposed mechanical method of turbocompressor surge detection uses vibration signals from vibration monitoring equipment mounted on the compressor components to detect a surge event and provide antisurge control thereby. This method utilizes only mechanical information to identify surge, as compared to present day antisurge controllers that use compressor thermodynamic information such as flow, pressure, and temperature to locate a compressor's operating point on a compressor map compared to a surge region. | 11-21-2013 |
20130309061 | FAN CONTROL SYSTEM AND FAN CONTROLLING METHOD THEREOF - A fan control system and a fan controlling method thereof are disclosed. The fan control system is used to an electronic apparatus for controlling an air pump fan device. The fan controlling method includes following steps: setting a plurality of vibrating working periods of the air pump fan device; setting a plurality of vibrating frequencies of the air pump fan device, wherein each vibrating frequency has a different vibrating frequency value; detecting a temperature of the electronic apparatus; determining whether the temperature of the electronic apparatus exceeding a first setting temperature; and if yes, controlling the air pump fan device to vibrate according to the plurality of vibrating frequencies during the plurality of vibrating working periods, wherein adjacent vibrating working periods of the plurality of vibrating working periods correspond to different vibrating frequency values. | 11-21-2013 |
20130309062 | VERTICAL AXIS TURBINE - Embodiments related to wind turbines and methods of guiding a flow of a fluid using a wind turbine. In one embodiment, a wind turbine includes a framework including an annular upper guide means and an annular base guide means; and an annular rotor assembly surrounding a central space, the rotor assembly comprising a plurality of rotor vanes, each rotor vane being held in position between the upper guide means and the base guide means. | 11-21-2013 |
20130315701 | AIRCRAFT PROPULSION SYSTEM AND A METHOD OF CONTROLLING THE SAME - An aircraft propulsion system has a propulsive rotor assembly rotatable about an axis of rotation and comprising a plurality of blades and a rotationally fixed vane assembly located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked. | 11-28-2013 |
20130323008 | TURBOMACHINE CONTAINMENT STRUCTURE - An exemplary containment structure includes an annular wall configured to receive a rotatable portion of a turbomachine. A plurality of apertures extend radially through the annular wall. The apertures have a varying circumferential width. | 12-05-2013 |
20130323009 | METHODS AND APPARATUS FOR COOLING ROTARY COMPONENTS WITHIN A STEAM TURBINE - A stationary component includes an outer ring including a first plenum, a first passageway, and a second plenum defined therein. The first passageway extends between the first plenum and the second plenum. An airfoil is disposed radially inward of the outer ring. The airfoil includes a second passageway defined therein. The second passageway is coupled in flow communication with the second plenum. | 12-05-2013 |
20130323010 | TURBINE COOLANT SUPPLY SYSTEM - A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore. | 12-05-2013 |
20130323011 | Nozzle Diaphragm Inducer - The present application provides a steam turbine driven by a flow of steam. The steam turbine may include a rotor, a number of nozzles positioned about the rotor, and a number of nozzle diaphragms. One or more of the nozzle diaphragms may include an inducer. | 12-05-2013 |
20130323012 | COMPRESSOR TIP CLEARANCE MANAGEMENT FOR A GAS TURBINE ENGINE - A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance. | 12-05-2013 |
20130323013 | NACELLE INNER FLOW STRUCTURE LEADING EDGE LATCHING SYSTEM - A latch assembly for securing a nacelle portion of a gas turbine engine includes first and second nacelle flow structures that define a portion of a bypass flowpath. A seal is engageable between the first and second nacelle flow structures. A latch is rotatable about a pivot between latched and unlatched positions. The latch maintains the seal in engagement with the first and second nacelle flow structures in the latched position. A method of opening a nacelle flow structure includes the steps of pivoting a latch from a latched position to an unlatched position, and unlatching a first nacelle flow structure relative to a second nacelle flow structure in response to the latch pivoting step. | 12-05-2013 |
20130323014 | ANTI-SURGE SPEED CONTROL - The present invention relates to a method and control system to control the speed of a centrifugal compressor operating within a vacuum pressure swing adsorption process to avoid an operation at which surge can occur and directly driven by an electric motor that is in turn controlled by a variable frequency drive. In accordance with present invention an optimal speed for operation of the compressor is determined at which the compressor will operate along a peak efficiency operating line of a compressor map thereof. This speed is adjusted by a feed back speed multiplier when the flow or other parameter referable to flow through the compressor is below a minimum and a feed forward multiplier during evacuation and evacuation with purge steps that multiplies the feed back multiplier to increase speed of the compressor and thereby avoid surge. | 12-05-2013 |
20130323015 | Power Distribution Unit With A Forced Lubrication Flow Assembly - A lubricant pump assembly for use with a power distribution unit for a vehicle, comprising a pump, a first rotating component, a second rotating component, and a lubricant. The pump has an inlet and an outlet. The inlet and the outlet are in fluid communication with a housing of the power distribution unit. The first rotating component is disposed in the housing of the power distribution unit. The second rotating component is disposed in the housing of the power distribution unit adjacent the first rotating component. The lubricant is disposed within the housing of the power distribution unit. The pump transfers a portion of the lubricant from the inlet to the outlet. The outlet is disposed adjacent the first rotating component and the second rotating component to dispose a portion of the lubricant therebetween. | 12-05-2013 |
20130323016 | METHOD FOR CONTROLLING THE CLEARANCE AT THE TIPS OF BLADES OF A TURBINE ROTOR - A method controlling a clearance between tips of blades of a turbine rotor of a gas turbine aircraft engine and a ring-shaped turbine shroud of a housing surrounding the blades, the method including: controlling flow and/or temperature of air directed toward the housing according to an estimate of the clearance, the estimate of the clearance is determined upon start-up of the aircraft engine, according to a temperature measured by a temperature sensor including a sensitive element positioned in a free space of the aircraft engine. | 12-05-2013 |
20130330166 | METHOD FOR CONTROLLING TEMPERATURE OF A TURBINE ENGINE COMPRESSOR AND COMPRESSOR OF A TURBINE ENGINE - According to one aspect of the invention, a method for temperature control of a turbine engine compressor includes directing a fluid from a first region proximate a main flow path in a downstream portion of a structure in a compressor to an upstream portion of the structure, wherein the fluid is cooled as the fluid flows through the upstream portion of the structure. The method further includes directing the fluid from the upstream portion of the structure downstream to a second region of the compressor to cool the second region, wherein the fluid is directed through passages in the upstream and downstream portions of the structure thereby substantially conserving an energy of the fluid within the structure and wherein a pressure of the second region is less than a pressure of the first region. | 12-12-2013 |
20130330167 | ACTIVE CLEARANCE CONTROL FOR GAS TURBINE ENGINE - An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The first wall includes impingement holes. The plenum is arranged over the structural member. A fluid source is fluidly connected to the second cavity to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member. A method includes the steps of providing a conditioning fluid to an outer cavity of a plenum providing an impingement cooling flow through impingement holes from an inner wall of the plenum to an inner cavity, directing the impingement cooling flow onto a structural member, and conditioning a temperature of the structural member with the impingement cooling flow to control a blade tip clearance. | 12-12-2013 |
20130330168 | THERMALLY ACTUATED ASSEMBLY FOR A GAS TURBINE SYSTEM AND METHOD OF CONTROLLING A COOLING AIRFLOW PATH - A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity. | 12-12-2013 |
20130336757 | ACTIVE CONTROL OF BUCKET COOLING SUPPLY FOR TURBINE - A cooling gas flow control device for a turbine rotor that is internally located between the compressor and the turbine section of a turbine is disclosed. The cooling gas flow control device has a shape memory material that is used to actively adjust the cooling gas flow to internal parts of the turbine section between, including the buckets. | 12-19-2013 |
20130336758 | VARIABLE BLADE OUTER AIR SEAL - A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter. | 12-19-2013 |
20130336759 | TURBOMACHINE FLOW CONTROL DEVICE - An exemplary flow control device assembly for a turbomachine includes a flow control device configured to move between a first position and a second position. The flow control device in the first position forces more flow through a plurality of cooling holes than the flow control device in the second position. The plurality of cooling holes are upstream the flow control device relative a direction of flow through the turbomachine. | 12-19-2013 |
20130336760 | FAN CONTROL METHOD, FAN MODEL IDENTIFICATION METHOD, AND FAN CONTROL CIRCUIT - A fan control method is to be implemented by a control circuit for controlling a fan coupled thereto. The fan control method includes configuring the control circuit to output a driving signal to the fan such that the fan rotates according to the driving signal, to detect a rotational speed of the fan and to generate a feedback signal corresponding to the rotational speed thus detected, to identify a model of the fan according to the feedback signal thus generated, and to control rotation of the fan according to the model thus identified. | 12-19-2013 |
20130343864 | TURBOMACHINE FLOW STABILITY ENHANCEMENT DEVICE CONTROL - An example method of controlling a flow enhancement device includes providing a flow enhancement device that is configured stabilize a flow of air near a nacelle. The flow enhancement device has a first setting and a second setting that provides more stabilization than the first setting. The method includes monitoring parameters of a turbomachine to determine the stability of the flow of air near the nacelle. The method also adjusts the flow enhancement device between the first setting and the second setting based on the monitoring. | 12-26-2013 |
20130343865 | Blower Housing - A blower housing has a discharge direction, an axis of rotation, a polar axis that intersects the axis of rotation and is substantially perpendicular to the discharge direction, and an angular sweep of increasing fluid flow area. The fluid flow area, A, increases with increasing angular magnitude, Φ, as a function comprising at least a functional component that is at least one of (1) equal to, (2) substantially mathematically reducible to, and (3) substantially mathematically analogous to the equation, | 12-26-2013 |
20130343866 | PRE-TURBINE ENGINE CASE VARIABLE AREA MIXING PLANE - A device for use with a gas turbine engine having an augmentor downstream includes a variable area mixing plane upstream of the turbine exhaust case for receiving core stream flow and fan stream flow. A swirl vane induces swirl in the fan stream flow and directs that stream flow to a mixing cavity to mix with the core stream and flow to the turbine exhaust case. A splitter proximate the swirl inducing vane diverts fan stream flow to an exhaust line to cool the fan case during operation of the augmentor. | 12-26-2013 |
20130343867 | GAS TURBINE ENGINE WITH REVERSE-FLOW CORE HAVING A BYPASS FLOW SPLITTER - A gas turbine engine includes a bypass flow path. A core flow path has a reverse duct configured to reverse a direction of core flow. The core flow path includes an exhaust duct in fluid communication with the bypass flow path and is configured to introduce core exhaust flow in the core flow path back into the bypass flow path. A splitter is arranged in the bypass flow path and adjoins the exhaust duct. | 12-26-2013 |
20130343868 | Systems and Methods to Control Flow in a Rotor Wheel - Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages. | 12-26-2013 |
20130343869 | HYDROELECTRIC TURBINE RECOVERY SYSTEM AND A METHOD THEREFOR - The present invention relates to a hydroelectric turbine recovery system, and in particular a system which significantly reduces the complexity of recovering a base mounted hydroelectric turbine from a deployment site on the seabed by providing a frame having an open mouth which can be advanced around the turbine before the frame is fully lowered into locking engagement with the base, thereby allowing the base, with the turbine thereon, to be recovered from the seabed. | 12-26-2013 |
20130343870 | WASTE WATER ELECTRICAL POWER GENERATING SYSTEM - An electrical power generating system is connected to a sewer for conveying waste water to a sanitary treatment station. Waste water is propelled through the sewer line by pumping equipment which simultaneously pulverizes most large objects carried by the waste water. The waste water drives one or more water-operated turbines. The turbines are operatively connected to electrical power generators for producing electrical power and dispersing the power through an electrical power transmission system. | 12-26-2013 |
20140003905 | TURBOMACHINE MONITORING SYSTEM AND METHOD | 01-02-2014 |
20140003906 | NON-INTERRUPTED TURBOMACHINE FLUID SUPPLY | 01-02-2014 |
20140003907 | COOLING SYSTEM AND METHOD FOR AN AXIAL FLOW TURBINE | 01-02-2014 |
20140003908 | GAS PRESSURE BIASED SEALING METHOD FOR AN ACTUATING SHAFT | 01-02-2014 |
20140003909 | NON-LINEAR ASYMMETRIC VARIABLE GUIDE VANE SCHEDULE | 01-02-2014 |
20140017060 | RADIAL COMPRESSOR BLADE CLEARANCE CONTROL SYSTEM - A diaphragm assembly includes a cylinder, a circular flange, and a diaphragm. The cylinder defines an axis and includes a first end and a second end opposite the first end. The circular flange is coaxial with the cylinder and at a greater radial distance from the axis than the cylinder. The diaphragm extends from the second end of the cylinder to the flange. | 01-16-2014 |
20140017061 | GAS TURBOMACHINE INCLUDING A PURGE FLOW REDUCTION SYSTEM AND METHOD - A gas turbomachine includes a turbine portion including at least one turbine wheel, and a wheel shaft operatively connected to the at least one turbine wheel. The wheel shaft includes an outer surface. A stationary member includes an inner surface positioned outward of the outer surface of the wheel shaft to form a purge flow passage. A bearing housing is linked to the stationary member and spaced radially outward of the wheel shaft. The bearing housing includes at least one purge flow passage configured and disposed to guide a purge flow toward the wheel shaft. At least one of the outer surface of the wheel shaft and the inner surface of the stationary member includes a roughness inducing coating configured and disposed to increase drag and residence time of purge flow in the purge flow passage. | 01-16-2014 |
20140017062 | VACUUM PUMP WITH LONGITUDINAL AND ANNULAR SEALS - A multi-stage vacuum pump may include first and second half-shell components defining a plurality of pumping chambers and for assembly together along respective longitudinal extending faces; first and second end stator components for assembly at respective longitudinal seals for sealing between the first and second half-shell stator components when assembled together at the longitudinally extending faces; and annular seals for sealing between the first and second end stator components and the first and second half-shell stator components when assembled; wherein the longitudinal seals have end portions which abut against the annular seals for sealing therebetween and the first and second half-shell stator components have formations for resisting movement of the end portions away from the annular seals when the end portions are compressed between the first and second half-shell stator components. | 01-16-2014 |
20140023477 | COMBINATION PUMP ASSEMBLY AND METHOD OF USE - A combination pump assembly for circulation of a coolant and for providing suction includes a shaft and a coolant pump portion with a coolant pump housing that defines at least a portion of a coolant flow path. The coolant pump portion also includes a coolant pump member that is rotatably disposed within the coolant pump housing. The coolant pump member is operably coupled to the shaft to be driven by the shaft to pump the coolant through the coolant flow path. Furthermore, the pump assembly includes a vacuum pump portion with a vacuum pump housing that defines at least a portion of a suction path. The vacuum pump portion also includes a vacuum pump member that is rotatably disposed within the vacuum pump housing. The vacuum pump member is operably coupled to the shaft to be driven by the shaft to provide suction through the suction path. | 01-23-2014 |
20140023478 | TURBINE AND OPERATING METHOD OF THE SAME - According to one embodiment, there is provided a single-flow turbine using CO | 01-23-2014 |
20140023479 | AIRCRAFT TAIL REGION WITH A COOLING SYSTEM INSTALLED IN AIRCRAFT TAIL REGION - An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment. | 01-23-2014 |
20140030055 | APPARATUS, SYSTEM AND METHOD FOR PUMPING GASEOUS FLUID - An apparatus, system and method for pumping gaseous fluid are described. The centrifugal pump of the invention homogenizes at least a portion of the gas and liquid contained in produced well fluid thereby improving the efficiency of the pump in electric submersible pump (ESP) applications and decreasing the downtime of the ESP system. The impeller of the invention comprises an increased inlet area. The centrifugal pump of the invention comprises a single shroud located on the bottom side of an impeller, an increased inlet area of the impeller and an increased clearance gap between the impeller and a diffuser. One or more truncated vanes extend substantially upstream from the single shroud, wherein each truncated vane sits at a mid-pitch location between untruncated vanes starting from the bottom side of the impeller. | 01-30-2014 |
20140030056 | PROCESS GAS FLOW GUIDES FOR LARGE AREA PLASMA ENHANCED CHEMICAL VAPOR DEPOSITION SYSTEMS AND METHODS - The present invention provides methods and apparatus for a gas diffusion assembly in a deposition processing chamber. The invention includes a backing plate having an inlet for providing a process gas to a process chamber, a diffusion plate including a plurality of apertures for allowing the process gas to flow into the process chamber, a blocking plate disposed between the backing plate and the diffusion plate and including a plurality of apertures, and at least one gas flow guide disposed between the blocking plate and the backing plate and adapted to direct process gas flow laterally. Numerous additional features are disclosed. | 01-30-2014 |
20140030057 | AFT CASCADE TRANSLATING VARIABLE AREA FAN NOZZLE - An aircraft turbofan engine variable area fan nozzle (VAFN) is disclosed that has a forward end that is continuously supported within a circumferential recess in the wall of the nacelle in front of it. During operation, the VAFN translates back and forth but always has its front end within the recess. Relatively simple seals help seal the recess against the VAFN. An array of openings with aft facing vanes, termed an aft cascade, is built into the VAFN. The openings are hidden within the recess when the VAFN is in the forward-most positions, and they are exposed to allow air to flow from the bypass duct through the cascade when the VAFN is in aft positions. The aft cascades can have different airflow directions based on their locations around the engine. | 01-30-2014 |
20140030058 | Enhanced Turbocompressor Startup - A control method and apparatus for startup of turbocompressors to avoid overpowering a driver of the turbocompressor. In a first embodiment, the control system monitors input signals from transmitters of various control inputs. When the input signals exceed threshold values, the control system begins to close the antisurge valve. In a second embodiment, the antisurge valve begins to close after a predetermined time measured from the time startup is initiated. In both embodiments, the antisurge valve continues to ramp closed until the compressor has reached its operating zone, or until the compressor's operating point reaches a surge control line, at which point the antisurge valve is manipulated to keep the compressor from surging. | 01-30-2014 |
20140030059 | FLUID TURBINE WITH VARIABLE PITCH SHROUD SEGMENTS - One or more variable pitch airfoils in fluid communication with a rotor of a fluid turbine can control the amount of energy directed to the rotor, and further control the amount of energy generated by the turbine. Varying the pitch of the airfoils may provide a means of controlling the power output of a fluid turbine without the need to control the pitch of the rotor blades, and may further provide a means of mitigating the effects of wind shear on the rotor. Variable pitch airfoils may also include a means of controlling the active power, reactive power and SCADA, of a group of fluid turbines. | 01-30-2014 |
20140037422 | SYSTEM AND COOLING FOR RAPID PRESSURIZATION OF A MOTOR-BEARING COOLING LOOP FOR A HERMETICALLY SEALED MOTOR/COMPRESSOR SYSTEM - A system and method for rapid pressurization of a motor compartment and cooling system during a shutdown, a surge, and/or other situations in which the suction pressure significantly varies. A motor/compressor arrangement includes a seal gas system fluidly communicating with the motor compartment via a motor pressurization line, with the outlet of the compressor, and with a shaft seal. A motor pressurization valve is coupled to the motor pressurization line and a controller is configured to open the motor pressurization valve at start-up of the motor-compressor to supply seal gas to the motor compartment and to pressurize the motor compartment when a difference between the seal gas supply pressure and the suction pressure is indicative of the seal gas supply pressure being insufficient. | 02-06-2014 |
20140037423 | RAM AIR TURBINE OVERSPEED PROTECTION - A power generation system includes a ram air turbine that is connected to a generator. The power generation system may be located in a pod, for example a pod for mounting on an aircraft. The ram air turbine receives air that passes through an air path through the pod, going in through an air inlet, through the turbine to turn the turbine, and out through an air outlet. The system includes a deployable flow obstruction, such as one or more airbags, that are deployable to suddenly obstruct the flow through the air path. The obstruction may be used to cut off flow (or greatly reduce flow), when overspeed of the ram air turbine is detected. The obstruction deploys (for example, airbags deploy in an air inlet of the system) to prevent continuation of the overspeed operation of the turbine, which may damage parts of the system. | 02-06-2014 |
20140037424 | Thrust Balancing Device for Cryogenic Fluid Pump - An improvement for a turbine generator or pump having main bearings separated by a span of shaft and a thrust equalizing mechanism adjacent one of said main bearings, the improvement comprising a stationary length compensator interposed between the thrust equalizing mechanism and its adjacent main bearing to reduce the span between said main bearings. Preferably the length compensator is composed of material that shrinks less than the shaft of the generator, and the height of the length compensator, i.e., the compensating dimension, is selected according to desired thrust equalizing mechanism operating parameters over a temperature range. | 02-06-2014 |
20140037425 | Air ducting shroud for cooling an air compressor pump and motor - A compressor assembly having a sound reduction shroud and a sound level of 75 dBA or less when in a compressing state. The sound reduction shroud can be a cylinder head shroud, a pump cylinder shroud, or a pump assembly shroud. The sound reduction shroud can optionally cover one or more of a compressor pump assembly, a cylinder head and a compressed gas outlet line. A compressor assembly having a sound reduction conduit and a sound level of 75 dBA or less when in a compressing state. The sound reduction conduit provides a cooling air channel directing cooling air to cool one or more portions of the compressor assembly and can direct exhaust cooling air to an exhaust port. A method for compressing a gas at a sound level of 75 dBA or less when the compressor is in a compressing state using a sound reduction shroud or a sound reduction conduit. | 02-06-2014 |
20140037426 | METHOD FOR CONTROLLING A REGULATED-ROTATION-SPEED LOW-PRESSURE CENTRIFUGAL FAN - A method for controlling an automatic stall-prevention of a rotation-speed-regulated centrifugal fan. A control automatics is controlled by an automation system of the process wherein, the control automatics stalling is detected from a function of the electric current, voltage and frequency going to the motor of the centrifugal fan. | 02-06-2014 |
20140044517 | AIR SUPPLY AND CONDITIONING SYSTEM FOR A TURBINE SYSTEM AND METHOD OF SUPPLYING AIR - An air supply and conditioning system for a turbine system includes an atomizing air system comprising at least one conditioning component configured to receive a compressor discharge air supply at an inlet at a first temperature and a first pressure, wherein the at least one conditioning component conditions the compressor discharge air supply to a second temperature and a second pressure at an outlet. Also included is an air processing unit configured to receive the compressor discharge air supply from the outlet of the atomizing air system, wherein the air processing unit further conditions the compressor discharge air supply to a third temperature and a third pressure. Further included is a filter housing having at least one filter for filtering a main inlet airstream, wherein the compressor discharge air supply is provided from the air processing unit to the at least one filter. | 02-13-2014 |
20140044518 | CONTINUOUS-FLOW MACHINE WITH AT LEAST ONE GUIDE VANE RING - A continuous-flow machine, especially an axial compressor, having at least one guide vane ring that includes at least one row of adjustable guide vanes, whereby each guide vane is tapered relative to its vane body in the direction of its longitudinal axis as seen in a side view of the guide vane. In order to increase the stability of the flow in the continuous-flow machine, each row of guide vanes comprises first guide vanes and second guide vanes, whereby, as seen in a combined side view of a first guide vane and of a second guide vane, each first guide vane is tapered along its vane body in the lengthwise direction, and each second guide vane is tapered in the opposite direction. | 02-13-2014 |
20140044519 | METHOD AND DEVICE FOR THE RAPID OIL CHANGE ON DRIVE DEVICES OF WIND POWER PLANTS - The invention relates to a method for performing an oil change on a wind power plant, comprising the steps of rotating the rotor ( | 02-13-2014 |
20140044520 | MOLD PUMP ASSEMBLY - A molten metal pump assembly ( | 02-13-2014 |
20140050558 | TEMPERATURE GRADIENT MANAGEMENT ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF MANAGING A TEMPERATURE GRADIENT OF A TURBINE SYSTEM - A temperature gradient management arrangement for a turbine system includes a rotor comprising a rotor bore extending axially along the rotor. Also included is a secondary flow path comprising an inlet for a secondary airflow to flow to the rotor bore and an outlet disposed axially upstream of the inlet, relative to a main flow direction of the turbine system. Further included is a flow rate manipulator disposed proximate the outlet and configured to increase a flow rate of the secondary airflow during a first turbine system operating condition and to decrease the flow rate of the secondary airflow during a second turbine system operating condition. | 02-20-2014 |
20140050559 | GAS TURBINE AND METHOD FOR OPERATING A GAS TURBINE - A gas turbine is provided including a rotor which includes a rotor portion of a fluid bearing for rotatably supporting the rotor, a radially outer stator portion, a radially inner stator portion including a stator portion of the fluid bearing, a compressor air passage extending between the radially outer stator portion and the radially inner stator portion, and an annular gap between the rotor and the radially inner stator portion partially forming an annular air passage in communication with the compressor air passage, wherein along a flow direction of air flowing within the annular air passage a radius of the air passage decreases in a first portion and then increases in a second portion. Further a method for operating a gas turbine is described. | 02-20-2014 |
20140050560 | Lubrication of Volumetrically Operating Expansion Machines - The present invention provides a method for lubricating an expansion machine, which method comprises: supplying of an operating medium which contains a lubricant by a vaporizer; separating of at least part of the lubricant from the operating medium which contains a lubricant and is supplied by the vaporizer; and supplying of the operating medium, which is depleted by the separation of the at least one part of the lubricant from the lubricant, to the expansion machine. Furthermore, a device is provided having a vaporizer which is configured for vaporizing an operating medium which contains a lubricant and for supplying it to an expansion machine, and having a lubricant separating device which is configured for separating at least one part of the lubricant from the operating medium which contains the lubricant and is supplied by the vaporizer to the expansion machine. | 02-20-2014 |
20140050561 | OIL SUPPLY SYSTEM AND METHOD FOR SUPPLYING OIL FOR A TURBOPROP ENGINE - An oil supply system for a propeller turbine engine includes a first oil circuit for supplying the turbomachine and a second oil circuit for supplying the propeller gearbox and the high-pressure pump associated with a propeller adjusting device. The two oil circuits are integrated into a common oil tank and connected to one another by means of an oil supply line in the flow direction downstream of the first and the second oil conveying pumps in such a way that a limited oil volumetric flow can flow from the first oil circuit into the second oil circuit, and only in this direction, if the pressure difference between the first and the second oil circuits falls below a certain level in the event of a pressure reduction in the second oil circuit. In this way, a sufficiently high initial pressure of the oil is produced at the high-pressure pump, even at low propeller speeds and during transient propeller adjustment processes, so that the function of the propeller adjusting device is not impaired and the high-pressure pump is not damaged. Limiting the oil volumetric flow in the oil supply line connecting the two oil circuits prevents that the turbomachine is inadequately supplied with oil, while oil is being removed from the first oil circuit. | 02-20-2014 |
20140056685 | ANNULAR TURBOMACHINE SEAL AND HEAT SHIELD - An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbomachine. | 02-27-2014 |
20140056686 | COOLING AIR CONFIGURATION IN A GAS TURBINE ENGINE - Cooling air is provided from a source of cooling air through a cooling air circuit in a turbine section of a gas turbine engine. A first portion of cooling air is provided from the source along a first path of the circuit to a plurality of blades associated with a stage of the turbine section. A second portion of cooling air is provided from the source along a second path of the circuit. The second path includes a turbine disc bore where the cooling air provides cooling to a radially innermost portion of at least one turbine disc that forms a part of a rotor of the engine. The second path is independent from the first path such that the second portion of cooling air bypasses the stage and is not mixed with the first portion of cooling air in the circuit after leaving the source. | 02-27-2014 |
20140056687 | INTEGRATED METHOD OF DRIVING A CO2 COMPRESSOR OF A CO2-CAPTURE SYSTEM USING WASTE HEAT FROM AN INTERNAL COMBUSTION ENGINE ON BOARD A MOBILE SOURCE - An integrated system and method for driving a CO | 02-27-2014 |
20140064908 | VALVE FOR CONTROLLING FLOW OF A TURBOMACHINE FLUID - An exemplary valve device for controlling flow of a turbomachine fluid includes a housing having a first inlet at a first elevation, a second inlet at a second elevation higher than the first elevation, and an outlet. A flow control member is within the housing. The flow control member in a positive g-force environment is biased toward a first position that permits flow through the first inlet to the outlet. The flow control member in a negative g-force environment is biased toward a second position that restricts flow through the first inlet to the outlet. | 03-06-2014 |
20140064909 | SEAL DESIGN AND ACTIVE CLEARANCE CONTROL STRATEGY FOR TURBOMACHINES - A labyrinth seal design, an actuation control clearance strategy, and a method of operating a turbomachine. The labyrinth seal design including a plurality of features configured to open and close radial clearances in response to relative axial movement between a stationary component and a rotating component. The actuation control clearance strategy and method of operating a turbomachine effective to achieve relative motion between a rotating component and a stationary component of the turbomachine using active elements. Axial displacement of the rotating component relative to the stationary component provides an adjustment in a radial clearance at one or more sealing locations between the rotating component and the stationary component to suit a given operating condition of the turbomachine. | 03-06-2014 |
20140064910 | Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines - Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism may include a moveable actuation rod in operative communication with a torque shaft such that movement of the actuation rod rotates the torque shaft. The control mechanism also may include a first unison ring in operative communication with the torque shaft such that rotation of the torque shaft drives the first unison ring. Moreover, the control mechanism may include a second unison ring in operative communication with the torque shaft such that rotation of the torque shaft drives the second unison ring. | 03-06-2014 |
20140064911 | Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines - Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring. The control mechanism also includes a linkage in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring drives the second unison ring. | 03-06-2014 |
20140064912 | Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines - Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism may include a moveable actuation rod in operative communication with a gear ring such that movement of the actuation rod drives the gear ring. The control mechanism may also include a first plurality of variable stator vanes disposed on a first side of the gear ring, the first plurality of variable stator vanes comprising gear stems in operative communication with the gear ring. Moreover, the control mechanism may include a second plurality of variable stator vanes disposed on a second side of the gear ring, the second plurality of variable stator vanes comprising gear stems in operative communication with the gear ring. | 03-06-2014 |
20140064913 | Impingement Plate for Damping and Cooling Shroud Assembly Inter Segment Seals - An impingement plate is cooperable with a shroud assembly. The shroud assembly includes an outer shroud and plural inner shrouds with seals between the plural inner shrouds, respectively. The impingement plate includes a trailing edge portion, a leading edge portion and a mid portion between the trailing edge portion and the leading edge portion. A plurality of impingement holes are formed across an area of the impingement plate, and a cooling and damping section includes at least one channel that is shaped to accelerate cooling flow through the impingement plate. | 03-06-2014 |
20140064914 | CONTROL ROD DEVICE - A control rod configuration for adjusting a position of a rotor blade of a helicopter. The control rod configuration includes a control rod which has a bearing eye, adjacent the swash plate, which is penetrated by an axle shaft which has a bearing supported by a bearing bracket. The control rod configuration, which can be simply constructed and is less susceptible to malfunction, has an eccentric with its pivotable bearing in the bearing bracket and which is provided between the bearing bracket and the bearing eye. In addition, a method in which a rotor blade of a helicopter has an assigned control rod which is supported by an axle shaft with a bearing in the bearing bracket which is mounted to the swash plate so as to enable adjustment of the control rod by pivoting the axle shaft during flight. | 03-06-2014 |
20140064915 | METHOD FOR OPTIMIZING THE SPEED OF A TWIN-SPOOL TURBOJET ENGINE FAN, AND ARCHITECTURE FOR IMPLEMENTING SAME - A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear. | 03-06-2014 |
20140064916 | COOLING SYSTEM AND METHOD FOR DATA CENTER - Cooling system for a data center includes at least one air-conditioner, at least one air-guiding fan, a first temperature sensor, a second temperature sensor, and a control unit. The air-guiding fan exchanges air between the data center and an external environment of the data center. The first temperature sensor senses an interior temperature of the data center. The second temperature sensor senses an environmental temperature outside of the data center. The control unit controls operating state of the air-conditioner, the first air-guiding fan, and the second air-guiding fan. When the environmental temperature is lower than the interior temperature, the control unit turns off the air-conditioner and the air-guiding fan. | 03-06-2014 |
20140064917 | Hydraulic Motor-Driven Bearing Lubrication System For A Centrifugal Pump - A bearing lubrication system for a centrifugal pump includes a hydraulic recirculating pump that is structured to provide recirculation of a fluid to and from the motor that drives the impeller of the centrifugal pump, and a system of efferent and afferent conduits that are connected to both the motor and the bearing housing of the centrifugal pump to direct lubricating fluid to or from the bearings, and to or from the motor for recirculation to the hydraulic recirculating pump, thereby utilizing the lubricating fluid used to lubricate the drive motor as a means of lubricating and cooling the bearings that support the rotating shaft of the pump. | 03-06-2014 |
20140072399 | SYSTEM AND METHOD FOR OPERATING A GAS TURBINE ENGINE - A system includes a gas turbine engine, which includes a compressor configured to generate compressed air and a turbine. The turbine includes a stationary component and a conduit configured to convey the compressed air from the compressor to the stationary component in a forward direction. The gas turbine engine also includes a flow control device coupled to the conduit. The conduit is configured to convey a gas path air from the stationary component in a reverse direction opposite from the forward direction when the flow control device is in a startup mode. The gas turbine engine also includes a shaft coupled to the compressor and the turbine. | 03-13-2014 |
20140072400 | Serpentine Cooling of Nozzle Endwall - A gas turbine nozzle section of a gas turbine may include an inner endwall with a leading edge. A serpentine passage may be configured substantially within the leading edge. The serpentine passage may have an inlet and an outlet. Air may be received at the inlet and exhausted at the outlet, cooling the leading edge. | 03-13-2014 |
20140072401 | Axial Diffuser Flow Control Device - An axial diffuser for a gas turbine includes diffuser walls that define diffuser channels receiving compressor discharge air. The diffuser walls diverge in a flow direction. A flow control device is disposed in the diffuser channels and includes a plasma controller that serves to ionize airflow in the diffuser channels. | 03-13-2014 |
20140079529 | Flat Bottom Damper Pin For Turbine Blades - A damper system for the buckets of a gas turbine engine. The damper system may include damper pins having a generally rounded top portion and a generally flat bottom portion along substantially the entire length thereof. The generally flat bottom portion may allow addition or removal of material to or from the pin in order to achieve an optimal dynamic weight ratio. | 03-20-2014 |
20140079530 | AIR COOLING DESIGN FOR TAIL-CONE GENERATOR INSTALLATION - A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust. | 03-20-2014 |
20140079531 | HYDROSTATIC MOTOR AND METHOD FOR OPERATING A HYDROSTATIC MOTOR - Disclosed is a motor which uses a hydrostatic force to generate a torque which repeats cyclically owing to a displacement of the center of gravity of a cyclic unit. Float bodies ( | 03-20-2014 |
20140079532 | HYDRAULIC MACHINE AND METHOD OF OPERATING SAME - In one embodiment, a hydraulic machine includes a runner including a plurality of blades arranged in a ring shape, a crown connected to the blades from an upper side and having a lower end surface at a position surrounded by the blades, and a band connected to the blades from a lower side, the runner being configured to convert energy of pressured water into rotational energy. The machine further includes a main shaft configured to transmit the rotational energy of the runner to a generator, and a draft pipe located downstream of the runner, and configured so that the water used to drive the runner flows into the draft pipe. The machine further includes a columnar member disposed on a rotation axis of the main shaft below the crown, and having a diameter smaller than a diameter of the lower end surface of the crown. | 03-20-2014 |
20140079533 | ELECTRONIC DEVICE AND METHOD FOR CONTROLLING TEMPERATURE OF ELECTRONIC DEVICE - An object of the present invention is to provide an electronic device in which a temperature control using a cooling fan can be made more efficiently and more stably and a method for controlling temperature of a device. | 03-20-2014 |
20140086722 | RAM AIR FLAP SYSTEM - An assembly for increasing air flow to a vehicle cooling system includes a portion of a cooling fan shroud, the portion having a face defining an opening therethrough, and a plurality of support members extending from the face. A flap includes a plurality of apertures proximal to an edge. Each aperture of the plurality of apertures is formed to receive one of the plurality of support members for coupling the flap thereto. A clearance fit formed between the apertures and the support members permits movement of the flap from a first position generally parallel to the face to a second position in response to a flow of air. | 03-27-2014 |
20140086723 | WIND TURBINE CONTROL SYSTEM WITH DECENTRALIZED VOTING - The present invention relates to a fault-tolerant control system for a wind turbine comprising a plurality of controllable wind turbine components, the control system comprising control means for generating a replica of essentially concurrent set-point values, a data communication network for transmitting the replica of essentially concurrent set-point values to the plurality of wind turbine components, and a plurality of decentralised voting means being arranged so that a decentralised voting means is assigned to each wind turbine component, each decentralised voting means being adapted to select one set-point value out of the replica of set-point values. The present invention further relates to a wind turbine and to an associated method. | 03-27-2014 |
20140086724 | GAS TURBINE ENGINE COMPONENT - An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes: | 03-27-2014 |
20140093349 | Systems and Methods for Operating and Validating a Compressor - Certain embodiments of the disclosure may include systems, methods and apparatus for operating and validating a compressor. According to an example embodiment of the disclosure, a method is provided for validating compressor operation. The method can include receiving compressor operating parameter data from a plurality of sensors; and adjusting a portion of a variable flow area downstream of a compressor discharge to achieve a desired compressor pressure ratio. | 04-03-2014 |
20140093350 | REAL TIME MODEL BASED COMPRESSOR CONTROL - A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin. | 04-03-2014 |
20140093351 | APPARATUS AND METHOD OF OPERATING A TURBINE ASSEMBLY - A method of operating a turbine assembly is provided. The method includes receiving a flow of air at a filter house that includes a first heat exchanger. The temperature of the air is controlled with the first heat exchanger by one of selectively cooling the air and by selectively heating the air. The air is then channeled from the first heat exchanger to a second heat exchanger to facilitate cooling the air. | 04-03-2014 |
20140093352 | EXHAUST DIFFUSER ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF REDIRECTING A FLOW - An exhaust diffuser arrangement for a turbine system includes an inlet for receiving a flow proximate a last stage bucket of the turbine system, the flow flowing in a first flow direction. Also included is a flow redirecting component. The flow redirecting component includes a first wall having a first side of a concave surface geometry for redirecting the flow and a second side of a convex surface geometry. The flow redirecting component also includes a second wall spaced downstream of the first wall and having at least one flow exit for reducing a boundary layer along the second side of the first wall. | 04-03-2014 |
20140093353 | SOLID SEAL WITH COOLING PATHWAYS - The present application provides a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine. The seal may include a first surface facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough. | 04-03-2014 |
20140099182 | DUCT DAMPER - An example damper includes a damping member configured to damp a duct wall at an interface between a duct band and the duct wall | 04-10-2014 |
20140099183 | TURBINE COMPONENTS WITH PASSIVE COOLING PATHWAYS - The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface. The adaptive cooling pathways may include a high temperature compound therein. | 04-10-2014 |
20140099184 | SEALING SYSTEMS FOR TURBOEXPANDERS FOR USE IN ORGANIC RANKINE CYCLES - Methods and systems for controlling infiltration of ambient air into, and exfiltration of process gas out of, an organic Rankine system. A system comprises a first sealing mechanism configured to seal at least one shaft against exfiltration of a process gas when the turbomachine is operating. The system further comprises a second sealing mechanism configured to seal the at least one shaft against infiltration of ambient air when the system is in a standstill mode. The system further comprises one or more pressure sensors configured to detect a pressure of gas within the system to monitor whether infiltration of ambient air has occurred and a system purge is needed. | 04-10-2014 |
20140099185 | HYDROELECTRIC POWER GENERATING DEVICE AND SYSTEM - A fluid conduit has a constant diameter and a chamber in the conduit has a larger diameter than the diameter of the conduit. Within the chamber, an impeller is rotatable by fluid moving through the conduit and the chamber. The impeller includes blades extending spirally along an impeller shaft. When rotated, the impeller blades define a cylinder having a diameter greater than the conduit diameter and less than the chamber diameter. | 04-10-2014 |
20140105720 | METHOD AND A SYSTEM FOR ADJUSTING NOZZLE AREA IN STEAM TURBINES - The various embodiments herein provide a method and a system for controlling a nozzle area in a steam turbine. The system comprises a nozzle ring provided with a plurality of nozzle blades at an outer edge. The steam enters into the nozzle ring and jets out on the blades of the rotor disk. When there is an off design condition, the nozzle blades are plugged or opened by adding or removing the inserts. The nozzle area is increased or decreased by opening or plugging the nozzle passages manually or automatically with the help of the inserts. The embodiments herein provide a cost effective and simple solution to deal with the off design conditions. | 04-17-2014 |
20140105721 | OPTIMIZED MASS FLOW THROUGH A MULTI STAGED DUCT SYSTEM GUIDE VANE OF A WIND TURBINE - A multi-stage duct system adaptable to generate maximum power from a wind turbine is presented. The multi-stage duct system comprises a plurality of wind turbine units. Each of the plurality of wind turbine units includes a plurality of turbine rings and a plurality of airfoils. The plurality of turbine rings defines to form a plurality of expanding stages and a plurality of contracting stages positioned in-line with a fluid flow direction. The multi-stage duct system further comprises a duct analysis unit having a plurality of axisymmetric ducts. The duct analysis unit utilizes a fluid dynamics mechanism to provide an optimal airfoil arrangement to the plurality of airfoils. The optimal airfoil arrangement optimizes a plurality of airfoil parameters associated with each of the plurality of airfoils thereby providing an efficient diffusion and an optimal fluid mass flow rate through the plurality of airfoils. | 04-17-2014 |
20140105722 | System and Methodology for Wind Compression - A wind compressor system having one or more wind turbines and a plurality of wind compressors located proximate the one or more wind turbines. The wind compressors optimize the energy created by the wind turbines by redirecting and converging the wind from the wind compressor to the wind turbines. Each of the wind compressors comprises an obstruction having a size and shape adapted to converge the wind currents by means of a Venturi effect toward the one or more turbines thereby increasing the velocity and force of the wind hitting the wind turbine. A plurality of transporters coupled to the wind compressors. The transporters configured to move at least one wind compressors to a location that maximizes the force of the wind encountered by the turbine. | 04-17-2014 |
20140105723 | GAS TURBINE DIFFUSER BLOWING METHOD AND CORRESPONDING DIFFUSER - A diffuser of a compressor of centrifugal or mixed type includes two end plates which enclose a plurality of regularly distributed circumferential blades, and at least one transverse upstream passage produced in lower or upper surfaces of the blades. An injection/withdrawal coupling is achieved by a recirculation of a stream in an air passage of the diffuser on the basis of injection of air from at least one point in a leading edge zone of an upstream side of the diffuser. Blowing of air is then effected in at least one groove formed along a lateral flank of each blade by withdrawal of the air stream in a region of a trailing edge. Thereby, effectively separation of the air in a boundary layer in a gas turbine compressor diffuser is realized by re-energizing the boundary layer with air at a higher pressure by a suction/re-injection coupling. | 04-17-2014 |
20140112753 | SEALING ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF SEALING BETWEEN TWO TURBINE COMPONENTS - A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material. | 04-24-2014 |
20140112754 | Thermal Control System Based on Nonlinear Zonal Fan Operation and Optimized Fan Power - An approach is provided in which a cooling manager retrieves pre-characterization data corresponding to a fan that electronic components included in a computer system. The pre-characterization data includes operational zones based upon fan power measurements and fan speed settings. The cooling manager sets the fan to a first speed setting within a first operational zone, and detects that one of the components generates a temperature change value that exceeds a specified temperature change value corresponding to the component. In turn, the cooling manager selects a second operational zone and sets the fan to a second speed setting within the second operational zone. | 04-24-2014 |
20140112755 | PUMPS - A pump assembly and components therefor including an impeller which has flow inducer elements on an inner surface of a front shroud thereof, a flow directing device or strainer having passageways for delivering material to the impeller and at least one flow circulating passageway and a pump casing having an intake section with flow distribution vanes in the region of a feed opening adjacent the intake section. | 04-24-2014 |
20140119878 | FLUIDIC TRAVERSE ACTUATOR - A system and methods for a self-rotating fluidic traverse actuator are presented. A turbine rotates in response to a fluid flow, and an outer cylinder with a longitudinal slot that ejects the fluid flow. An inner cylinder rotates inside the outer cylinder in response to a rotation of the turbine and at least one helical slot of the inner cylinder ejects the fluid flow into the longitudinal slot. | 05-01-2014 |
20140119879 | TURBOMACHINE PLASMA SEAL SYSTEM - Various embodiments include a turbomachine with a plasma seal system. The turbomachine can include: a diaphragm section having: an axially facing diaphragm wall; and a discourager seal protruding axially from the axially facing diaphragm wall; a rotor section having: a bucket having an axially facing bucket wall opposing the axially facing diaphragm wall; and a seal member extending from the axially facing bucket wall, wherein the seal member axially overlaps a portion of the discourager seal of the diaphragm section leaving a radial gap between the seal member and the discourager seal; and a plasma generator coupled to the diaphragm section for generating a plasma which reduces the radial gap between the seal member and the discourager seal. | 05-01-2014 |
20140119880 | TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE - A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer is provided including a flow body located within the intermediate space and including an inlet port, an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space. | 05-01-2014 |
20140119881 | APPARATUS FOR RECIRCULATING A FLUID WITHIN A TURBOMACHINE AND METHOD FOR OPERATING THE SAME - A turbomachine for use with a high-temperature and high-pressure working fluid is provided. The turbomachine includes a rotatable shaft and a casing enclosing the rotatable shaft, which defines at least a first and second compartment fluidly coupled together. The first compartment at least partially encloses one of a compressor and an expander. The second compartment at least partially encloses a generator. Attached to opposite ends of the rotatable shaft is a compressor for compressing the working fluid and an expansion turbine for expanding the working fluid. A motor-generator is attached to the rotatable shaft between the compressor and expansion turbine. The turbomachine includes at least one sealing system positioned between the first and second compartments that includes a number of seals for regulating the flow rate of the working fluid between the first and second compartments and for suppressing the heat and pressure transfer between the first and second compartments. | 05-01-2014 |
20140119882 | FAN CONTROL SYSTEM AND FAN CONTROL METHOD - A fan control system and a method thereof are applicable to a computer device. The system includes a fan, a board management unit, a power control module and a rotation speed switching module. The fan is driven by a control power and a rotation speed control signal. The board management unit provides a fan enabling signal, a rotation speed switching signal and a first fan rotation speed signal in a standby state. The power control module receives the fan enabling signal to determine whether to provide the control power to the fan, and switches between an auxiliary power or a main power served as the control power to the fan. The rotation speed switching module receives the rotation speed switching signal to accordingly switch between the first fan rotation speed signal or a second fan rotation speed signal served as the rotation speed control signal to the fan. | 05-01-2014 |
20140119883 | BLEED FLOW PASSAGE - A liner wall insert is provided for a compressor rotor stage of a gas turbine engine. Several liner wall inserts are provided radially outboard of the tips of the rotor blades. The liner wall inserts have bleed flow channels formed therein. The bleed flow channels are arranged to remove flow from a trailing edge region of the stage and re-inject the bleed flow at an upstream region. The re-injected bleed flow alters the flow field around the tips of the rotor blades, for example the tip leakage flow. Thus, the bleed flow is used to improve the efficiency of the compressor rotor stage, and thus of the gas turbine engine. | 05-01-2014 |
20140126991 | SYSTEMS AND METHODS FOR ACTIVE COMPONENT LIFE MANAGEMENT FOR GAS TURBINE ENGINES - The present application thus provides an active cooling system for a compressor and a turbine of a gas turbine engine. The active cooling system may include an air extraction pipe extending from the compressor to the turbine, a heat exchanger positioned about the air extraction pipe, and an external air cooling system in communication with the air extraction pipe. | 05-08-2014 |
20140126992 | TURBINE ENGINE COMPRISING A FLOATING BEARING FOR GUIDING A SHAFT OF THE TURBINE ENGINE - A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film. | 05-08-2014 |
20140126993 | DEVICE AND A METHOD FOR MEASURING THE TIMES OF PASSAGE OF BLADE TIPS IN A TURBINE ENGINE - A device and method to measure times of passage of blade tips in a turbine engine by a capacitive sensor mounted on a casing in register with a path followed by the tips of blades of a compressor wheel of the turbine engine. The sensor includes at least one elongate electrode fastened to an inside face of the casing and oriented obliquely relative to the path of the blade tips. | 05-08-2014 |
20140133955 | CARRIER INTERLOCK - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine case, a rotor stage including a plurality of rotor blades, a plurality of carriers for supporting a plurality of blade outer air seals and an interlock formed between circumferential ends of a first adjacent carrier and a second adjacent carrier of the plurality of carriers. | 05-15-2014 |
20140133956 | PROCESS FOR COOLING THE TURBINE STAGE AND GAS TURBINE HAVING A COOLED TURBINE STAGE - A gas turbine having a turbine stage is presented. The gas turbine has a guide vane that can be operated cooled by a cooling medium, and a cooling medium feed device for feeding the cooling medium into the interior of the guide van, which, in the region of its rear edge, has on the pressure side at least one cooling medium outlet opening, through which the cooling medium can flow out of the interior of the guide vane into the main flow. The cooling medium feed device has a mass flow control device for controlling the mass flow through the at least one cooling medium outlet opening, with which the mass flow through the at least one cooling medium outlet opening can be increased during operation of the gas turbine under part-load compared to operation of the gas turbine under full load. | 05-15-2014 |
20140133957 | METHOD OF DIFFUSING A GAS TURBINE COMPRESSION STAGE, AND DIFFUSION STAGE FOR IMPLEMENTING SAME - A diffusion stage of a radial or mixed gas turbine engine compressor includes an impeller formed by two plates, between which fluid flows in a centrifugal or inclined manner from a center towards a periphery. Blades of a cascade are distributed between the plates to channel the flow of the fluid between leading edges of the blades at the center and trailing edges at the periphery. At least one of the plates has an internal face including at least one zone with alternating hollow and bump curvatures between two adjacent blades, in at least one of two substantially perpendicular directions, in the direction of flow along the blades and in an inter-blade tangential direction. | 05-15-2014 |
20140133958 | Flexible Support Structure For A Geared Architecture Gas Turbine Engine - A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed. | 05-15-2014 |
20140140805 | Inducer Guide Vanes - According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity. | 05-22-2014 |
20140140806 | ENTHALPY DETERMINING APPARATUS, SYSTEM AND METHOD - Various embodiments include apparatuses and related methods for determining the enthalpy of steam. In some embodiments, an apparatus includes: an extraction conduit fluidly connected with a steam turbine section, the extraction conduit for obtaining wet steam from the steam turbine section; a mixing chamber fluidly connected with the extraction conduit; an injector fluidly connected with the mixing chamber, the injector for providing dry steam to the mixing chamber for mixing with the wet steam from the steam turbine section to produce a sample mixture; and an enthalpy detection system fluidly connected with the mixing chamber, the enthalpy detection system configured to determine an enthalpy of the sample mixture. | 05-22-2014 |
20140140807 | TURBINE SHROUD ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF CONTROLLING A TURBINE SHROUD ARRANGEMENT - A turbine shroud arrangement for a turbine system includes a first region of a tip shroud, the first region disposed in close proximity to an adjacent tip shroud. Also included is a second region of the tip shroud, the second region disposed in close proximity to the adjacent tip shroud, the second region comprising a temperature sensitive material configured to engage the second region and the adjacent tip shroud in contact over a first operating condition of the turbine system and configured to provide a second region gap over a second operating condition of the turbine system. | 05-22-2014 |
20140140808 | MITIGATING WIND TURBINE BLADE NOISE GENERATION IN RESPONSE TO AN ATMOSPHERIC VARIATION - Described embodiments include a wind turbine system. In this embodiment, the system includes a rotor blade attached to a rotor hub drivingly coupled to an electric generator. The system includes a controllable feature configured to decrease a noise generated by the rotor blade if activated. The system includes a sensor configured to detect an atmospheric variation approaching the rotor blade. The system includes a noise manager circuit configured to authorize a noise mitigation measure responsive to the detected atmospheric variation. The system includes a control circuit configured to activate the controllable feature in response to the authorized noise mitigation measure. In an embodiment, the system includes a support structure positioning the rotor hub a sufficient distance above the ground to allow rotation of the rotor blade about the rotor hub without contacting the ground. | 05-22-2014 |
20140140809 | HEAT PROTECTION ASSEMBLY - A flexible component includes a core element provided with a heat protection assembly. The heat protection assembly includes an intumescent coil wrap that extends around the core element. The coil wrap is arranged such that it is interlaced with a coil-shaped gap. This arrangement allows the component to retain flexibility, whilst still ensuring an adequate level of heat protection to the core element. | 05-22-2014 |
20140140810 | CONDENSER FAN SPEED CONTROL FOR AIR CONDITIONING SYSTEM EFFICIENCY OPTIMIZATION - A method for fan speed control for a condenser fan in an air conditioning system includes determining a refrigerant condition at an inlet of a compressor by a condenser fan speed control module; determining a refrigerant condition at an outlet of the compressor by the condenser fan speed control module; determining a parabolic curve of a relationship between an air conditioning system performance metric and a speed of the condenser fan based on the determined inlet condition and the determined outlet condition by the condenser fan speed control module; identifying an optimum condenser fan speed based on a vertex of the parabolic curve by the condenser fan speed control module; and controlling the speed of the condenser fan to meet the optimum fan speed by the condenser fan speed control module. | 05-22-2014 |
20140140811 | ABRASION RESISTANCE IN WELL FLUID WETTED ASSEMBLIES - Enhanced abrasion resistance in well fluid wetted assemblies is described. The bearing set of the invention provides an enhanced abrasion resistance that is better capable of withstanding friction from solids in electric submersible pump (ESP) well production applications. The flutes, grooves, sectors and intersections of the invention provide improved fluid and solid flow through assembly components, which improves cooling while the assembly is in operation and reduces body wear, thereby increasing the lifespan of the ESP system. | 05-22-2014 |
20140147242 | SEAL SYSTEMS FOR USE IN TURBOMACHINES AND METHODS OF FABRICATING THE SAME - A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al | 05-29-2014 |
20140147243 | Contra Rotating Wet Gas Compressor - A counter-rotating wet gas compressor for deployment and operation on the sea floor is described. The compressor has alternating rows of impellers, with each successive row of impellers being mounted a central hub or to an outer sleeve. According to some embodiments, no static diffusers are positioned between the alternating counter-rotating rows of impellers such that the design is structurally robust, compact and capable of compressing fluids that contain significant portions of liquid phase. | 05-29-2014 |
20140147244 | LIQUID RING HEAT ENGINE - A method and at least two devices demonstrate improvements to energy extraction from a compressible rotation working fluid in a liquid ring heat engine, which has a rotor mounted in a case. A space in the case is occupied by a liquid that establishes a liquid ring piston for the rotor. The rotor defines at least a first and a second operating zone. In the first zone, the working fluid is expanded against the liquid and, in the second zone, the working fluid is re-compressed. Between the two zones, the working fluid is cooled. In one device, the cooling step occurs on the rotor in a third zone. In another device, the cooling occurs outside of the case. | 05-29-2014 |
20140147245 | MONITORING AND CONTROL SYSTEM - A method of controlling the angular orientation of at least one variable fluidfoil. The method includes the steps of receiving detected fluidfoil angular orientation data for the at least one fluidfoil; receiving a fluidfoil angular orientation demand; generating a modified angular orientation demand by modifying the fluidfoil angular orientation demand before it is used to control adjustment of the at least one fluidfoil, the modification being performed using the detected fluidfoil angular orientation data; and outputting the modified demand and controlling the at least one fluidfoil angular orientation in accordance with the modified demand. | 05-29-2014 |
20140147246 | METHOD AND SYSTEM FOR DETECTING MALFUNCTION OF A MEMS MICROPUMP - Method for detecting failure including possible under or over delivery of a micropump having at least an inlet valve, a pumping chamber with an inner pressure sensor and an outlet valve, said method comprising the determination of the pump tightness via the measurement of the pressure by said inner pressure sensor in said pumping chamber at least at certain intervals when the pump is inactive and the comparison with a value of reference. | 05-29-2014 |
20140147247 | METHOD FOR OPERATING A ROTARY MACHINE - A method for operating a rotary machine with a rotor that is mounted in a bearing is provided. The rotor is subjected to a thrust that acts substantially in only an axial direction during the operating time. The thrust is received and dissipated by a first thrust bearing of the bearing via sliding means, the bearing having a second thrust bearing. The axial vibrations of the rotor are damped or completely prevented by means of the second thrust bearing generating a force that acts on the first thrust bearing in the direction of the thrust at least temporarily at the same time as the thrust occurs. | 05-29-2014 |
20140154046 | VARIABLE AREA TURBINE NOZZLE WITH A POSITION SELECTOR - A gas turbine engine ( | 06-05-2014 |
20140154047 | METHOD AND SYSTEM FOR STEAM PURITY MONITORING THROUGH USE OF HIGH ELECTRON MOBILITY TRANSISTORS - A method or system for steam purity monitoring in a steam powered turbine includes providing a chloride-sensing device in a steam flow path; generating a signal from the chloride-sensing device indicative of a concentration level of chloride ions in a steam flow; and indicating a concentration level of chloride ions in a steam flow. The steam turbine includes a rotor, a rotating shaft and a plurality of axially spaced rotor wheels. A plurality of rotating blades is mechanically coupled to each rotor wheel. A chloride-sensing device is disposed in a steam flow path. A controller is arranged to generate a signal from the chloride-sensing device indicative of a concentration level of chloride ions in a steam flow and indicate a concentration level of chloride ions in a steam flow. | 06-05-2014 |
20140154048 | HUB COOLING APPARATUS ADAPTED TO WIND-POWER GENERATOR AND METHOD THEREOF - A hub cooling apparatus adapted to a wind generator has a circulating fan module installed in a nosed end of a hub and a wind guiding module installed in a main shaft of a nacelle; wherein the circulating fan module is driven by the rotating hub, the wind guiding module is driven by the rotating main shaft. | 06-05-2014 |
20140154049 | VERIFICATION SYSTEM AND METHOD FOR ROTATION SPEED VALUE OF FAN - A verification method for a rotation speed value of a fan includes steps of receiving a predictive rotation speed value of the fan, an input environmental temperature value and a plurality of temperature values of components, sending the received environmental temperature value and a plurality of temperature values of components to the control unit to control the fan to rotate on the condition of the input temperature values; acquiring the actual rotation speed value of the fan on the condition of the input temperature values; detecting whether the actual rotation speed value of the fan is consistent with the predictive rotation speed value of the fan; and outputting information of showing that the actual rotation speed value of the fan does not match the predictive rotation speed value of the fan if not. | 06-05-2014 |
20140161585 | TURBO-MACHINE COMPONENT AND METHOD - A component, a component manufacturing process, and a component operation process are disclosed. The component has a diffuser permitting compressible fluid to flow throughout a first region and a second region of the diffuser at a decreasing velocity. The diffuser includes a coating collection feature. The component manufacturing process includes positioning the component and applying the coating to at least a surface of the component outside of the diffuser and to at least a portion of the second region, not to the first region, to the coating collection feature, or a combination thereof. The component operation process includes positioning the component and transporting the compressible fluid through the diffuser. | 06-12-2014 |
20140161586 | Pump Turbine Plant - The invention concerns a pump turbine plant, comprising a
| 06-12-2014 |
20140161587 | Seal Monitoring and Control System - A seal monitoring and control system for a gas lubricated non-contacting seal includes various sensors providing signals to a programmable logic control system. The control system is disposed to determine a presence of an anomalous operating condition of the seal, for example, based on phase, relative position of rotor to stator or other signals in combination provided by the various sensors to provide an output signal, which in one embodiment performs at least one mitigating process to correct the anomalous operating condition by adjusting at least one operating parameter of the seal. | 06-12-2014 |
20140169933 | Vertical Axis Windmill with Passive Over-Speed Protection - A windmill is disclosed having over speed protection. In a preferred embodiment, the vanes are symmetric, curved metal sheets, with each vane's shape having a circular arc corresponding to its portion of the cylindrical support structure. Each vane is mounted with a large leading portion exposed to the wind. The imbalance of surface area causes the wind to push the vane open when moving downwind and push the vane closed when moving upwind. During periods of high rotational speed, the off-axis centers of mass cause each vane to rotate towards a closed position under centrifugal force. Once the critical speed is reached, the vanes fully close as they pass through the upwind side. | 06-19-2014 |
20140169934 | ANTI-ICE SUPPLY SYSTEM FOR INLET GUIDE VANES - Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid. The at least one passageway is configured to communicate the fluid to each of the plurality of inlet guide vanes. | 06-19-2014 |
20140169935 | LIGHTWEIGHT SHROUDED FAN BLADE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan. | 06-19-2014 |
20140169936 | METHOD FOR DETECTING HEAT-DISSIPATING AIR FLOW AND ELECTRONIC DEVICE USING THE SAME - A method for detecting heat-dissipating air flow is disclosed. The method includes the following steps: detecting whether a reset command is input; if the reset command is input, resetting a wind pressure standard value according to the reset command; if the reset command is not input, controlling a fan to operate at full speed according to a start signal; detecting the wind pressure of a heat-dissipating air flow after controlling the fan to operate at full speed to acquire a wind pressure value; determining whether the wind pressure value is equal to the wind pressure standard value; and generating a warning signal if the wind pressure value is not equal to the wind pressure standard value. | 06-19-2014 |
20140169937 | MIXER-EJECTOR TURBINE WITH ANNULAR AIRFOILS - Example embodiments are directed to fluid turbines that include a turbine shroud, a rotor and an ejector shroud. The turbine shroud includes an inlet, an outlet, a leading edge and a trialing edge. The leading edge of the turbine shroud can be round and the trialing edge of the turbine shroud can include linear faceted segments. The rotor can be disposed within the turbine shroud and can define a rotor plane. The turbine shroud can provide a first portion of a fluid stream to the rotor plane via the inlet of the turbine shroud. The ejector shroud can provide a second portion of the fluid stream to the outlet of the turbine shroud via an open area. An example method of operating a fluid turbine is also provided. | 06-19-2014 |
20140178173 | EJECTOR ASSEMBLY - A recirculation flow collector for a fan includes an arcuate housing; a first face with a first circular opening to receive flow; a second face with a second circular opening to allow flow in a normal fan operating condition; and an outlet in a bottom of the arcuate housing to allow recirculation flow. | 06-26-2014 |
20140178174 | GAS TURBINE ENGINE INCLUDING A PRE-DIFFUSER HEAT EXCHANGER - According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage. | 06-26-2014 |
20140178175 | AIR TURBINE STARTER MONITOR SYSTEM - A method of monitoring a rotational system includes identifying a non-nominal spool-down profile. | 06-26-2014 |
20140178176 | Axial Compressor and Operation Method of the Same - An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing. | 06-26-2014 |
20140186152 | BLADE OUTER AIR SEAL SYSTEM FOR CONTROLLED TIP CLEARANCE - A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion. | 07-03-2014 |
20140186153 | SEALING SYSTEM AND METHOD OF MAINTAINING A CLEAN ENVIRONMENT IN A WIND TURBINE BY ABSORBING LUBRICANT USED IN THE PITCH OR YAW BEARINGS - A sealing system for a wind turbine comprises first component and a second component positioned proximate the first component and movable relative thereto. An absorbent element is secured to the first component and comprises an oil-absorbent material. A contact member is secured to the absorbent element and comprises a non-absorbent material. The contact member abuts the second component so that lubricant leaking from between the first and second components is collected by the absorbent element. A method of maintain a clean environment in a wind turbine with such a sealing system is also disclosed. | 07-03-2014 |
20140193236 | POWER PRODUCING DEVICE WITH CONTROL MECHANISM - A power-producing device, such as a ram air turbine, includes a controller that is used to control operation of a turbine of the power-producing device. The controller uses an input based on an airspeed of the aircraft as part of a control mechanism in the controller for controlling the turbine. For example controller may be used to control backpressure of the turbine, for example by controlling the angle of doors of that are used to adjust backpressure of the turbine. The control mechanism may include a PID controller, with the gain of one or more of the values of the PID controller being a function of the airspeed of the aircraft. In addition the control mechanism may include manipulating a setpoint as a function of load on the power-producing device. The power-producing device may be part of a detachable pod that is installed on the aircraft. | 07-10-2014 |
20140193237 | TURBO-MACHINE WITH ACTIVE ELECTRICAL CLEARANCE CONTROL - The disclosure relates to a turbo-machine comprising a stator and a rotor arranged rotatable inside the stator as well as at least one electric heating device which is arranged on the surface of at least part of the stator for active clearance control. Besides the turbo-machine, a method for operating the active clearance control comprising electric heating devices is disclosed. | 07-10-2014 |
20140193238 | METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE - A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0. | 07-10-2014 |
20140199155 | METHODS AND SYSTEM FOR DETECTING TURBOCHARGER DEGRADATION - Various methods and systems are provided for detecting turbocharger degradation. In one example, a method comprises detecting an axial position of a turbine rotor based on output from a turbine speed sensor, and if the axial position is greater than a threshold distance from a base position, indicating turbocharger degradation. | 07-17-2014 |
20140199156 | METHOD OF OPERATING A WIND TURBINE - A method of operating a variable speed wind turbine as a function of a wind speed is disclosed. The method comprises following a power curve describing the operation of the wind turbine as a function of wind speed in steady-state conditions. The method further comprises changing the pitch angles of the blades in transient conditions in which the wind turbine cannot follow the power curve in the second operational range. | 07-17-2014 |
20140199157 | METHOD FOR BARRING A ROTOR OF A TURBOMACHINE AND BARRING APPARATUS FOR CONDUCTING SUCH METHOD - A method for barring a rotor of a thermally loaded turbomachine includes stopping normal operation of the turbomachine; providing a barring device for rotating the rotor about a machine axis; coupling the barring device to the rotor; letting the rotor cool down during cool down of the rotor rotating the rotor by means of the barring device. A damage of the machine due to thermally induced buckling during the barring process is avoided by consecutively determining the force or torque applied to the rotor by the barring device for rotating the rotor and/or the circumferential speed of the rotor during barring. The rotation of the rotor is controlled by means of the barring device in dependence of the determined force or torque and/or circumferential speed in order to reduce a bending or imbalance of the rotor, which is due to a nonuniform temperature distribution on the rotor during cool down. | 07-17-2014 |
20140199158 | AIRCRAFT CONTROL AND MONITORING SYSTEM - A system for bleeding air on an aircraft, including: at least one air bleed valve that can bleed a flow of air on the aircraft, a first temperature information module, a second temperature information module, at least one control module, and at least one data processing module coupled to the control module. | 07-17-2014 |
20140199159 | WELL PUMP SYSTEM - Provided is a well pump system that includes a pressure pipe, a rotatable shaft surrounded by a plurality of bearings, a pumping mechanism mounted to the pressure pipe and having a plurality of pump impellers mounted to a second end of the shaft, a rotating mechanism mounted to a first end of the shaft and configured for rotating it within the bearings, thereby causing the pump impellers to move the fluid in the pressure pipe, and at least one non-return valve configured for assuming at least two states including a first, opened state, in which the second pipe chamber is in fluid communication with the first pipe chamber, and a second, closed state, in which the non-return valve obstructs the fluid communication between the first and the second pipe chambers, thereby lubricating them. | 07-17-2014 |
20140199160 | WIND TURBINE WITH TWO SETS OF BLADES AND METHOD OF OPERATION THEREOF - An air turbine has two sets of blades concentrically mounted on a rotatable shaft. The two sets of blades are housed separately and an air supply for the turbine enters an air inlet of a first housing to drive a first set of blades and exits from the first housing to a second housing through an air transfer opening to drive the second set of blades in the same direction, the air exiting the second housing through an air outlet. Returning blades of each cycle of each set of blades is subjected to little or no resistance. A flywheel is concentrically mounted on the shaft and is connected to drive generators. The air supply is a controlled air supply and, preferably, the air supply is compressed air. The shaft of the turbine is oriented to the either horizontal or vertical. | 07-17-2014 |
20140205424 | Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines - Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring. The control mechanism also includes a bell crank mechanism in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring drives the second unison ring. | 07-24-2014 |
20140205425 | OIL COOLING ARRANGEMENT AND METHOD OF COOLING OIL - An oil cooling arrangement includes a first manifold and a second manifold, each configured to route an oil. Further included is a first tube having a first end proximate the first manifold and a second end proximate the second manifold, wherein the first tube is configured to receive the oil and route the oil toward the second manifold. Yet further included is a second tube having a third end proximate the second manifold and a fourth end proximate the first manifold, wherein the second tube is configured to route the oil from the second manifold toward the first manifold. Also included is a turbine exhaust path configured to route an exhaust flow, wherein the first tube and the second tube are disposed along the turbine exhaust path, wherein the oil is cooled upon passage of the exhaust flow over the first tube and the second tube. | 07-24-2014 |
20140205426 | MULTIPLE TURBOCHARGER CONTROL - A turbocharger system comprises: a gas input for receiving exhaust gases from an engine; a first turbocharger comprising a first compressor driven by a first turbine, arranged to be driven by received exhaust gases and providing a compressed air output defining a boost pressure a second turbocharger, arranged to be driven by exhaust gases passing through the first turbocharger or exhaust gases received at the gas input and being coupled to an electrical generator operative to provide electrical power, the first turbine not being coupled to an electrical generator; and a controller. A diversion mechanism may be configured to affect the flow of exhaust gases between the gas input and the first turbocharger. The controller may be configured to adjust the operation of the electrical generator independently from the operating mode of the associated engine, to affect the boost pressure. | 07-24-2014 |
20140205427 | DEVICE FOR DE-ICING A LEADING EDGE OF A TURBINE ENGINE BY SLANTING NOTCHES - A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a first fluid flow device provided along an upper zone of the downstream guide vane so as to guide the fluid to the wall of the leading edge, and a second fluid flow device provided along a lower zone of the downstream guide vane so as to evacuate the fluid from the leading edge, wherein the first fluid flow device is arranged such that the wall of the leading edge is impacted by the fluid along a non-orthogonal direction. | 07-24-2014 |
20140205428 | Method for Primary Adjustment of a Hydroelectric Power Plant - The invention relates to a method for primary adjustment of a hydroelectric power plant comprising a dual adjustment turbine, at least one first actuator, and at least one second actuator, wherein the first and second actuators are reset depending upon an actual value of a network frequency of an electrical network which receives the generated electrical power for influencing the turbine output in order to achieve a target value of the network frequency. The invention is characterised in that the first actuators are only operated in predefined actuating steps, and then an adjustment to the target value of the network frequency is performed by resetting the second actuators. | 07-24-2014 |
20140205429 | ENERGY DIFFUSING WEAR RING AND METHODS THEREOF - An energy diffusion sealing ring [ | 07-24-2014 |
20140212260 | Airfoil Assembly with Paired Endwall Contouring - An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow. | 07-31-2014 |
20140212261 | LIGHTWEIGHT SHROUDED FAN - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan. | 07-31-2014 |
20140212262 | VARIABLE OUTER AIR SEAL SUPPORT - A variable outer air seal support system according to an exemplary aspect of the present disclosure includes, among other things, a case having a plurality of slots, and an extension of a variable outer air seal segment. The extension provides at least one extension aperture. A connector pin is configured to move within the slot to move the variable outer air seal segment from a first position to a second position. The variable outer air seal segment overlaps a circumferentially adjacent variable outer air seal segment more in the first position than in the second position. | 07-31-2014 |
20140212263 | AIRFOIL WITH VARIABLE PROFILE RESPONSIVE TO THERMAL CONDITIONS - An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions. | 07-31-2014 |
20140212264 | SYSTEM AND METHOD FOR FLUID LEVEL SENSING AND CONTROL - A system and method for sensing level of a fluid associated with a submersible pump having an impeller driven by an associated motor include a fluid level sensor having a probe with a plurality of discrete resistive elements each having an associated contact pair substantially evenly spaced along a length of the probe and an associated switch powered by an induced voltage or current generated by power provided to the submersible pump motor and activated by the fluid conducting across the contact pair to shunt the associated discrete resistive element. | 07-31-2014 |
20140212265 | GAS TURBINE INLET SILENCER - A system for attenuating sound emissions from an inlet to a flow path for an air inducting machine including an inlet duct structure having inlet and outlet passages. A planar vortex generator is located adjacent to the outlet passage and creates vortices that interact with a specific tonal acoustic frequency emitted from the inlet of the machine to effect formation of a standing wave at the vortex generator. The standing wave has an upstream propagating component that reflects off an acoustic reflector wall to form a reflected component that interferes with the upstream propagating component to attenuate the specific tonal acoustic frequency from the inlet of the machine. | 07-31-2014 |
20140212266 | DEVICE AND METHOD FOR REDUCING VIBRATION IN A COMPRESSOR - A device and method for reducing vibration in a compressor are provided. The device for reducing vibration in a compressor may include a compressor controlled to be operated at a target operating velocity after starting; a power supply that supplies power to the compressor; and a controller that controls the power supply so that a magnitude or a phase of the power supplied to the compressor is changed. The controller may control the power supply so that vibration generated in the compressor is offset by an exciting force generated in the compressor within a predetermined time interval multiple times when the compressor starts or when the compressor stops during a target operation velocity operating of the compressor. | 07-31-2014 |
20140219771 | Hydraulic Blocking Rotary Actuator - In one embodiment, a hydraulic blocking rotary actuator including a stator housing having a through bore to position a rotor assembly. A rotor assembly includes an output shaft and at least one rotary piston disposed radially about the output shaft. The rotary piston includes an integral first vane element and an integral second vane element each with peripheral longitudinal faces substantially concentric to the other. A continuous seal groove is disposed in peripheral longitudinal faces and lateral end faces of the rotary pistons. A continuous seal is disposed in the continuous seal groove. The bore through the stator housing includes an interior cavity with surfaces adapted to receive the rotor assembly. With rotation fluid ports blocked the housing cavity is sealed with the continuous piston seal for hydraulic blocking, preventing actuator displacement by external forces. Other embodiments are disclosed. | 08-07-2014 |
20140219772 | INDIVIDUAL INLET GUIDE VANE CONTROL FOR TIP TURBINE ENGINE - A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion. | 08-07-2014 |
20140219773 | Internal Mixing Of A Portion Of Fan Exhaust Flow And Full Core Exhaust Flow In Aircraft Turbofan Engines - A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle. A mixer duct shell is supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell. A first portion of fan exhaust may be routed through the mixer duct shell between its inner surface and an outer surface of a core engine shroud. A second portion of fan exhaust may be routed over an outer surface of the mixer duct shell. At least one of the inner surface and an outer surface of the mixer duct shell may have an acoustic lining including a honeycomb core structure. | 08-07-2014 |
20140219774 | TURBOMACHINE GEARED ARCHITECTURE SUPPORT ASSEMBLY - An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion. The less compliant portion includes a stop that limits axial movement of a geared architecture within a turbomachine | 08-07-2014 |
20140234070 | Systems and Methods for Facilitating Onboarding of Bucket Cooling Flows - Systems and methods Embodiments for facilitating onboarding of a cooling fluid are disclosed herein. According to one embodiment, a system may include a rotor assembly, a wheel space cavity adjacent to the rotor assembly, and a bucket shank cavity in fluid communication with the wheel space cavity. The system may also include at least one protrusion disposed on the rotor assembly in the wheel space cavity. The at least one protrusion may be configured to direct the cooling fluid radially from the wheel space cavity to the bucket shank cavity to minimize pressure loss in the cooling fluid. | 08-21-2014 |
20140234071 | BEARING HAVING PRE-LOADING ELEMENT AND METHOD FOR OPERATION OF THE BEARING - A bearing is provided which includes a first set of rolling elements, a second set of rolling elements spaced away from the first set of rollers, a race at least partially enclosing the first and second sets of rolling elements, and a pre-loading element in the race between two outer sections of the race applying pre-load forces to the first and second set of rolling elements. In this way, a simplified bearing structure is achieved while better maintaining pre-load forces. | 08-21-2014 |
20140234072 | MULTIPLE SPOOL TURBOCHARGER - Systems and methods for a multiple spool engine turbocharger are described. In one example approach, a multi-spool turbocharger comprises a compressor including a plurality of counter-rotating compressor spools and a turbine including a plurality of counter-rotating turbine spools. | 08-21-2014 |
20140234073 | CASING COOLING DUCT - A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine. | 08-21-2014 |
20140234074 | METHOD OF MIXING BETWEEN A PRIMARY FLOW AND A SECONDARY FLOW IN A TURBINE ENGINE, CORRESPONDING DEVICE AND TURBINE ENGINE - The invention relates to a method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, characterised in that it consists of disposing at least one divergent radial deflection means in primary duct, spaced apart from the walls of said primary duct. | 08-21-2014 |
20140241850 | AIR PARTICLE SEPARATOR - A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow. | 08-28-2014 |
20140241851 | AXIAL OIL SCOOP FOR A GAS TURBINE ENGINE - An axial oil scoop for a gas turbine engine includes an outer surface with a concave profile, the outer surface includes a multiple of radial holes. | 08-28-2014 |
20140241852 | METHODS AND APPARATUS FOR MEASURING AXIAL SHAFT DISPLACEMENT WITHIN GAS TURBINE ENGINES - In some embodiments, an apparatus includes a target member, a sensor and a mounting assembly. The target member is coupled to a shaft that is disposed within an engine housing and that rotates about an axis. The target member includes a target surface that is substantially normal to the axis of rotation of the shaft. The sensor is configured to produce a signal associated with a distance between a sensor tip and the target surface. The mounting assembly is coupled to the sensor and the engine housing, and is configured to adjust the distance between the sensor and the target surface. | 08-28-2014 |
20140241853 | VACUUM PUMP - A vacuum pump, in particular to a turbomolecular pump, has a pump inlet, a pump outlet and a pump space for a gas to be pumped arranged between the pump inlet and the pump outlet, and at least one cooling gas inlet for a cooling gas for cooling the vacuum pump, the pump further having one or more hollow regions for the cooling gas connected in a gas conducting manner to the cooling gas inlet and arranged outside the pump space, wherein the or each hollow region is bounded by at least one component of the vacuum pump to be cooled. | 08-28-2014 |
20140248115 | Active Clearance Control System with Zone Controls - An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment. | 09-04-2014 |
20140248116 | ACOUSTIC TREATMENT IN AN UNDUCTED AREA OF A GEARED TURBOMACHINE - An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine. | 09-04-2014 |
20140248117 | EXTERNAL MIDSPAN PACKING STEAM SUPPLY - An external supply pipe is disclosed, for supplying steam to a mid-span packing disposed about a shaft coupling a high pressure (HP) and an intermediate pressure (IP) section of an opposed flow steam turbine. The external supply pipe is disposed on an exterior of the steam turbine casing, which allows for direct measurement of steam flow to the mid-span packing. | 09-04-2014 |
20140248118 | START-UP METHOD FOR A WIND TURBINE AND A CONTROL ASSEMBLY - A method for starting-up a wind turbine having a rotor with at least one rotor blade is provided. The method includes rotating the at least one rotor blade towards a main operating position using a pitch drive system including a pitch bearing supporting the at least one rotor blade, and a pitch-driving pinion meshing with the pitch bearing; and activating a pump to feed a lubricant to a lubrication pinion meshing with one of the pitch bearing and the pitch-driving pinion before the at least one rotor blade reaches the main operating position so that the lubricant is mainly transferred to a load portion of the pitch bearing and/or a load portion of the pitch-driving pinion. Further, a control assembly for use with the wind turbine is provided. | 09-04-2014 |
20140248119 | Bifurcated Inlet Scoop for Gas Turbine Engine - A bifurcated inlet scoop frame for a gas turbine engine and method of using such frame for a gas turbine engine are disclosed. The bifurcated inlet scoop frame may include a nose, a first side panel, and a second side panel. The first side panel and the nose may define a first inlet port. The second side panel and the nose may define a second inlet port. The method may comprise providing a bifurcated inlet scoop frame, splitting the fan air flow, and receiving fan air through the bifurcated inlet scoop frame. | 09-04-2014 |
20140248120 | BI-METAL STRIP-SEAL - An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path. Upon heating, the bi-metal sealing member “uncoils” contacting the second perpendicular surface, thus blocking the flowpath between the two surfaces. Various metals may be provided to provide predetermined sealing characteristics. | 09-04-2014 |
20140248121 | AIRCRAFT POWER SYSTEM - A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible. | 09-04-2014 |
20140248122 | HIGH PRESSURE COMPRESSOR THERMAL MANAGEMENT - A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft. | 09-04-2014 |
20140248123 | CONTROL OF WIND TURBINES - A wind turbine power plant comprises a plurality of wind turbines, each having a rated output and under the control of a power plant controller. The power plant also has a rated output which may be over-rated in response to one or more of electricity pricing data, power plant age and operator demand. The power plant controller can send over-rating demand signals to individual turbines. The controllers at the turbines include a fatigue life usage estimator which estimates a measure of the fatigue life consumed by key components of the turbine. If this measure exceeds a target value for any component, over-rating is prevented at that turbine. | 09-04-2014 |
20140255144 | FLANGED BUSHING FOR VARIABLE VANE - An example turbomachine bushing a bushing having a wear surface configured to interface directly with a variable vane assembly to limit radially inward movement of the variable vane assembly, wherein the variable vane assembly is moveable axially between a first position contacting the wear surface and a second position spaced from the wear surface. | 09-11-2014 |
20140255145 | Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application - Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one embodiment, there is disclosed a turbine assembly. The turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one fixed purge air orifice may be associated with the stator assembly. The fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity. Moreover, at least one adjustable cooling air orifice may be associated with the stator assembly. The at least one adjustable cooling air orifice may be configured to provide a flow of cooling air to the wheel space cavity. | 09-11-2014 |
20140255146 | FIELD CONFIGURABLE FAN OPERATIONAL PROFILES - A system, apparatus, and procedure for controlling a fan module. The system comprises a chassis having a backplane, at least one fan module arranged in the chassis, and a profile switch. In one embodiment, the profile switch is arranged in the chassis. Each fan module includes at least one fan and a fan module controller arranged to receive a control signal from a shelf controller. The profile switch is arranged to signal the fan module controller so as to control the at least one fan based on operating profiles corresponding to selected switch positions of the switch. | 09-11-2014 |
20140255147 | METHOD OF IMMOBILIZING LOW PRESSURE SPOOL AND LOCKING TOOL THEREFORE - A method of immobilizing a low pressure spool assembly including maintaining a body of the locking tool in the annular gas path, attaching a securing portion of the body across an aperture defined through an annular wall delimiting the gas path; positioning a stop connected to the body of the locking tool into a rotary path of a given one of the sets of blades of the low pressure spool assembly; and rotating the high pressure spool assembly thereby biasing a blade of the given set of blades of the low pressure spool assembly against the stop, thereby immobilizing the low pressure spool assembly. A locking tool and a method of performing engine maintenance are also provided. | 09-11-2014 |
20140255148 | GAS TURBINE ENGINE CLEARANCE CONTROL - One embodiment of the present disclosure is a unique gas turbine engine having a bearing system and method of operating the engine. Another embodiment is a unique rotor machine. Desired clearances are maintained in the engine and rotor and by the method. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for rotor machines, such as but not limited to, gas turbine engines. | 09-11-2014 |
20140255149 | DUAL INLET TURBINE PUMP - A pump for providing a flow of fluid from a fluid source to a fluid destination. The pump includes a rotatable turbine, a first inlet port in fluid communication with the turbine, a first outlet port in fluid communication with the first inlet port, a second inlet port in fluid communication with the turbine, and a second outlet port in fluid communication with the second inlet port. The turbine pumps fluid from the fluid source into the first inlet port and out of the first inlet port into a reservoir. The turbine pumps fluid in the reservoir into the second inlet port and out of the second outlet port to the fluid destination. | 09-11-2014 |
20140255150 | CEILING FAN SYSTEM - A ceiling fan system that includes a motor/blade assembly that may include a motor, a main rotor attached to the motor, and a plurality of blades attached to the main rotor. A plurality of hoods may partially enclose the motor/blade assembly. The plurality of hoods may include an intake nozzle hood acting as an air inlet and an outlet surface hood with an aerodynamic surface. The profile of the hoods is designed so that the resulting flow from the blades produces a flow pattern controlled by the aerodynamic shape of the hoods. | 09-11-2014 |
20140271101 | MODULATED TURBINE VANE COOLING - A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity. | 09-18-2014 |
20140271102 | MODIFIED HEAT CHAMBER AND METHOD TO IMPROVE HEAT CYCLE EFFICIENCY USING AIRFLOW CONTROL - The present invention relates to improvements in the art of operating large heat chambers so as to reduce both the time and the cost required for heating materials. More specifically, the modified heat chamber of the present invention provides a programmable control mechanism capable of significantly reducing areas with temperature variations or hot and cold spots. A programmable heat chamber leads to significant reductions in the required processing time and in the cost of the required energy. | 09-18-2014 |
20140271103 | VANE CARRIER THERMAL MANAGEMENT ARRANGEMENT AND METHOD FOR CLEARANCE CONTROL - A thermal management arrangement ( | 09-18-2014 |
20140271104 | Turbine Shroud Cooling System - The present application provides a turbine shroud cooling system for a gas turbine engine. The turbine shroud cooling system may include a number of variable area cooling shrouds with tuning pins and a number of fixed area cooling shrouds with anti-rotation pins. The variable area cooling shrouds may include modulated cooling shrouds. The fixed area shrouds may include non-modulated shrouds. | 09-18-2014 |
20140271105 | TURBINE SHROUD SEGMENT SEALING - A segmented shroud ring surrounds a circumferential array of blades of a gas turbine engine rotor. The shroud ring has a plurality of shroud segments disposed circumferentially one adjacent to another. The circumferentially adjacent shroud segments have confronting sides defining an inter-segment gap therebetween. The inter-segment gaps are sealed by a sealing band mounted to the radially outer surface of the segmented shroud ring so as to extend across the inter-segment gaps around the full circumference of the shroud ring. Impingement jet holes may be defined in the sealing band for cooling the shroud segments. | 09-18-2014 |
20140271106 | Pump Testing for Predicting Lifetime and Wear Conditions - System and method for testing a pump. The testing of the pump includes determining a Mechanical Power Index (MPI) for the pump. The MPI is determined by operating the pump at operating speed for a minimum operating interval. When the pump is stopped under normal operation by the application, the pump speed is continuously monitored. The time when the pump speed decreases to an initial speed close to the operating speed is read as an initial time. When the pump speed decreases to a final pump speed close to the critical speed, the end time is read and the elapsed time is determined as Δt=end time−initial time. The MPI is calculated to be the initial pump speed minus the final pump speed divided by Δt. The MPI can be used during the lifetime of the pump to determine when the pump is deteriorating. | 09-18-2014 |
20140271107 | Systems and Methods for Preventing Damage to Pump Diffusers - Systems and methods for preventing diffusers in pumps such as electric submersible pumps from bursting or collapsing in over-pressure and/or under-pressure conditions, where one or more diffusers in the pump includes check valves in the exterior diffuser wall. The check valves remain closed when a pressure differential between the diffuser interior and exterior is within a predetermined range, but open when the pressure differential between the diffuser interior and the interstitial space is outside the predetermined range to relieve overpressure and underpressure conditions. When the pressure differential returns to an acceptable range, the check valves close, preventing recirculation of fluid between the diffusers of the different stages. O-rings or other types of seals may be installed between each stage and the pump housing to provide some isolation of the external pressure on the diffuser of each stage. | 09-18-2014 |
20140271108 | COMPRESSOR BLEED SELF-RECIRCULATING SYSTEM - A compressor for a gas turbine engine having a bleed air recirculation system includes a plurality of bleed holes extending through the shroud at a first axial location thereon substantially adjacent the blade tips. The bleed holes have a closed outer perimeter along their complete length. An annular bleed cavity surrounds the shroud and is in communication with outlet openings of the bleed holes. The bleed holes provide communication between said main gas flow passage and the bleed cavity. The bleed cavity includes exit passages having outlets disposed in said shroud at a second axial location which is upstream of both the first axial location and the leading edge of the blades of the rotor. Bleed air is passively bled from the main gas flow passage via the bleed holes, recirculated through the bleed cavity and re-injected back into the main gas flow passage at the second axial location. | 09-18-2014 |
20140271109 | AXIAL COMPRESSOR AND METHOD FOR CONTROLLING STAGE-TO-STAGE LEAKAGE THEREIN - The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may include a slot planar surface facing away from the rotor disk. The compressor also may include a compressor blade coupled to the rotor disk via the slot. The compressor blade may include a platform positioned over the radially outer surface of the rotor disk, and the platform may include a platform sealing edge facing toward the rotor disk. The compressor further may include a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low-pressure side of the compressor blade. The present application and the resultant patent further provide a related method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine. | 09-18-2014 |
20140271110 | COMPRESSOR START BLEED SYSTEM FOR A TURBINE SYSTEM AND METHOD OF CONTROLLING A COMPRESSOR START BLEED SYSTEM - A compressor start bleed system for a turbine system includes a compressor section. Also included is a turbine section disposed downstream of the compressor section. Further included is at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section. Yet further included is at least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system. | 09-18-2014 |
20140271111 | METHOD AND APPARATUS TO IMPROVE HEAT TRANSFER IN TURBINE SECTIONS OF GAS TURBINES - A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide. | 09-18-2014 |
20140271112 | LOW NOISE TURBINE FOR GEARED GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed. | 09-18-2014 |
20140271113 | MODULATED COOLING FLOW SCHEDULING FOR BOTH SFC IMPROVEMENT AND STALL MARGIN INCREASE - A turbine engine includes a compressor, and high and low pressure turbines. The configuration includes a mid-compression station which can be, in the case of a single compressor in the middle of that compressor, or at the exit of the first compressor in the case of two compressors. Also, there is an exit pressure station at the exit of the compression system. A first gas flow line is interposed between the mid-compression station of the compressor and the low pressure turbine, and a second gas flow line is interposed between the exit pressure station of the compression system and the high pressure turbine. A first valve is coupled to the first gas flow line and modulates a low pressure flow rate of coolant in the first gas flow line, and a second valve is coupled to the second gas flow line and modulates a high pressure flow rate of coolant in the second coolant flow line. A controller is configured to operate the first and second valves based on an operating condition of the turbine engine so as to improve the specific fuel consumption while ensuring acceptable stall margin. | 09-18-2014 |
20140271114 | Engine Health Monitoring and Power Allocation Control for a Turbine Engine Using Electric Generators - A control for a turbine engine using electrical machines monitors engine health and allocates power extraction between the electrical machines. | 09-18-2014 |
20140271115 | ADJUSTABLE TURBINE VANE COOLING - A turbine vane cooling system operably coupling a cooling fluid source to a turbine vane assembly is disclosed herein. A plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body is connected to the turbine vane assembly. An inlet can be operably connected to each turbine vane to form a fluid communication path between a cooling fluid source and an interior of the hollow body of each turbine vane. At least one outlet fluidly communicating with the interior of said hollow body can be formed in the vane. A regulating member can variably block a portion of an inlet of each of the turbine vanes in response to a temperature of each turbine vane. | 09-18-2014 |
20140271116 | HEAT EXCHANGER INTEGRATED WITH A GAS TURBINE ENGINE AND ADAPTIVE FLOW CONTROL - One embodiment of an engine may include an enclosure surrounding an engine having an engine centerline, and the enclosure defining a passage for a cold-side airflow. The engine may also include one or more contiguous heat exchangers having a cold side inlet surface receiving a cold-side airflow. The heat exchanger may be disposed within the passage, such that a surface normal relative to the cold side inlet surface is offset by at least 30 degrees from the engine centerline. | 09-18-2014 |
20140271117 | Lifing and Performance Optimization Limit Management for Turbine Engine - A control for a multi-shaft turbine engine system using electrical machines seeks optimal system performance while accommodating hard and soft component limits. To accommodate the component limits, the control may generate a number of possible operating point options reflecting potential trade-offs in performance, lifting, efficiency, or other objectives. | 09-18-2014 |
20140271118 | GAS TURBINE ENGINE LUBRICATION SYSTEM - A lubrication system for a gas turbine engine is disclosed. The lubrication system is configured to provide pressurized air and lubricant to a bearing sump of the gas turbine engine to cool and lubricate a bearing included in the bearing sump. | 09-18-2014 |
20140271119 | METHOD AND APPARATUS FOR CONTROLLING MODULATED COOLING OF A GAS TURBINE COMPONENT - A method of modulating the cooling of a gas turbine component is disclosed. The method includes determining a target component temperature at which the gas turbine component can be maintained without the gas turbine component experiencing a failure over the course of an indicated life of the gas turbine component; scheduling a cooling air value to the target component temperature; and determining one or more of a demanded cooling air temperature and a demanded cooling air mass flow rate based on the scheduled cooling air value. | 09-18-2014 |
20140271120 | DISK TURBINE USING HEAT PIPES - Disclosed is a steam turbine that utilizes heat pipes to remove heat from the surfaces of the disks of the steam turbine to provide greater efficiency and longer operational service of the steam turbine. | 09-18-2014 |
20140271121 | GAS TURBINE ENGINE ARCHITECTURE WITH INTERCOOLED TWIN CENTRIFUGAL COMPRESSOR - A gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path. | 09-18-2014 |
20140271122 | Rooster Tail Suppression Apparatus - A modifier may be used to prevent formation of a rooster tail when surface drive propellers are used with marine vessels. The modifier may be retractable by attaching it to the transom of the marine vessel or fixed-mounted by attaching it to the drive housing. The modifier changes the direction of the rooster tail so it flows substantially parallel to the surface of the water and hull of the marine vessel. | 09-18-2014 |
20140286745 | APPARATUS AND METHOD FOR ROTATING FLUID CONTROLLING VANES IN SMALL TURBINE ENGINES AND OTHER APPLICATIONS - Actuation systems and methods for varying the angle of small turbine engine inlet guide vanes (IGV) and/or compressor stator vanes (CSV). Such systems and methods may employ a piezoelectric inchworm actuator (or a piezo stack actuator or magnetostrictive actuator, depending upon actuation requirements) to actively modify the angle of attack of a single or a cascade of inlet guide vanes or compressor stator vanes. The change in angle of attack is necessary due to large variations in engine operating envelope including but not limited to air density, velocity, temperature, and the like. The present invention is especially suitable to actuate small inlet guide vanes and compressor stator vanes found in small turbine jet engines including but not limited to those under ten (10) inches in diameter. | 09-25-2014 |
20140286746 | COMPRESSOR SHROUD REVERSE BLEED HOLES - A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface. Bleed air removed from the annular gas flow passage flows through the bleed holes from the inlet to the outlet ends. The outlet end of each bleed hole is located circumferentially upstream of the inlet end relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor. | 09-25-2014 |
20140286747 | PUMP HAVING SELECTABLE OUTLETS - A liquid pump ( | 09-25-2014 |
20140294557 | Turbine Rotor Blade - A turbine rotor blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the blade and suppress degradation in performance even if cooling air mixes in toward the blade. The rotor blade is mounted to a rotor to form a turbine blade row rotating in a stationary member that includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is smaller on the downstream side than on the upstream side. | 10-02-2014 |
20140294558 | TURBOMACHINE FLUID DELIVERY MANIFOLD AND SYSTEM - An example turbomachine fluid delivery manifold provides a journal fluid path and a gear mesh fluid path that is separate from the journal fluid path. An example turbomachine lubrication system includes a geared architecture having a journal bearing and a gear. In this example, a manifold provides a portion of a first fluid path and a portion of a second fluid path separate from the first fluid path. The first fluid path is operative to communicate a first fluid from a fluid supply to the journal bearing. The second fluid path is operative to communicate a second fluid from the fluid supply to a gear mesh. | 10-02-2014 |
20140294559 | MULTIPLE MODE GAS TURBINE ENGINE GAS FUEL SYSTEM WITH INTEGRATED CONTROL - A method for operating a gas turbine engine is disclosed. The method includes determining whether the gas turbine engine fuel system is in a steady state mode or a transient mode. The method also includes modifying the gas turbine engine power output by modifying a pressure set point of the fuel system while maintaining a fuel control valve in a steady state when in the steady state mode. The method further includes modifying the gas turbine engine output by modifying the position of the fuel control valve while maintaining the pressure set point of the fuel system constant when in the transient mode. | 10-02-2014 |
20140294560 | Gas Turbine Shroud Assemblies - Embodiments of the present disclosure include a gas turbine shroud assembly. The shroud assembly may include a shroud structure that defines a first cooling chamber and a second cooling chamber. The shroud assembly may also include a first impingement plate disposed within the first cooling chamber and a second impingement plate disposed within the second cooling chamber. Further, the shroud assembly may include one or more cooling channels formed within the shroud structure. The cooling channels may be configured to connect the first cooling chamber with the second cooling chamber. The shroud assembly may also include a flow of cooling air in communication with the first cooling chamber. In this manner, the flow of cooling air may flow from the first cooling chamber to the second cooling chamber by way of the one or more cooling channels. | 10-02-2014 |
20140294561 | STEAM TURBINE GOVERNING SYSTEM FOR MAINTAINING SYNCHRONIZATION AND PROCESS FOR PERFORMING THE SAME - The invention relates to a steam turbine governing system for maintaining synchronization between an electrical grid and an electric generator, driven by a steam turbine, after the occurrence of a grid short circuit at the electrical grid. The governing system includes a governor adapted to control an arrangement of valves for regulating the steam flow in the steam turbine and means for measuring the voltage drop at the output of the electric generator. The governing system further includes means for measuring the electric power drop at the output of the electric generator. The governor is adapted to initiate operation of the arrangement of valves of the steam turbine in response to a voltage drop exceeding a predetermined value and to an electric power drop exceeding a predetermined value. | 10-02-2014 |
20140294562 | STRUT FOR A GAS TURBINE ENGINE - The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut. | 10-02-2014 |
20140294563 | CRYOGENIC LIQUID EXPANSION TURBINE - A cryogenic liquid expansion turbine has a turbine wheel mounted on a rotary shaft, at least one radial inlet for cryogenic liquid to be expanded in the expansion turbine for the rotary shaft, and a dry gas sealing means at a position along the rotary shaft between the turbine wheel and the bearings. There is a thermal barrier member between the turbine wheel and the dry gas sealing means, a gas chamber on the dry gas sealing means side of the thermal barrier member, and an internal passage for cryogenic gas to the said gas chamber. A method is also provided. | 10-02-2014 |
20140301820 | TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE - A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas turbine engine is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine. The turbine engine shutdown temperature control system may operate during the shutdown process where the rotor is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing to uniformly, from top to bottom, cool down. | 10-09-2014 |
20140301821 | SYSTEM AND METHOD OF CONTROLLING WRAPPING FLOW IN A FLUID WORKING APPARATUS - A fluid working apparatus ( | 10-09-2014 |
20140301822 | FLUID PUMP WITH A ROTOR - The invention relates to a fluid pump, in particular to a liquid pump having a rotor with at last one rotor blade for conveying the fluid, the rotor being variable with respect to its diameter between a first, compressed state and a second expanded state. In order to produce a simple compressibility and expandability of the rotor of the pump, it is provided according to the invention that at least one rotor blade is deformable between a first state which it assumes in the compressed state of the rotor and a second state which it assumes in the expanded state of the rotor by means of a fluid counterpressure during a rotation of the rotor during pump operation. | 10-09-2014 |
20140301823 | HYDRAULIC MACHINE HAVING AN INTAKE MANIFOLD LOCATED AT THE TOP - The invention relates to a hydraulic machine having turbines or a pump turbine, comprising an impeller that is mounted such as to be rotatable about a vertical axis of rotation and has a plurality of blades, an inlet spiral that surrounds the impeller in an annular manner and has a circular outlet opening on the inner circumferential ring thereof, a distributor and/or closure device for adjusting the inflow into the impeller, and an intake manifold for guiding of the water flowing out of the impeller. The intake manifold is arranged above the impeller. At least a bypass pipe can be provided for bypassing the distributor and/or closure device, which bypass pipe connects the inlet spiral directly to the impeller when a bypass valve arranged in the run of said bypass pipe is opened. Furthermore, at least one drainage pipe can be provided for draining the impeller, which drainage pipe connects the impeller directly to a pump sump when a drainage valve arranged in the nm of said drainage pipe is opened. The invention also relates to a method for filling and draining such a machine, and to the preferred use thereof. | 10-09-2014 |
20140308110 | ADJUSTABLE COMPRESSOR TRIM - An assembly can include a compressor housing, an adjustable wall disposed within the compressor housing that defines an air inlet to an inducer portion of a compressor wheel, and an adjustment mechanism to adjust the wall and thereby adjust at least a diameter of the air inlet. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 10-16-2014 |
20140314540 | GAS TURBINE ENGINE SYNCHRONIZATION RING - A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the synchronization ring for engaging a case on the gas turbine engine. | 10-23-2014 |
20140314541 | TURBOMACHINE THRUST BALANCING SYSTEM - An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine. | 10-23-2014 |
20140314542 | GAS TURBINE ENGINE EXHAUST DIFFUSER WITH MOVABLE STRUTS - An exhaust diffuser for a gas turbine engine gas turbine engine includes a multiple of circumferentially spaced struts that extend between an inner gaspath wall and an outer gaspath wall, at least one of the multiple of circumferentially spaced struts movable about a strut axis. | 10-23-2014 |
20140314543 | COMPRESSOR SYSTEM AND METHOD OF CONTROLLING THE SAME - Provided is a compressor system including: a guide vane; a compressor compressing a fluid flowing from the guide vane; a drive unit connected to the compressor and driving the compressor; a guide flow path connecting the compressor and an external device; a branch flow path branching off from the guide flow path; a flow control valve opening and closing the branch flow path; a sensor unit measuring a current of the drive unit and a pressure of the guide flow path; and a control unit controlling at least one of the guide vane, the drive unit, and the flow control valve, calculating an operation point of the compressor, comparing the operation point of the compressor with a greater one of a first anti-surge control line and a second anti-surge control line and controlling the flow control valve according to the comparison. | 10-23-2014 |
20140314544 | DEVICES AND METHODS FOR REDUCING NOISE IN A BLOWER HOUSING - Devices and methods for reducing noise of a blower reduce and/or substantially block the exchange of gas within the blower housing from an area of a generally high-velocity flow of gas to an area of a comparatively lower-velocity flow of gas, for example near the outlet of the blower housing. | 10-23-2014 |
20140321961 | MATE FACE COOLING HOLES FOR GAS TURBINE ENGINE COMPONENT - A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage. | 10-30-2014 |
20140321962 | Turbine Nozzle for Air Cycle Machine - A nozzle for use in an air cycle machine has a plate. A plurality of vanes extend away from the plate. The plurality of vanes extend for a height away from the plate. A width is defined as the closest distance between two adjacent vanes. A ratio of the height to the width is between 3.253 and 3.800. An air cycle machine and a method of repair are also disclosed. | 10-30-2014 |
20140321963 | Turbine Nozzle and Shroud for Air Cycle Machine - A nozzle and shroud for use in an air cycle machine has a plate and a shroud curving in a first axial direction about a center axis of the shroud relative to the plate. A plurality of vanes extends in a second axial direction away from the plate. The plurality of vanes extends for a height away from the plate and a width defined as the closest distance between two adjacent vanes, with a ratio of the height to the width being between 1.3653 and 1.7992. An air cycle machine and a method of repair are also disclosed. | 10-30-2014 |
20140321964 | Turbine Nozzle and Shroud for Air Cycle Machine - A nozzle and shroud for use in an air cycle machine has a plate and a shroud curving in a first axial direction about a center axis of the shroud relative to the plate. A plurality of vanes extends in a second axial direction away from the plate. The plurality of vanes extends for a height away from the plate and a width defined as the closest distance between two adjacent vanes, with a ratio of the height to the width being between 0.1091 and 0.1401. An air cycle machine and a method of repair are also disclosed. | 10-30-2014 |
20140321965 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. | 10-30-2014 |
20140321966 | PACKAGED VACUUM PUMP AND OIL PUMP, AND SYSTEM AND METHOD THEREOF - A packaged vacuum pump and oil pump for use in a vehicle generally includes an oil pump module and a vacuum pump module. The oil pump module is configured to circulate oil, and is fitted to a first drive shaft configured to transmit torque to the oil pump module. The vacuum pump module is configured to generate a vacuum, and is fitted to a second drive shaft configured to transmit torque to the vacuum pump module. The packaged vacuum pump and oil pump also includes a clutch. The clutch connects the first drive shaft and the second drive shaft, and is configured to transfer torque from the first drive shaft to the second drive shaft when the clutch is engaged. The clutch may be a hydraulic clutch configured to receive a pressurized fluid, which may be oil received from the oil pump module, to engage the clutch. | 10-30-2014 |
20140321967 | Gas Turbine Power Augmentation System - The present application provides a power augmentation system for use with a gas turbine engine. The power augmentation system may include a compressor discharge manifold, an inlet bleed heat system in communication with the compressor discharge manifold via an inlet bleed heat line, and an auxiliary compressor in communication with the compressor discharge manifold via the inlet bleed heat line. | 10-30-2014 |
20140321968 | BLADE ROTARY ASSEMBLY WITH AERODYNAMIC OUTER TOROID SPOILER FOR A SHROUDED PROPULSION ROTARY ASSEMBLY - An inside vessel arrangement ( | 10-30-2014 |
20140321969 | SLIDE RING SEAL - A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall ( | 10-30-2014 |
20140321970 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section. | 10-30-2014 |
20140321971 | INTERNALLY-COOLED CENTRIFUGAL COMPRESSOR WITH COOLING JACKET FORMED IN THE DIAPHRAGM - An internally-cooled centrifugal compressor having a shaped casing and a diaphragm disposed within the shaped casing having a gas side and a coolant side so that heat from a gas flowing through the gas side is extracted via the coolant side. An impeller disposed within the diaphragm has a stage inlet on one side and a stage outlet for delivering a pressurized gas to a downstream connection. The coolant side of the diaphragm includes at least one passageway for directing a coolant in a substantially counter-flow direction from the flow of gas through the gas side. | 10-30-2014 |
20140321972 | DRY GAS SEAL FOR SUPERCRITICAL CO2 PUMP-HIGH PRESSURE BUFFER - Systems and methods for assuring a safe working condition of a dry gas seal when a pump/compressor is in a standstill condition. A small booster compressor is added to boost the pressure of an intermediate buffer gas injected into the chamber between a primary seal and a secondary seal of the dry gas seal. Control components detect when the barrier gas pressure drops below a preconfigured value and when detected, closes a valve in a line to a flare safe area and turns on the compressor. The boosted intermediate buffer gas, Nitrogen or dry air, slows the flow of untreated process gas through the primary seal of the dry gas seal and prevents icing of the primary seal. | 10-30-2014 |
20140321973 | HYDROELECTRIC TURBINE SYSTEM - The present invention provides a hydroelectric turbine system comprising a base mounted turbine for location on the seabed or the like, in order to generate electricity from the tidal flow of water through the turbine, the system incorporating a load bank, for example in the form of an array of resistive windings, to which the turbine can be selectively electrically connected in order to dissipate the electrical power as heat into the passing water. | 10-30-2014 |
20140328664 | SINGLE CIRCUIT DOUBLE-ACTING PUMP - Removing water from a subterranean formation entails pumping hydraulic oil from a surface-located hydraulic oil pump through a hydraulic oil line to a downhole water pump piston to drive it in a first direction to pump water through a downhole water line to a water chamber of a hydraulic accumulator at the surface. A piston separates the water chamber and an oil chamber and moves to compress the hydraulic oil in the oil chamber of the hydraulic accumulator. The hydraulic oil pump may then pump hydraulic oil into the oil chamber causing the piston to move toward the water chamber, thereby moving water in the downhole water line and resetting the piston in the downhole water pump. A water valve in the downhole water line at the surface may open and release water when the piston in the downhole water pump reaches a predetermined or reset position. | 11-06-2014 |
20140328665 | WASTEGATE CONTROL TO REDUCE CHARGE AIR COOLER CONDENSATE - Methods and systems are provided for adjusting a wastegate in response to condensate forming conditions in a charge air cooler (CAC). In one example, a wastegate may be opened in response to an induction pressure greater than a threshold pressure when the induction pressure is greater than required to produce a manifold pressure required for a torque demand. Further, a compressor recirculation valve may be opened to further reduce the induction pressure during certain driving conditions. | 11-06-2014 |
20140328666 | Bezentropic Bladeless Turbine - A bezentropic bladeless turbine has a bladeless rotor, a bladeless stator, and a CD nozzle that feeds a rectified molecular, supersonic flow of gas and/or steam into the rotor. Spiral channels are provided in the rotor, which serve to maintain and sustain the rectified molecular flow of the working fluid through the rotor. An energy booster device is assembled at the exit of the CD nozzle, to increase the efficiency of the CD nozzle. The rotor is attached to an output shaft, to convert the kinetic energy of the working fluid to mechanical work. Various fluids, such as steam, Freon, wind, may be used as the working fluid. | 11-06-2014 |
20140328667 | VARIABLE GEOMETRY DIFFUSER HAVING EXTENDED TRAVEL AND CONTROL METHOD THEREOF - An improved variable geometry diffuser (VGD) mechanism for use with a centrifugal compressor. This VGD mechanism extends substantially completely into the diffuser gap so that the VGD mechanism may be used more fully to control other operational functions. The VGD mechanism may be used to minimize compressor backspin and associated transient loads during compressor shut down by preventing a reverse flow of refrigerant gas through the diffuser gap during compressor shutdown, which is prevented because the diffuser gap is substantially blocked by the full extension of the diffuser ring. During start-up, transient surge and stall also can be effectively eliminated as gas flow through the diffuser gap can be impeded as load and impeller speed increase, thereby alleviating the problems caused by startup loads at low speeds. The VGD mechanism can be used for capacity control as well so as to achieve more effective turndown at low loads. | 11-06-2014 |
20140334911 | METHOD FOR OPERATING A MULTISTAGE COMPRESSOR - A method for operating a multistage compressor is provided. The method includes monitoring the pump limit, wherein at least a first measurement parameter measured during operation is compared to a reference parameter. The reference parameter is characteristic of reaching the surge limit or a specific distance of the operating point from the surge limit. A multistage compressor is also provided. In order to enlarge the operating range without risking safety, it is proposed that each stage to be monitored individually for the onset of the surge. | 11-13-2014 |
20140341702 | FLOW SLEEVE FOR THERMAL CONTROL OF A DOUBLE-WALL TURBINE SHELL AND RELATED METHOD - A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell. | 11-20-2014 |
20140341703 | METHOD AND SYSTEM FOR OPERATING AN ENGINE TURBOCHARGER WASTE GATE - A system and method for operating an engine turbocharger is described. In one example, the turbocharger includes an electrically actuated waste gate. A controller adjusts a position of the electrically actuated waste gate. | 11-20-2014 |
20140341704 | HEAT EXCHANGE ARRANGEMENT - A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid. The arrangement further includes a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion. The arrangement includes divert valve in the first conduit which diverts flow to the second conduit as the flow in the second conduit is moderated to reduce thermal shock in the heat exchange portion. | 11-20-2014 |
20140341705 | ADJUSTABLE SIDE LINER FOR A PUMP - An adjustment assembly for pump casing of a pump, the pump casing including a main part and a side part having a main axis and a side wall section extending laterally with respect to the main axis. The adjustment assembly is operable to cause relative displacement between the side part and the main part of the pump casing. The adjustment assembly includes a drive device and an actuator which can be activated externally of the pump, the drive device being operable to cause the relative displacement of the side part in response to activation of said actuator, the relative displacement capable of being a combination of axial and rotational movement. | 11-20-2014 |
20140341706 | SUPERSONIC COMPRESOR - A supersonic compressor provided may include an axial inlet and a centrifugal impeller fluidly coupled to the axial inlet. The centrifugal impeller may have a periphery and may be configured to impart energy to process fluid received via the axial inlet and discharge the process fluid from the periphery in at least a partially radial direction. The supersonic compressor may further include a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive the process fluid from the centrifugal impeller and convert the energy imparted. The static diffuser may include a plurality of diffuser vanes defining diffuser passageways therebetween. A supersonic ramp may be formed at an end of the at least one diffuser vane proximate the periphery of the centrifugal impeller. The supersonic ramp may be configured to generate a shock wave from the process fluid. | 11-20-2014 |
20140341707 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine. | 11-20-2014 |
20140341708 | VALVE FOR GAS TURBINE ENGINE - A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source. The port cover extends circumferentially around the gas turbine engine and can include a portion that is anchored and an opposite portion coupled to an actuator. Movement of the actuator causes the port cover to open and close the port. Biasing members can be used to urge the port cover into one of an open and closed position against the movement of the actuator. | 11-20-2014 |
20140348629 | TURBOMACHINE ASSEMBLY AND METHOD OF USING SAME - A turbomachine assembly generally has a compressor section including a first end of a rotating member and a first cover configured to substantially enclose the first end therein. The compressor section includes a bypass valve coupled to the first cover portion and configured to control fluid flow within the compressor section to enable controlling at least one operating parameter of the compressor section. A turbine section is arranged in flow communication with the compressor section. The turbine section includes a second end of the rotating member and a second cover configured to substantially enclose the second end therein. At least one regulating valve that is in flow communication with the compressor section and the turbine section, wherein the regulating valve is configured to control fluid flow between the compressor and turbine sections to enable controlling at least one operating parameter of the turbine section. | 11-27-2014 |
20140348630 | NOISE REDUCING VANE - A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure. | 11-27-2014 |
20140348631 | TURBOMACHINE STAGE AND METHOD FOR DETERMINING A SEAL GAP AND/OR AN AXIAL POSITION OF SUCH A TURBOMACHINE STAGE - A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange. | 11-27-2014 |
20140348632 | TURBOMACHINE STAGE AND METHOD FOR DETECTING A SEALING GAP OF SUCH A TURBOMACHINE STAGE - A turbomachine stage, in particular a turbine stage or compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, in particular conical, housing in which a rotor blade arrangement having a plurality of rotor blades is disposed which have an outer shroud having at least one radial sealing flange. The sealing flange has a recess arrangement having at least one radial recess in which a radial projection is disposed, in particular centrally. A sensor arrangement having at least one capacitive sensor for detecting a radial distance from a circumferential surface of the sealing flange is disposed on the housing. | 11-27-2014 |
20140348633 | TURBINE STAGE WITH A BLOW-OUT ARRANGEMENT AND METHOD FOR BLOWING OUT A SEALING GAS FLOW - A turbine stage having a gas channel in which at least one rotor assembly is disposed, is disclosed. A cavity communicates with the gas channel and is delimited by a front side of a rotor element and by a rotor element-mounted seal. A blow-out arrangement with at least one gas passage for blowing out a sealing gas flow into the cavity is provided, where the gas passage for blowing out the sealing gas flow is configured with a swirl in the circumferential direction and has an outlet opening that is offset radially outwardly from the rotor element-mounted seal. | 11-27-2014 |
20140356122 | SYSTEM AND METHOD FOR CONTROLLING ICE FORMATION ON GAS TURBINE INLET GUIDE VANES - Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency. | 12-04-2014 |
20140356123 | CENTRIFUGAL COMPRESSOR HAVING LUBRICANT DISTRIBUTION SYSTEM - Embodiments of the present disclosure are directed towards a bearing of a rotor assembly having a first lubricant flow path configured to flow a first lubricant flow to a first bearing surface of the rotor assembly and a second lubricant flow path separate from the first lubricant flow path and configured to flow a second lubricant flow to a second bearing surface of the rotor assembly. | 12-04-2014 |
20140356124 | AIR COMPRESSOR BACKING PLATE - A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.25% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included. | 12-04-2014 |
20140356125 | GAS TURBINE ENGINE HEAT EXCHANGER SYSTEM - An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid. | 12-04-2014 |
20140356126 | METHOD AND SYSTEM FOR SYNCHRONOUSLY INHIBITING SUBCRITICAL VIBRATIONS OF MAGNETIC LEVITATION MOLECULAR PUMP ROTOR - It is provided in the present invention a method for synchronously inhibiting subcritical vibrations of magnetic levitation molecular pump rotor, by means of synchronously sampling signals of subcritical vibrations of the rotor generated after the rotor of the magnetic levitation molecular pump touches down so as to obtain the amplitude and the phase of subcritical vibrations of the rotor, based on which outputting a compensation force for inhibiting subcritical vibrations of the rotor. Through using the present method, it is achieved of accurate synchronous for signals of subcritical vibrations and fast inhibition for subcritical vibrations of the rotor. | 12-04-2014 |
20140356127 | METHOD AND PUMP FOR PUMPING HIGHLY VISCOUS FLUIDS | 12-04-2014 |
20140356128 | METHOD AND DEVICE FOR STABILIZING A COMPRESSOR CURRENT - The present invention relates to a method for providing a fluid flow to a compressor system of a first turbo machine, wherein the compressor system includes at least one compressor housing in which at least one impeller is arranged and through which a compressor flow flows. The method includes feeding a primary fluid flow to a mixing region of the compressor system. The method further includes feeding a secondary fluid flow from an outside region of the compressor housing to the mixing region so that the secondary fluid flow mixes at least in part with the primary fluid flow to form a resulting fluid flow so that between the primary fluid flow and the secondary fluid flow a momentum exchange takes place, and so that the secondary fluid flow is promoted by the primary fluid flow. The method further includes feeding the resulting fluid flow to the compressor flow upstream of the impeller in the direction of the impeller. | 12-04-2014 |
20140356129 | FLUIDICS MODULE, DEVICE AND METHOD FOR PUMPING A LIQUID - A fluidics module rotatable about a rotational center includes first and second chambers and a compression chamber. First and second fluid channels are provided between the first and second chambers and the compression chamber, respectively. The flow resistance of the second fluid channel is smaller, for a flow of liquid from the compression chamber to the second chamber, than a flow resistance of the first fluid channel for a flow of liquid from the compression chamber to the first chamber. Upon rotation at a high rotational frequency, liquid is initially introduced from the first chamber into the compression chamber via the first fluid channel, so that a compressible medium is compressed within the compression chamber. Subsequently, the rotational frequency is reduced, so that the compressible medium within the compression chamber will expand and so that, thereby, liquid is driven into the second chamber via the second fluid channel. | 12-04-2014 |
20140363268 | METHOD AND TURBINE FOR EXPANDING AN ORGANIC OPERATING FLUID IN A RANKINE CYCLE - It is described a method and a turbine for expanding an organic operating fluid in a Rankine cycle, the method comprising the step of feeding the operating fluid to a turbine provided with a plurality of arrays of stator blades (S | 12-11-2014 |
20140363269 | COMPRESSOR CONTROL DEVICE AND CONTROL METHOD THEREFOR, AND COMPRESSOR SYSTEM - A compressor control device includes an inlet guide vane opening degree control unit configured to control an opening degree of an inlet guide vane. The inlet guide vane opening degree control unit includes an inlet guide vane opening degree command value calculation unit configured to calculate an inlet guide vane opening degree command value based on an outlet pressure detection value and a plurality of inlet guide vane opening degree correction units each configured to correct the inlet guide vane opening degree command value based on the post-merger pressure detection value and a corresponding inlet flow rate detection value for each of a plurality of upstream-most compressor bodies. | 12-11-2014 |
20140369803 | VARIABLE DISCHARGE COMPRESSOR CONTROL - Embodiments are disclosed that relate to controlling a compressor. In one example, method of controlling a compressor comprises regulating a discharge capacity of the compressor via a control current supplied to a control device, holding the control current supplied to the control device at substantially zero amperes for a first duration, and stepping the control current from substantially zero amperes to a sustainable current that provides a sustainable level of a performance parameter of the compressor. | 12-18-2014 |
20140369804 | VARIABLE BLEED SLOT IN CENTRIFUGAL IMPELLER - The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot. | 12-18-2014 |
20140369805 | AIR CONDITIONER AND CONTROL METHOD THEREOF - An air conditioner for determining whether a human body exists in a sensing region using a plurality of heat sensors, as human body-detecting sensors, installed in the air conditioner and arranged at regular intervals. The air conditioner recognizing, when a human body has been detected, angles formed between the human body-detecting sensors and the human body, and calculating a distance from the human body-detecting sensors to the human body based on the recognized angles and a distance between the human body-detecting sensors, and adjusting a direction and speed of wind according to the calculated distance to the human body, and a control method of the air conditioner. Also, the air conditioner may be used as a security sensor when it does not operate. | 12-18-2014 |
20140369806 | PNEUMATIC COMPRESSOR RECIRCULATION VALVE SYSTEM FOR MINIMIZING SURGE UNDER BOOST DURING THROTTLE CLOSING - An engine system having a compressor coupled to an engine and supplying air to an intake manifold, a throttle controlling the supply of air from the compressor to the intake manifold, a compressor recirculation valve (CRV) having a pneumatic control chamber, and a throttle aspirator having its motive section in fluid communication with an inlet of the throttle and its discharge section in fluid communication with an outlet of the throttle and its suction port in fluid communication with the pneumatic control chamber of the CRV. Such an engine system automatically minimizes surge during boost without a control system activating the CRV. Here, the CRV operates purely on the changes in pressure within the system forming a loop that resets itself. In another embodiment, a gate valve and a vacuum canister may be included rather than having the throttle aspirator directly connected to the CRV's pneumatic control chamber. | 12-18-2014 |
20140377051 | TURBOCHARGER - Systems and methods are disclosed for a turbocharger compressor, the system comprising: an actuatable annular disk comprising choke slots therein; an outer annular disk comprising choke slots therein; and an actuator to rotate the actuatable annular disk relative to the outer annular disk to vary alignment of the choke slots of the actuatable annular disk and the outer annular disk. The actuator may be controlled by an engine controller responsive to operating conditions of the compressor and actuated to align choke slots. Alignment of the choke slots allows air to be drawn into the impeller effectively expanding the compressor flow capacity to prevent compressor choke. | 12-25-2014 |
20150010382 | TURBINE FLOW MODULATION FOR PART LOAD PERFORMANCE - Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation. | 01-08-2015 |
20150010383 | CENTRIFUGAL COMPRESSOR DIFFUSER CONTROL - A centrifugal refrigerant compressor system includes an impeller connected to a shaft. A diffuser is arranged on a downstream side of the impeller and is configured to regulate refrigerant flow exiting the impeller. A magnetic bearing supports the shaft. A sensing element is configured to produce an output relating to a shaft condition. A controller is configured to receive the output and determine an undesired impeller operating condition based upon the shaft condition. The controller is configured to command the diffuser to a desired state in response to the undesired impeller operating condition. | 01-08-2015 |
20150016944 | COOLED GAS TURBINE ENGINE COMPONENT - A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn. | 01-15-2015 |
20150016945 | LINER FOR GAS TURBINE ENGINE - An embodiment of a gas turbine engine having a liner and casing is disclosed. The liner is disposed between the casing and a rotatable turbomachinery component. In one form, the rotatable turbomachinery component is a turbofan engine. The liner can be thin relative to a distance between the liner and the casing. Protrusions can be used between the liner and the casing. The protrusions can be a rib and can extend from the casing or the liner. An insert, such as an abradable surface, can be used with the liner. A filler can be used in the space between the liner and the casing. | 01-15-2015 |
20150016946 | BLADE CLEARANCE CONTROL FOR GAS TURBINE ENGINE - An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud. | 01-15-2015 |
20150016947 | AUGMENTED COOLING SYSTEM - An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component. | 01-15-2015 |
20150016948 | LINEAR PUMP CONTROL - A demand-based load balancing function may be provided by one or more drive controllers that takes advantage of the affinity laws to linearize the control of the variable of interest (e.g., flow, pressure, etc.). Each drive controller may be set up by the user simply inputting a few values into the drive controller. Based on the inputs, the drive controllers may interpolate control points using an assumed linear relationship between the variable to be controlled (e.g., pressure) and the current driven to the pump. Feedback data from the system may be used to continually update the drive controllers so as to potentially allow them to better balance power usage to each pump. | 01-15-2015 |
20150016949 | TIP CLEARANCE CONTROL METHOD - A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run. The method further comprises measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run. The thermal condition of at least part of the engine in accordance with the measured performance parameters is then recorded. Finally the recorded thermal condition is retrieved and the temperature of the casing is controlled during at least part of the second run in a manner dependent on it. | 01-15-2015 |
20150016950 | DEVICE AND METHOD FOR DISCHARGING SEALING AIR IN A TURBOFAN ENGINE - A device and method for discharging sealing air in a turbofan engine includes a primary flow duct that extends through a core engine of the turbofan engine and a bypass duct. The device has at least one bearing chamber sealed by sealing air of the turbofan engine, said bearing chamber surrounding at least one oil-lubricated bearing element for mounting a mechanical component of the turbofan engine. At least one discharge path for escaping sealing air is provided, which extends up to the bypass duct of the turbofan engine. | 01-15-2015 |
20150016951 | PLANT AND METHOD FOR DAMPING ACOUSTIC VIBRATIONS IN A CORRESPONDING PLANT - A facility, in particular a power plant, is provided having a steam turbine and a bypass station for diverting a working medium, as required, for the steam turbine around the steam turbine, wherein at least one resonance absorber is provided for the bypass station. | 01-15-2015 |
20150016952 | GAS PRESSURE REDUCTION GENERATOR - Gas Pressure Reduction Generator (GPRG) systems and methods for implementing a GPRG system are provided, where the GPRG systems comprise a gas inlet configured to receive a pressurized gas flow, at least one expander in gas flow receiving communication with the gas inlet wherein the expander is operable to convert the pressurized gas flow into mechanical energy and a depressurized gas flow, and a generator configured to convert the mechanical energy into electrical energy. | 01-15-2015 |
20150016953 | TANK DAMPENING DEVICE - A compressor assembly that has a compressed air tank having a vibration absorption member. The vibration absorption member can exert a pressure on a portion of the compressed air tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which applies a force against the compressed gas tank. Controlling the sound level of the compressed gas tank is accomplished by absorbing vibration from the compressed gas tank by which exerting a pressure on a portion of the compressed gas tank. | 01-15-2015 |
20150016954 | BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT - An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member. | 01-15-2015 |
20150023776 | FLUID COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE AND METHOD - A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut. | 01-22-2015 |
20150023777 | Systems and Methods for Directing a Flow Within a Shroud Cavity of a Compressor - A compressor is disclosed herein. The compressor may include a shroud cavity. The compressor also may include a flow directing device positioned within the shroud cavity. The flow directing device may be configured to direct a flow within the shroud cavity. | 01-22-2015 |
20150030428 | METHOD FOR ENHANCING POWER OF A GAS TURBINE ENGINE - A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module. The method includes increasing an operating range of each inlet guide vane to at least 62 degrees. The method also includes modifying a total flow area of the third stage power turbine nozzle by 2% to 12%, the total flow area including flow areas between adjacent airfoils in the third stage power turbine nozzle. | 01-29-2015 |
20150030429 | WASTE PUMP - The invention is a device which uses stored pressure to pump waste and a corresponding method of use. Waste is stored in a first chamber and the chamber is subsequently sealed by a valve and pressurised prior to a second valve opening. The pressurised waste is thereby ejected from the pressure chamber down an outlet pipe. | 01-29-2015 |
20150030430 | WATER TURBINE - This invention is relates to water turbine power. In particular, the invention relates to a water turbine for generating power in a body of water. There is provided a turbine for operation in a body of water for the generation of power, the turbine comprising: (a) a housing having an inlet for receiving water and an outlet for allowing water to exit; and (b) a power generation unit disposed in the housing and intermediate the inlet and outlet, the power generation unit comprising two propellers for rotation about an axis in response to water flow, wherein the inlet comprises a flared outer end for channelling the water towards the power generation unit, and a truncated cone disposed within the flared outer end of the inlet, the flared portion of the truncated cone protrudes the inlet. | 01-29-2015 |
20150030431 | BLADE RING FOR AN AXIAL TURBOMACHINE, AND A METHOD FOR ADJUSTING THE MAXIMUM FLOW RATE OF SAID BLADE RING - A blade ring for an axial turbomachine is provided, having an outer surface that is arranged on an outer ring and faces radially inwards, and an inner surface that is arranged on an inner ring and faces radially outwards, the surfaces being arranged concentrically and parallel to one another and delimiting an annular flow channel that tapers in the main flow direction of the axial turbomachine, as well as at least one adjustment blade that is arranged so as to be displaceable, in the flow channel, parallel to a surface line of one of the surfaces by a guiding device, and that is able to be fixed, in a predetermined position, to at least one of the rings. | 01-29-2015 |
20150037133 | SYSTEM AND METHOD RELATING TO AXIAL POSITIONING TURBINE CASINGS AND BLADE TIP CLEARANCE IN GAS TURBINE ENGINES - A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means. | 02-05-2015 |
20150037134 | Method for Producing Mechanical Energy, Single-Flow Turbine and Double-Flow Turbine, and Turbo-Jet Apparatus Therefor - The invention relates to mechanical engineering, in particular to air-driven, gas-driven and steam-driven turbines having increased power generation efficiency and reduced weight and dimensions. The invention can be used in electrical power generators, propulsion systems, refrigeration compressors, heat pumps, turbo-jet apparatuses and the like. | 02-05-2015 |
20150037135 | ACOUSTIC LINER - A gas turbine engine ( | 02-05-2015 |
20150044015 | Side Channel Liquid Ring Pump and Impeller for Side Channel Liquid Ring Pump - A liquid ring pump is provided. The liquid ring pump is designed to reduce the overall envelop of the ring pump. The liquid ring pump includes a housing and an impeller. The housing defines an impeller cavity. The impeller cavity has an inlet port and a discharge port. The impeller is positioned within the impeller cavity for rotation about a central rotational axis. The impeller includes a central hub defining a conical outer surface and a plurality of angularly spaced apart main vanes extending radially outward from the conical outer surface relative to the central rotational axis. The inlet and discharge ports may be located on a same side of the impeller housing. | 02-12-2015 |
20150044016 | Fuel System With Liquid Ring Pump With Centrifugal Air/Fuel Separator - A fuel system incorporating a boost pump unit, a boost pump unit and method of pumping fuel are provided. The fuel system and boost pump unit are preferably self-priming and do not utilize an airframe mounted pump for supplying fuel for an aircraft combustor. The boost pump unit includes a liquid ring pump and an air/fuel separator. The air/fuel separator has an inlet and first and second outlet ports. The inlet is operably fluidly coupled to an outlet of the liquid ring pump. The air/fuel separator has an arcuate flow path. The first outlet port is in fluid communication with a radially outer portion of the arcuate flow path and the second outlet port is in fluid communication with a radially inner portion of the arcuate flow path. A return line connected to the first outlet port is configured to return fuel to the liquid ring pump. | 02-12-2015 |
20150044017 | TURBOMACHINE AIRFOIL POSITIONING - Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine. | 02-12-2015 |
20150044018 | ACTIVE SEAL SYSTEM - One embodiment of the present disclosure is a unique active seal system. Another embodiment is another unique active seal system. Another embodiment is a unique method for operating a turbomachine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for active seal systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 02-12-2015 |
20150044019 | COMPRESSOR - A compressor may include a crankshaft, a lower bearing, an oil sump, an oil pump and a pressure equilibrium tube. The crankshaft may include an oil supply passage formed therethrough. The lower bearing may rotatably support a lower part of the crankshaft. The oil sump may be disposed proximate the lower part of the crankshaft. The oil pump may include an inlet, an outlet, an intake chamber and a discharging chamber. The inlet may be positioned below a level of oil in the oil sump and in fluid communication with the intake chamber. The discharging chamber may be in fluid communication with the oil supply passage at the lower part of the crankshaft through the outlet. The pressure equilibrium tube provides fluid communication between a space above the level of oil in the oil sump and the intake chamber. | 02-12-2015 |
20150044020 | METHOD FOR AVOIDING PUMP SURGES IN A COMPRESSOR - A method for avoiding pump surges in a compressor is provided, wherein a plurality of parameters of the compressor are monitored during operation and a desired value range for the plurality of parameters is predetermined, wherein a reaction that counteracts the pump surge is triggered if a number of parameters from the desired value range are exceeded or fallen below. The method also reliably prevents pumping of the compressor during a comparatively high running performance. For this purpose, the plurality of parameters has a parameter assigned to the rotational noise of the compressor. | 02-12-2015 |
20150044021 | TURBINE SYSTEM WITH THREE TURBINES COUPLED TO A CENTRAL GEARBOX AND METHOD FOR OPERATING A WORK MACHINE - A turbine system and a method for operating a work machine are provided herein. The turbine system including: a first, a second, and a third turbine, a central gearbox mechanically coupled on the input side to the three turbines and having a mechanical connection on the output side for connecting a work machine, a first fluid line for conveying a working fluid from the first turbine to the second turbine, a second fluid line for conveying the working fluid from the second turbine to the third turbine, a first connecting unit designed such that a first partial mass flow of the working fluid can be removed from the first fluid line or supplied to the first fluid line, and a second connecting unit designed such that a second partial mass flow of the working fluid can be removed from the second fluid line or supplied to the second fluid line. | 02-12-2015 |
20150044022 | METHOD AND DEVICE FOR CONTROLLING A HOT RESTART OF A CENTRIFUGAL COMPRESSOR - Methods, devices and systems capable of performing a hot restart of a compressor driven by a turbine are provided. The turbine has a high speed shaft and a low speed shaft connected to the compressor. A base slow roll speed at which a speed of the low speed shaft is in a slow roll range is maintained at the high speed shaft for a predetermined time. Then, when a vibration amplitude of the compressor is larger than a vibration limit, the maintaining is repeated. Otherwise, a set speed of the high speed shaft is increased, until a current speed of the low speed shaft reaches a minimum operating speed. If, while increasing the set speed, the vibration amplitude becomes larger than the vibration limit, the maintaining is repeated. | 02-12-2015 |
20150050120 | FAN SPEED AND MEMORY REGULATOR CONTROL BASED ON MEMORY MARGIN - Methods and systems for fan speed control based on memory margin are disclosed. According to an aspect, a method includes determining an operating margin of a memory interface. The method also includes determining whether the operating margin of the memory interface meets a predetermined condition. Further, the method includes controlling a speed of a computing system cooling fan based on the operating margin in response to determining the operating margin meets the predetermined condition. | 02-19-2015 |
20150050121 | FAN CONTROL SYSTEM AND METHOD FOR CONTROLLING FAN SPEED - A fan control system for processor is provided. The system has: a fan, configured to cool the processor; a power measurement module, coupled between the processor and a power supply of the processor, configured to measure the power of the processor; and a control module, coupled between the fan and the power measurement module, configured to control a speed of the fan according to the power of the processor, wherein when the power is higher than a predetermined power upper limit, the control module control the fan to increase the rotation speed. | 02-19-2015 |
20150056057 | ALTERNATING NOZZLES FOR RADIAL INFLOW TURBINE - A radial inflow turbine may include a wheel, a first set of nozzle vanes surrounding the wheel and a second set of nozzle vanes surrounding the wheel. A first circumferential spacing between two adjacent nozzle vanes of the first set may differ from a second circumferential spacing between another two of the nozzle vanes of the first set. | 02-26-2015 |
20150056058 | PROPELLER SOUND FIELD MODIFICATION SYSTEMS AND METHODS - A propeller system for an aircraft includes an assembly for modifying a sound field of the propeller system. The propeller system includes a rotor supported for rotation about a rotor axis. The rotor has a central hub and a plurality of blades each extending outwardly from the hub to a tip. The rotor and blades are operable to propel an aircraft to travel in a direction. The rotor blades define a rotor plane perpendicular to the rotor axis. The blade tips define a circumferential rotational path as the blades are rotated by the rotor. The propeller system includes an acoustic resonator or multiple resonators having openings disposed within a distance to the propeller blade tip that is small compared to the wavelength of the propeller's fundamental blade tone and proximate to the rotor plane. The resonators are excited by tip flow of the blade as it passes the opening. The acoustic resonators are configured and positioned so as to direct acoustic energy to modify the sound field of the propeller system at blade pass or higher harmonic frequency tones in a desired direction relative to the aircraft. | 02-26-2015 |
20150056059 | CONTROL SYSTEM - A control system controls the output capacity of a compressor to avoid surge conditions in the compressor. The control system determines a capacity control output for the compressor and then modifies the capacity control output in view of any output limiters or overrides as determined by system operating parameters and to maintain a minimum frequency of operation for the compressor. | 02-26-2015 |
20150056060 | Multiple Port Vacuum Pump System - A vacuum pump system for evacuating at least five volumes comprising a turbomolecular pump and a forevacuum pump arranged to pump an output of the turbomolecular pump arrangement to atmosphere. The turbomolecular pump has at least five pumping stages separated by rotor blades. Not more than three pumping stages have pumping speeds in excess of ⅓ of the highest pumping speed when under vacuum and/or a pumping port cross section in excess of ⅓ of the highest pumping port cross section, and at least two pumping stages have pumping speeds less than ¼ of the highest pumping speed when under vacuum and/or a pumping port cross section of less than ¼ of the biggest pumping port cross section. The ratio of pressures between the pumping stage with the highest pressure and the pumping stage with the lowest pressure is at least 100000:1 when under vacuum. | 02-26-2015 |
20150071758 | Electro-Pneumatic Actuator For A Turbocharger Waste Gate, And A Turbocharger And A Method Employing Same - An electro-pneumatic actuator for a waste gate includes an electric actuator to impart linear motion to an actuator shaft, and a pneumatic chamber defining a passage extending therethrough, the actuator shaft extending through the passage, the pneumatic chamber being sealed with respect to the actuator shaft. A piston is disposed in the pneumatic chamber and arranged for movement in the pneumatic chamber, the piston being affixed to the actuator shaft such that the actuator shaft and the piston move together as a unit. There is a port into the pneumatic chamber for feeding a gas into the pneumatic chamber or exhausting the gas therefrom so as to exert a pressure force on the piston and thereby provide a pneumatic assist to the force exerted on the actuator shaft. | 03-12-2015 |
20150071759 | METHODS AND SYSTEMS FOR LOW-PRESSURE EXHAUST GAS RECIRCULATION - A method for controlling air flow through a compressor recirculation passage, comprising: during a first condition: reducing air flow through the compressor recirculation passage based on a margin, the margin based on a rate of air flow at a compressor inlet, a rate of air flow through the compressor recirculation passage, and a rate of EGR flow. In this way, the CRV recirculation flow may be controlled to be less than the amount that could potentially backflow into an air filter disposed in the air intake passage, thus preventing EGR contained in the CRV recirculation flow from fouling the air filter with soot, oil and water. | 03-12-2015 |
20150071760 | ACOUSTIC RESONATORS FOR COMPRESSORS - A compressor and a method for reducing acoustic energy generated in the compressor are provided. The compressor may include a housing defining a fluid pathway and a shunt hole fluidly coupling the fluid pathway with another component of the compressor. The compressor may also include an impeller at least partially disposed in the fluid pathway and coupled with a rotary shaft. The impeller may be configured to rotate with the rotary shaft to direct a process fluid through the fluid pathway of the compressor. A disk may be disposed between the fluid pathway and the shunt hole. The disk may define a plurality of openings fluidly coupling the fluid pathway with the shunt hole and configured to reduce acoustic energy generated in the compressor. | 03-12-2015 |
20150078879 | AIRCRAFT ENGINE COWL DOOR MOVEMENT CONTROL SYSTEM AND METHOD - A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation. | 03-19-2015 |
20150078880 | SUPPORT ASSEMBLY FOR A TURBOMACHINE - A support assembly and method for supporting an internal assembly in a casing of a turbomachine are provided. The support assembly may include a support member that may be slidably disposed in a recess formed in the internal assembly and configured to engage an inner surface of the casing. A biasing member may be disposed in a pocket extending radially inward from the recess. The biasing member may at least partially extend into the recess and may be configured to apply a biasing force to the support member disposed therein. | 03-19-2015 |
20150078881 | ARRANGEMENT WITH A VACUUM PUMP AND METHOD OF COMPENSATING MAGNETIC FIELD PRODUCED BY MAGNETIC INTERFERENCE FIELD OF AT LEAST ONE VACUUM PUMP COMPONENT - An arrangement includes a vacuum pump having a rotor, and a drive unit for driving the rotor and having at least one magnetic interference field-generating component and at least one compensation coil for compensating the magnetic interference field generated by the at least one component. | 03-19-2015 |
20150078882 | Hydraulic Rotary Actuator - A hydraulic rotary actuator including a stator housing having a through bore to position a rotor assembly. A rotor assembly includes an output shaft and at least a first rotary piston member disposed radially about the output shaft. The rotary piston member includes an vane element. A continuous seal is disposed on peripheral longitudinal faces and lateral end faces of the rotary piston element. The bore through the stator housing includes an interior cavity with surfaces adapted to receive the rotor assembly and contact the continuous seal. With rotation fluid ports blocked, the housing cavity is sealed with the continuous piston seal for hydraulic blocking, preventing actuator displacement by external forces. A method of operation and method of assembly is disclosed. | 03-19-2015 |
20150086325 | PUMP WITH INTEGRATED HEATING ELEMENT - A pump for a dishwasher is configured as an impeller pump having a central water inflow to a rotating impeller for conveying the water in the radial direction out of the impeller into a pump chamber which surrounds the impeller in a ring-like manner and has a heated pump chamber wall on its outer side. Here, the pump has an outlet in the end region of the pump chamber at an axial spacing from the impeller. Heating elements which have a decreasing power output with regard to the area power output in the axial direction of the pump toward the outlet are arranged on the pump chamber wall. An input of energy into the pump chamber can thus be varied and in the process adapted depending on a turbulent or laminar flow. | 03-26-2015 |
20150086326 | METHOD FOR OPTIMIZING PERFORMANCE OF A COMPRESSOR USING INLET GUIDE VANES AND DRIVE SPEED AND IMPLEMENTATION THEREOF - A method for optimizing performance of a compressor by adjusting the position of an inlet guide vane and the speed of a drive unit. In one embodiment, the method can compare measured values for operating flow rate and operating pressure for a combination of operating settings for the position and the speed against threshold values for each of these measured values. In this way, the method can identify “how” the compressor is operating and equate such operation to one of a plurality of operation scenarios. In turn, the method can provide an adjustment to one or both of the speed and the position that corresponds with such operating scenario. The method can also vet the selected adjustment to avoid operation of the compressor outside of its safe operating configurations, as defined for example by minimum and maximum values for the position of the inlet guide vane and the speed of the drive unit. | 03-26-2015 |
20150093232 | SUPERSONIC COMPRESSOR AND ASSOCIATED METHOD - A supersonic compressor rotor and method of compressing a fluid is disclosed. The rotor includes a first and a second rotor disk, a first set and a second set of rotor vanes. The first set and second set of rotor vanes are coupled to and disposed between the first and second rotor disks. Further, the first set of rotor vanes are offset from the second set of rotor vanes. The rotor includes a first set of flow channels defined by the first set of rotor vanes disposed between the first and second rotor disks. Similarly, the rotor includes a second set of flow channels defined by the second set of rotor vanes disposed between the first and second rotor disks. Further, the rotor includes a compression ramp disposed on a rotor vane surface opposite to an adjacent rotor vane surface. | 04-02-2015 |
20150093233 | TURBOCHARGER WITH JOURNAL BEARING - A turbocharger assembly can include a housing with a through bore and an axial face disposed in the through bore; a locating plate with a keyed opening attached to the housing; and a journal bearing disposed in the through bore where the journal bearing includes a keyed compressor end and an enlarged outer portion defined between two axial faces by an outer diameter and an axial length where the axial face disposed in the through bore of the housing, the locating plate, and the two axial faces of the journal bearing axially locate the journal bearing in the through bore and where the keyed opening of the locating plate and the keyed compressor end of the journal bearing azimuthally locate the journal bearing in the through bore. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 04-02-2015 |
20150098791 | METHOD AND SYSTEM FOR PASSIVE CLEARANCE CONTROL IN A GAS TURBINE ENGINE - A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance. | 04-09-2015 |
20150098792 | METHOD OF OPERATING A TURBINE ENGINE AFTER FLAME OFF - The present invention relates to a method of decelerating a turbine rotor of a turbine engine. At least one electric motor is engaged with the turbine rotor. A braking system, preferably the starting system, is engaged with the at least one electric motor, preferably the generator of the turbine engine, so as to use the at least one electric motor to apply a negative (braking) torque on the turbine rotor. The method includes after flame off, the braking system being used for dissipating kinetic energy available in the turbine engine after flame off by means of the at least one electric motor. | 04-09-2015 |
20150098793 | TURBINE-PUMP SYSTEM - A turbine-pump system adapted for use with well liquid that is displaceable within a well conduit. The turbine-pump system may include a bowl assembly; and a bowl support device fixedly attachable to the bowl assembly and selectively engageable with the well conduit for holding a portion of the bowl assembly in substantially axially, radially and rotationally fixed relationship with the well conduit. | 04-09-2015 |
20150098794 | TURBINE-PUMP SYSTEM BOWL ASSEMBLY - A turbine-pump system bowl assembly for use with flowing liquid in a liquid conduit has an impeller subassembly that includes multiple axially abutting impeller members. | 04-09-2015 |
20150104288 | DUAL CHANNEL COMPLIANT TURBINE PUMP - A pump has a housing that defines a pump chamber ( | 04-16-2015 |
20150104289 | METHODS AND APPARATUS TO ADJUST BLEED PORTS ON AN AIRCRAFT ENGINE - Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port. | 04-16-2015 |
20150104290 | SUPERSONIC COMPRESSOR WITH SEPARATOR - A fluid processing device may include a rotatable shaft, a driver configured to drive the rotatable shaft, a separator installed on the rotatable shaft, and a supersonic compressor fluidly communicating with the separator. | 04-16-2015 |
20150104291 | Shaft Seal Assembly With Contaminant Detection System - A seal assembly for sealing a fluid passageway from contaminants is disclosed. The fluid passageway is formed by a rotating shaft entering an opening in a housing. The fluid passageway connects an interior of the housing, and any exterior of the housing. The seal assembly includes a first sealing member and a second sealing member, which divides the fluid passage into an interior section, an open section, and a sealed section. The interior section is exposed to the interior of the housing. The sealed section is fluidly sealed between the interior section and the open section. A sensor is disposed within the sealed section. The sensor is configured to sense the contaminants within the sealed section and is electronically coupled to a controller configured to send an alarm signal. The sensor is a moisture sensor and extends into an annular recess formed in the stationary member. | 04-16-2015 |
20150110595 | METHOD FOR ADJUSTING A BAROMETRIC CELL - A method for adjusting a barometric cell may include coupling the barometric cell to a control device via an actuating rod. The actuating rod may be movably mounted on a charging device in any desired position. The method may include applying a freely selectable pressure to the barometric cell so as to bring the actuating rod into contact with a stop, adjusting the barometric cell until a sensor registers a predefined value, and fixing the barometric cell on the charging device. | 04-23-2015 |
20150110596 | SYSTEM AND METHOD FOR STOPPING THE OPERATION OF WIND TURBINE - A method for stopping the operation of a wind turbine is disclosed. The method may generally include receiving signals associated with at least one operating condition of the wind turbine, analyzing the at least one operating condition with a controller of the wind turbine, implementing a first stopping procedure in order to stop operation of the wind turbine when analysis of the at least one operating condition indicates that a pitch system failure has occurred and implementing a second stopping procedure in order to stop operation of the wind turbine when analysis of the at least one operating condition indicates that a different wind turbine stop event has occurred. | 04-23-2015 |
20150110597 | Controlling a Turbine with a Recurrent Neural Network - The invention relates to a method for controlling a turbine which is characterized by a hidden state at each point in time of the control. The dynamic behavior of the turbine is modeled using a recurrent neural network comprising a recurrent hidden layer. The recurrent hidden layer is formed by vectors of neurons which describe the hidden state of the turbine at the points in time of the control. For each point in time, two vectors are connected chronologically to a first connection which bridges one point in time, and two vectors are additionally connected chronologically to a second connection which bridges at least two points in time. Short-term effects can be corrected by means of the first connections, and long-term effects can be corrected by means of the second connections. Emissions and occurring dynamics can be minimized in the turbine by means of the latter. The invention further relates to a control device and a turbine comprising such a control device. | 04-23-2015 |
20150118013 | Hot Gas Path Component with Impingement and Pedestal Cooling - The present application provides a hot gas path component for use in a hot gas path of a gas turbine engine. The hot gas path component may include an internal wall, an external wall facing the hot gas path, an impingement wall, a number of internal wall pedestals positioned between the internal wall and the impingement wall, and a number of external wall pedestals positioned between the external wall and the impingement wall. | 04-30-2015 |
20150118014 | Setting Gas Turbine Firing to Maintain Metal Surface Temperatures - The systems, methods, and computer-readable media set a gas turbine firing temperature to maintain gas turbine metal surface temperatures. In certain embodiments, a method of setting a gas turbine firing temperature is disclosed that may comprise determining a critical temperature at which ash from ash bearing fuels becomes unremovable by conventional water wash procedures, determining hot gas path component metal surface temperatures, and adjusting the gas turbine firing temperature to maintain the metal surface temperatures below the critical temperature. Determining the metal surface temperatures may be based at least in part on measured gas turbine parameters, gas turbine performance models, and empirical models. | 04-30-2015 |
20150118015 | GAS TURBINE DIFFUSER STRUT INCLUDING COANDA FLOW INJECTION - An exhaust diffuser comprising an inner boundary and an outer boundary forming an annular gas path, and a plurality of strut structures extending radially within the gas path. Each of the strut structures include pressure and suction side walls, and a plurality of radially spaced flow injectors are formed in at least one of the pressure and suction side walls for injecting a fluid flow into the gas path adjacent to the strut structure. At least two fluid supply conduits provide a fluid flow to respective radially spaced flow injectors, and a flow control device is associated with each of the conduits to independently control a fluid flow from a fluid source to each of the radially spaced flow injectors. | 04-30-2015 |
20150118016 | SYSTEMS AND METHODS FOR PURGING AN AFT JOINT OF A LAST STAGE WHEEL - Embodiments of the present application include a gas turbine assembly. The gas turbine assembly may include a solid wheel, a turbine aft shaft, and an aft joint connecting the solid wheel to the turbine aft shaft. The turbine assembly also may include a cover plate positioned between the solid wheel and the turbine aft shaft. The cover plate may be configured to direct a flow of compressor extraction fluid inboard through the aft joint and out the turbine aft shaft. | 04-30-2015 |
20150118017 | ELECTRONIC DEVICE AND FAN CONTROLLING METHOD - According to one embodiment, an electronic device includes a fan, a temperature sensor and a controller. The temperature sensor is configured to output a value indicative of a detected temperature. The controller is configured to control a rotational speed of the fan. The controller is configured to keep the rotational speed of the fan constant when the value is within a first temperature zone or to change the rotational speed of the fan when the values is within a second temperature zone. | 04-30-2015 |
20150118018 | COMPRESSOR, SEAL GAS DELIVERY, AND METHOD - A seal gas delivery system for an end seal on a turbo machine rotor shaft includes a seal gas passageway for delivering a seal gas to the end seal and a seal gas distributor for receiving at least a portion of the seal gas from the seal gas passageway, the seal gas distributor having a plurality of holes for distributing the seal gas about the rotor shaft during turbo machine standstill; the holes are located on a cylindrical surface and are typically arranged all around said rotor shaft, preferably regularly all around said rotor shaft. | 04-30-2015 |
20150118019 | IMPINGEMENT COOLING ARRANGEMENT - The present disclosure refers to an impingement cooling arrangement for cooling a duct wall of a duct guiding a hot gas flow. The impingement cooling arrangement includes an impingement sleeve which is at least partly disposed in a compressed air plenum, and spaced at a distance to the duct wall to form a cooling flow path between the duct wall and the impingement sleeve such that cooling air injected from the compressed air plenum through apertures in the sleeve impinges on the duct wall. At least one flow diverter is arranged in the cooling flow path to divert the cross flow away from at least one aperture. Besides the impingement cooling arrangement a gas turbine with such an arrangement as well as a method for cooling a duct wall are provided. | 04-30-2015 |
20150125257 | Systems and Methods for Boundary Control During Steam Turbine Acceleration - Certain embodiments of the disclosure may include systems and methods for boundary control during steam turbine acceleration. According to an example embodiment, the method can include receiving an indication the turbine is in an initial acceleration phase; receiving speed control parameter data from a plurality of sensors; receiving boundary control parameter data from a plurality of sensors; providing a control valve configured for controlling steam flow entering the turbine; determining the control valve position based on received speed control parameter data; determining the control valve position based on received boundary control parameter data; adjusting at least one boundary control parameter to the at least one boundary control parameter limit during turbine startup, wherein the value of a speed control parameter is simultaneously adjusted based on the adjusted at least one boundary control parameter; and adjusting the control valve position based at least on determined parameter data. | 05-07-2015 |
20150125258 | ROTARY WING AIRCRAFT HAVING TWO MAIN ENGINES TOGETHER WITH A LESS POWERFUL SECONDARY ENGINE, AND A CORRESPONDING METHOD - An aircraft ( | 05-07-2015 |
20150125259 | GAS TURBINE ENGINE VARIABLE PITCH FAN BLADE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section. | 05-07-2015 |
20150125260 | Steam Turbine Forced Air Cooling System, Equipment, and Steam Turbine Equipped with it - The invention offers a steam turbine forced air cooling system, its method, and a steam turbine provided with the system, the system being of an inexpensive and simple device configuration and improving a cooling effect by the use of an easy-to-get device. | 05-07-2015 |
20150125261 | VALVE SEQUENCING SYSTEM AND METHOD FOR CONTROLLING TURBOMACHINE ACOUSTIC SIGNATURE - A system and method for controlling the acoustic signature of a turbomachine having a plurality of valves wherein an operating load is identified and an arc of admission across a plurality of nozzles is associated therewith. A valve sequencing scheme is selected and implemented to activate the arc of admission for a particular operating load so as to minimize valve noise by adjusting valves simultaneously rather than consecutively. | 05-07-2015 |
20150132101 | COOLING SYSTEM WITH COMPRESSOR BLEED AND AMBIENT AIR FOR GAS TURBINE ENGINE - A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply. | 05-14-2015 |
20150132102 | APPARATUS AND METHOD FOR DETERMINING A TEMPERATURE DISTRIBUTION OF A HOT-TEMPERATURE FLOW IN A TURBINE ENGINE - Apparatus and method for determining a two-dimensional temperature distribution in a cross-sectional path of a hot-temperature flow in a turbine engine ( | 05-14-2015 |
20150139775 | SYSTEM FOR EXTRACTING MATTER THROUGH VARIABLE BLEED VALVES IN TURBINES - A system for extracting foreign matter in a gas turbine includes multiple variable bleed valve (VBV) doors disposed on the outer engine casing between a low pressure compressor and a high pressure compressor for bleeding a portion of flow from a core engine flow path into a bypass flow path. The system includes an outlet guide vane (OGV) assembly having multiple guide vanes disposed within the core flow path and multiple support struts positioned downstream from the multiple guide vanes. Each pairs of adjacent support struts comprises at least one VBV door therebetween and a section of the OGV assembly located at an upstream side of the fan hub frame before the each pairs of adjacent support struts. Each section of the OGV assembly includes a first side with one or more guide vanes with trimmed trailing edges configured for directing flow into the at least one VBV door. | 05-21-2015 |
20150139776 | COMPRESSOR CONTROL DEVICE, COMPRESSOR SYSTEM AND COMPRESSOR CONTROL METHOD - Provided is a compressor control device configured to control a flow rate of a compressor having a plurality of impellers connected to an outlet port-side flow path in parallel and a flow rate regulation unit configured to regulate a flow rate of each of the impellers, the compressor control device including a pressure detection unit configured to detect a pressure of the outlet port-side flow path, a flow rate detection unit configured to detect the flow rate of each of the impellers, and a control unit configured to output a flow rate regulation command of each of the impellers to the flow rate regulation unit and control the flow rate regulation unit based on the detection result of the pressure detection unit. | 05-21-2015 |
20150139777 | TURBOCHARGER SYSTEM - A turbocharger system and method for a vehicle, wherein the system comprises a high pressure turbocharger and a low pressure turbocharger. Both the high and low pressure turbochargers are driven by exhaust gas on an exhaust side of the turbochargers. The system further comprises a first bypass conduit that bypasses the low pressure turbocharger during set events. | 05-21-2015 |
20150147154 | SYSTEM AND METHOD FOR IMPLEMENTING INTRINSIC SAFETY IN ROTATING MACHINE - The embodiments herein disclose a system and method for providing an intrinsic safety to rotating machinery from the failure of internal high speed rotating structures. According to one embodiment herein, a system assembly comprises a unique design of the rotating structure to provide a sufficient safety margin and redundancy in configuration. The system assembly comprises a blower fan assembled inside a blower casing and rotated inside the casing. The fan is manufactured by a single forging process instead of an investment casting. The fan comprises several blades mounted to a hub in a shroud to draw a required quantity of fluid. The fan is mounted to a shaft through the hub. When the blower fan is rotated at a high speed exceeding the design parameters, a ‘rub and stop’ mechanism is initiated to halt the fan. | 05-28-2015 |
20150147155 | FAN CONTROL METHOD, APPARATUS, AND SYTEM - A fan control method, apparatus, and system, so as to implement speed regulation and rotation direction control on a four-wire system counter-rotating fan with a conventional four-wire fan interface by using a PWM control bus. The method provided by the embodiments of the present invention includes: receiving a first fan regulation and control signal sent by a system control module; converting the first fan regulation and control signal to a forward-rotating control signal, a counter-rotating control signal, or a rotation direction switchover control signal according to a duty cycle range of the first fan regulation and control signal and a current rotation direction of the fan; and sending a control signal obtained by the conversion to a fan driving module, so that the fan driving module drives, according to the control signal obtained by the conversion, the fan to operate. | 05-28-2015 |
20150292344 | INGESTION BLOCKING ENDWALL FEATURE - An endwall of a gas turbine engine section comprises a flow path surface and a wall. The flow path surfaces defines an inner diameter of a main flow path through the gas turbine engine section, and terminates in an aft waterfall step. The wall extends substantially radially inward from the waterfall step, and defines a blockage feature that impedes airflow from the main flow path to a secondary air cavity situated inward of the waterfall step. | 10-15-2015 |
20150292349 | TURBOEXPANDER AND DRIVEN TURBOMACHINE SYSTEM - A turboexpander and driven turbomachine system comprising a turboexpander configured for expanding a first fluid and comprising an expander stage with one expander impeller; a first set of moveable inlet guide vanes at the inlet of the expander stage; a driven turbomachine configured for processing a second fluid and comprising a turbomachine impeller; a second set of moveable inlet guide vanes at the inlet of the turbomachine impeller; a mechanical transmission between the turboexpander and the driven turbomachine; and a controller connected to the second set of moveable inlet guide vanes and configured for controlling the second set of moveable inlet guide vanes for adjusting the rotary speed of the driven turbomachine and said turboexpander. | 10-15-2015 |
20150292359 | LUBRICATING A ROTATING COMPONENT DURING FORWARD AND/OR REVERSE ROTATION - An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating component, a turbine engine component and a lubrication system. The lubrication system is adapted to lubricate the turbine engine component where the rotating component rotates a first direction about an axis. The lubrication system is also adapted to lubricate the turbine engine component where the rotating component rotates a second direction about the axis. | 10-15-2015 |
20150292521 | BLOWER AND METHOD FOR DECREASING EDDY NOISE - A blower and a method for decreasing eddy noise are provided. The blower includes a fan frame, a fan wheel, at least one induction element and a coil. The fan frame has in inlet and an outlet. The fan wheel is disposed in the fan frame and has a wheel hub and a plurality of fan blades connected to periphery of the wheel hub. The induction elements are fixed to the corresponding fan blades, the coil is disposed on the fan frame for driving the at least one induction element, such that the fan blade corresponding to the induction element swing back and forth to generate a vibration sound, and the vibration sound is counteracted with eddy noise generated when the fan wheel rotates. Moreover, the method for decreasing eddy noise is also provided. | 10-15-2015 |
20150292522 | SYSTEM AND METHOD FOR TRAILING EDGE NOISE REDUCTION OF A WIND TURBINE BLADE - A system and method for reducing the operational noise of a blunt trailing edge of a wind turbine blade is described. The system involves increasing the trailing edge solid angle at the blade trailing edge by providing a wedge element or projection adjacent the trailing edge of the blade, the wedge element acting to provide improved mixing of the suction side and pressure side flows at the blunt trailing edge, thereby reducing the strength of vortex shedding at the trailing edge and the associated operational noise. | 10-15-2015 |
20150300183 | Fluid Turbine With Turbine Shroud And Ejector Shroud Coupled With High Thrust-Coefficient Rotor - The present disclosure includes a shrouded fluid turbine that generates large wake expansion to generate power coefficients greater than the Betz power coefficient of 16/27 based on maximum system area. The Virtual Diffuser Wind Turbine (VDWT) system operates differently with, and without power extraction. With power extraction the VDWT system includes a high rotor thrust coefficient combined with an annular shroud system that uses bypass flow to form an annular, high-energy bypass flow stream that flows outward at the exit plane of the VDWT generating an observable virtual diffuser downstream therefrom. This outward, high-energy flow reduces exit plane pressure generating large wake expansions. The large wake expansion increases the flow rate through the rotor. Without rotor power extraction, separation takes place which reduces some of aerodynamic loads on the VDWT at extreme winds. | 10-22-2015 |
20150300187 | TURBOMACHINE THERMAL MANAGEMENT - An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior. | 10-22-2015 |
20150300195 | BLADE OUTER AIR SEAL WITH CORED PASSAGES - A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook. | 10-22-2015 |
20150300265 | GAS TURBINE ENGINE WITH COOLING SCHEME FOR DRIVE GEAR SYSTEM AND PITCH CONTROL - A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system. | 10-22-2015 |
20150300357 | PUMP SYSTEM FOR HIGH PRESSURE APPLICATION - A pump system for high pressure, high volume applications is presented. The pump system includes a turbo-shaft engine having a drive shaft and a high pressure, high RPM centrifugal pump coupled to the drive shaft. In certain embodiments the pump system further includes a second low pressure, high RPM centrifugal pump coupled to the drive shaft. | 10-22-2015 |
20150300369 | CENTRIFUGAL COMPRESSOR WITH TWISTED RETURN CHANNEL VANE - Three-dimensional (3D) return vane for a multistage centrifugal compressor. The return channel vane extends upstream to a region proximate the bend apex of the return channel. In each point of the return channel vane, the angle “beta” is defined as the acute angle between the tangent to the local camberline and the local circumferential direction. At each normalised position between leading edge and trailing edge, the local twist of the return channel vane is defined as the algebraic difference between the angles beta at the two points at hub and shroud having said normalised position. When moving in streamwise direction from leading edge to trailing edge, the twist first decreases, reaching an algebraic minimum, then increases, reaching an algebraic maximum, then decreases again. However, the absolute twist of the algebraic minimum is larger than the absolute twist of the algebraic maximum. | 10-22-2015 |
20150308442 | DEAD TIME REDUCER FOR PISTON ACTUATOR - An anti-surge system capable of anticipating a surge event in a compressor for readying the actuator to quickly actuate the anti-surge valve from the closed position to the open position. The control system includes a compressor surge controller configured to transmit a signal to the valve positioner when the operating point of the valve is approaching the surge control line. The compressor surge controller may monitor an operating margin equal to the difference between the operating point and the surge control line, and when the operating margin falls below a prescribed threshold, the compressor surge controller may send a signal to the positioner. In turn, the positioner may vent some pressure from the actuator. In this way, the dead time of the anti-surge valve on the valve seat is minimized and the valve will react more promptly to an opening signal. | 10-29-2015 |
20150308443 | COMPRESSOR WITH THRUST BALANCING AND METHOD THEREOF - A compressor for a motor-compressor set, comprising, on a rotating shaft, a balancing piston, a set of bladed wheels, a rear cavity of the piston adjacent to the balancing piston on a side opposite to the set of bladed wheels, a regulation valve suitable for coupling the rear cavity to the input of the set of bladed wheels, a suction pressure chamber coupled to the input of the set of bladed wheels, the rear cavity being arranged between the balancing piston and the suction pressure chamber. The compressor comprises a discharge pressure chamber arranged between the rear cavity of the piston and the suction pressure chamber, the discharge pressure chamber being coupled via a discharge line to a discharge area between the set of bladed wheels and the balancing piston. | 10-29-2015 |
20150308444 | MULTIPHASE PUMP - A product-lubricated multiphase pump for pumping a multiphase mixture containing hydrocarbon includes a separation system and a supply system. To achieve a good cooling and lubrication of pump elements without a lot of operating media and operating medium circuits, the separation system has a first separation stage for at least partly separating at least a portion of the multiphase mixture into a plurality of phase-enriched components and the supply system supplies a liquid-enriched liquid component as lubricant to a pump element to be lubricated. | 10-29-2015 |
20150308446 | IMPELLER FOR A CENTRIFUGAL PUMP, A CENTRIFUGAL PUMP AND A USE THEREOF - An impeller for a centrifugal pump, the impeller includes a front shroud, a rear shroud, and one or more working vanes therebetween, the front shroud having a front face opposite to the face having the working vanes, the rear shroud having a rear face opposite to the face having the working vanes, the front shroud having an outer circumference and a plurality of front pump-out vanes attached to the front face of the front shroud, the rear shroud having a plurality of rear pump-out vanes attached to the rear face of the rear shroud,
| 10-29-2015 |
20150308459 | GAS TAKEOFF ISOLATION SYSTEM - A fluid takeoff assembly for a motor-compressor is provided and includes an outer pipe having an inlet and an outlet, and an inner pipe defining a fluid passage extending from an open axial end toward a closed axial end thereof and a radial opening fluidly coupled with the fluid passage. The inner pipe may be disposed in the outer pipe such that the open axial end and the closed axial end are oriented toward the outlet and the inlet, respectively, and the inner and outer pipes define an annular space therebetween. A cross-flow member may be coupled with the inner pipe and may define a flowpath fluidly coupled with the fluid passage via the radial opening. A vane and the cross-flow member may be disposed in the annular space and configured to at least partially induce a swirling flow in a process fluid flowing through the annular space. | 10-29-2015 |
20150308460 | INLET TUBE DESIGN - A ram air fan assembly includes an outer housing. An inner housing is located within the outer housing. A motor is attached to the inner housing. An inlet tube extends between the outer housing and the motor. The inlet tube includes a straight first portion and a curved second portion. At least one of the two portions includes a perforated portion. | 10-29-2015 |
20150315884 | MULTIPHASE PRESSURE BOOSTING PUMP - The invention provides a system for multiphase pumping, preferably for subsea application, distinctive in that it comprises a multiphase pressure boosting pump and a separator, preferably adapted for subsea operation, a multiphase fluid inlet connected to the pump, a multiphase outlet from the separator, an outlet of the pump arranged to an inlet of the separator, a liquid outlet of the separator arranged to a liquid inlet on the pump, and a power recovery turbine arranged between said liquid outlet of the separator and said liquid inlet on the pump. The invention also provides a multiphase pressure boosting pump, preferably adapted for subsea operation, comprising a motor, one or more impellers arranged on a shaft common with a motor shaft or coupled to the motor, a pressure housing, a multiphase fluid inlet and an outlet, distinctive in that the pump further comprises a liquid injection inlet and a power recovery turbine, with the power recovery turbine arranged between the liquid injection inlet and the pump impellers. | 11-05-2015 |
20150316064 | MULTISTAGE COMPRESSOR AND METHOD FOR OPERATING A MULTISTAGE COMPRESSOR - A multi-stage compressor is described, comprising a rotor having a plurality of axially stacked impellers and a tie rod extending through the stacked impellers and holding the impellers together. A gas compression path extends from a compressor inlet to a compressor outlet and through the impellers. A flow channel is provided between the tie rod and the stacked impellers. The flow channel develops along at least a portion of the tie rod. Hot gas is diverted from the compression path and flows through the flow channel to heat the tie rod during startup of the compressor. | 11-05-2015 |
20150322952 | WET GAS COMPRESSOR AND METHOD - A centrifugal compressor for processing a wet gas. The centrifugal compressor includes: a casing; and least one compressor stage comprising at least one impeller rotatingly arranged in the casing and provided with an impeller hub and a plurality of impeller blades, each impeller blade having a suction side and a pressure side. The at least one compressor stage comprises at least one droplet breaking arrangement configured for promoting breakup of liquid droplets flowing through the compressor stage. | 11-12-2015 |
20150322956 | METHOD FOR PREVENTING SURGE IN A DYNAMIC COMPRESSOR USING ADAPTIVE PREVENTER CONTROL SYSTEM AND ADAPTIVE SAFETY MARGIN - A method of preventing surge in a dynamic compressor is disclosed. The method includes providing an anti-surge valve having an adjustable opening for increasing the flow through a dynamic compressor. The next step is sensing process conditions in the dynamic control to determine a compressor load variable. A control system estimates a process disturbance model using the compressor load variable. The control system then adjusts a safety margin using a rate limited response and initiates a closed loop response using process feedback based on the process disturbance model. The control system adjusts the opening of the anti-surge valve according to the safety margin and closed loop response. | 11-12-2015 |
20150322968 | SYSTEM FOR EXCLUDING PROCESS FLUID AND SOLIDS FROM SEALS AND BEARINGS OF AN AXIAL PUMP IN A LOOP REACTOR - A mechanical expelling mechanism for an axial pump system in a loop reactor includes straight or curved repelling vanes mounted to a vertical or tapered rear face of the impellor hub and a tapered wall provided in the adjacent seal housing. In combination, these elements exclude and eject process slurry, especially polymer solids, away from the seals and bearings, and thereby prevent damage to the seals and bearings, at least until a flow of flushing fluid can be restored. The repelling vanes further serve to circulate and exchange any process fluid and catalyst that remains in the space between the impellor and the seals, so that localized warming and run-away formation of polymer solids near the seals is avoided. The repelling vanes can be curved or straight. In embodiments, the repelling vanes reduce pump efficiency by less than 1%. | 11-12-2015 |
20150322970 | PRESSURIZED LIQUID LIFTING DEVICE AND LIQUID LIFTING METHOD - A liquid lifting device includes: a liquid lifting tank storing liquid; an air pump pressurizing the interior of the liquid lifting tank; a liquid lifting pipe connecting the liquid lifting pipe to the liquid lifting tank having a liquid delivery port in the other end that stands upright; an air supply pipe in which one end portion of the air supply pipe connected to a branching section provided at a position halfway in the liquid lifting pipe and an upright section provided in the other end portion thereof; an air valve that is provided on the other end portion of the air supply pipe; and a liquid storage section that is formed in part of the liquid lifting pipe at a position between the liquid delivery port and the branching section and that is positioned below the branching section. | 11-12-2015 |
20150329187 | PROPELLER AND RELATIVE METHOD FOR FINE ADJUSTING THE FLUID DYNAMIC PITCH OF THE PROPELLER BLADES - A propeller and related method for adjusting the fluid-dynamic pitch of the propeller blades are described. The propeller has at least one rotatable blade pivoted to a propeller cylindrical casing, a hub adapted to be coupled to an engine and mounted within the propeller casing. The hub is rotatable with respect to the propeller cylindrical casing, or vice versa, for a non-zero angular interval (α) for the adjustment of the fluid-dynamic blade pitch. Moreover, the hub has a contact surface movable between direct or indirect disengagement and engagement positions with a respective abutment which defines a limit stop of the angular interval (α). The limit stop abutment has a region of a movable element arranged in a seat of the propeller cylindrical casing for modifying the limit stop abutment position of the angular interval (α). | 11-19-2015 |
20150330220 | METHOD FOR BALANCING THRUST, TURBINE AND TURBINE ENGINE - A turbine comprising a rotatable rotor and a pressure chamber; a wall of the pressure chamber is arranged to act on the rotor so that to balance thrust exerted by the rotor when it rotates; a conduit connects the pressure chamber and arranged to a pressure source; a valve associated to the conduit may open and close the conduit; the valve is arranged to open automatically when the pressure upstream of the valve exceeds a first predetermined threshold value; in this way, when the load of the turbine is high excessive thrust is balanced because of the higher pressure in the pressure chamber. | 11-19-2015 |
20150330229 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall. | 11-19-2015 |
20150330230 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane. | 11-19-2015 |
20150330240 | TURBOCHARGER OUTBOARD PURGE SEAL - The propensity for oil leakage around the clearance seals of a rotating turbocharger assembly can be minimized by the addition of a variety of sealing systems using an externally pressurized cavity formed between the backface of the compressor wheel and the bearing housing. In one implementation, a pressure plate can be provided. In another embodiment, labyrinth seals can be provided. In addition to these various sealing arrangements, external pressurized air or internally supplied charge air can be selectively supplied to the space behind the pressure plate or labyrinth seal to maintain an inward directed pressure gradient across the seal interface regardless of operating conditions. | 11-19-2015 |
20150330251 | GAS TURBINE ENGINE WITH FLUID DAMPER - A gas turbine engine includes a static structure which includes a first fluid passage and a rotatable shaft. A bearing assembly supports the rotatable shaft relative to the static structure. The bearing assembly includes an outer race with a damper passage that extends between the static structure and the outer race. A second fluid passage extends from the damper passage to a seal. | 11-19-2015 |
20150330305 | ANTI-ICING INTERNAL MANIFOLD - A manifold for a gas turbine engine includes oppositely facing first and second walls that extend from an annular wall. An undulating wall oppositely faces the annular wall and couples the first wall to the second wall. The walls collectively form a plurality of first chambers in fluid communication with a plurality of second chambers so that each of the second chambers intersperse adjacent first chambers. Each first chamber has a first volume that is greater that a second volume of each second chamber. | 11-19-2015 |
20150330362 | METHOD AND DEVICE FOR CONTROLLING FLOATING BODY WIND TURBINE POWER GENERATING APPARATUS, AND FLOATING BODY WIND TURBINE POWER GENERATING APPARATUS - A method of controlling a floating-body wind turbine power generating apparatus including a wind turbine generator disposed on a floating body includes a pitch-angle increasing step of increasing a pitch angle of a blade of the wind turbine generator when the wind turbine generator is stopped, so that an aerodynamic braking force is applied to a rotor of the wind turbine generator. In the pitch-angle increasing step, a first change rate of the pitch angle of the blade in a first period during which the wind turbine generator is in an inclining motion toward an upwind side from a vertical direction due to sway of the floating body, is smaller than a second change rate of the pitch angle of the blade in a second period during which the wind turbine generator is in an inclining motion toward a downwind side from the vertical direction due to the sway of the floating body. | 11-19-2015 |
20150330394 | CENTRIFUGAL BLOWER HOUSING HAVING SURFACE STRUCTURES, SYSTEM, AND METHOD OF ASSEMBLY - A centrifugal blower assembly includes a housing having an inner surface and an outer surface. The inner surface of the housing defines in part an interior space. The centrifugal blower also includes a first portion of texture applied to at least a first portion of at least one of the inner surface and the outer surface of the housing. The first portion of texture has a first height based at least in part on a local boundary layer height of an airflow moving across at least one of the inner surface and the outer surface respectively. The first portion of texture is configured to generate a turbulent flow within the airflow moving across the first portion of texture. | 11-19-2015 |
20150330402 | SEALING ASSEMBLY FOR TURBOMACHINE - The invention relates to a turbine engine comprising an air compression stage comprising at least one movable compressor wheel, an air inlet duct coupled to said air compression stage, a first sealing device, which is arranged between a front portion of the movable compressor wheel and the air inlet duct and comprising at least one seal, a channel for conveying the air compressed by the movable wheel and a second sealing device, which is arranged between a rear portion of the movable compressor wheel and the conveying channel and is configured to receive an airflow coming from the conveying channel, the turbine engine being remarkable in that the second sealing device is configured to allow some of the air passing therethrough to be bled and in that the bleed air is conveyed to the seal of the first sealing device so as to keep it under pressure. | 11-19-2015 |
20150337679 | METHOD FOR DETECTING A FLUID LEAK IN A TURBOMACHINE AND SYSTEM FOR DISTRIBUTING A FLUID - The invention relates to a method for detecting a fluid leak in a turbomachine. The turbomachine comprises a high temperature fluid source, at least one fluid distribution pipe adapted to distribute said fluid to different parts of the turbomachine and/or the aircraft which is intended to be equipped with said turbomachine, a turbomachine compartment in which the distribution pipe is at least partly accommodated, said compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source. The method comprises the following steps: measuring a temperature variation in the compartment between two instants to obtain a temperature gradient; and detecting a fluid leak if the temperature gradient is greater than or equal to a threshold temperature gradient. The invention further relates to a system for distributing a high temperature fluid for a turbomachine and a turbomachine comprising such a system for distributing a fluid. | 11-26-2015 |
20150337682 | COOLING ARCHITECTURE FOR TURBINE EXHAUST CASE - Cooling a turbine exhaust case (TEC) employed in an industrial gas turbine engine includes supplying cooling airflow from an outer diameter (OD) to an inner diameter (ID) cavity, supplying a secondary airflow having a pressure greater than the pressure of the cooling airflow to the ID cavity for mixing with the cooling airflow to provide a mixed airflow, and directing the mixed airflow in a serpentine cooling path that includes first directing the mixed airflow radially outward via hollow struts to an OD cavity, then radially inward via hollow fairings that surround the hollow struts. | 11-26-2015 |
20150337684 | Acoustic Treatment to Mitigate Fan Noise - A gas turbine engine has a propulsor including a fan and a liner positioned upstream of the fan. The liner has a backing plate, a cellular structure with cells extending from the backing plate, and a perforated sheet with a depth defined as a distance between the perforated sheet and the backing sheet. The depth is selected to achieve a desired ratio of the depth relative to a gap?. A depth to gap ratio is substantially in a range of 0.035 to 0.08. A method is also disclosed. | 11-26-2015 |
20150337846 | METHOD AND DEVICE FOR DRIVING A TURBOCHARGER - In a method for driving a turbocharger with the aid of induction air which is fed to the turbine inlet, the compressed air which exits at the compressor outlet is guided into a turbine auxiliary inlet of the turbine, which turbine auxiliary inlet opens downstream of the turbine inlet into the turbine chamber at a point, at which the pressure in the driven state of the turbine is lower than the pressure of the air which is compressed by the turbocompressor. | 11-26-2015 |
20150345265 | UP-THRUSTING FLUID SYSTEM - A submersible fluid system for operating submersed in a body of water includes a fluid-end housing having an upper end and a lower end. A fluid rotor is disposed to rotate in the fluid-end housing and to receive and interact with a process fluid flowing from an inlet of the fluid-end housing to an outlet of the fluid-end housing. The fluid rotor is configured to thrust upwards toward the upper end when rotating. A bearing near the lower end of the fluid-end housing has an upward-facing bearing surface coupled to the fluid rotor and a downward-facing bearing surface coupled to the fluid housing, the bearing surfaces cooperate to support the upward thrust of the fluid rotor. | 12-03-2015 |
20150345323 | VARIABLE STATOR VANE ARRANGEMENT - A variable stator vane arrangement includes a casing, a plurality of stator vanes, at least one control ring, a plurality of connecting rods and a crankshaft. The stator vanes are circumferentially spaced apart in the casing and the plurality of stator vanes are rotatably mounted in the casing. Each control ring is rotatably mounted on the casing and each stator vane is connected to an associated control ring. The crankshaft, rotatably mounted on the casing, is drivingly connected to each control ring and has an axis and a plurality of clevises. Each connecting rod connects one of the clevises on the crankshaft to a respective one of the control rings. At least one clevis is adjustably secured to the crankshaft by an adjusting mechanism and the adjusting mechanism is used to select the radial and/or angular position of at least one clevis relative to the axis of the crankshaft. | 12-03-2015 |
20150345336 | APPARATUS AND METHOD FOR ADJUSTING AN INNER CASING OF A TURBOMACHINE - A support assembly for externally adjusting an inner casing with respect to an outer casing for a turbomachine includes a carrier plate, a carrier block that is fixedly connected to the carrier plate, a restrictor block fixedly connected to the carrier plate, a rod coupled to the carrier plate, and a plate threadably connected to the rod. The carrier block includes an inclined side and a carrier side. The restrictor block includes a restrictor side and an inclined side. The restrictor side is generally oriented towards the carrier side. A vertical gap for receiving a support arm of an inner turbine casing is defined between the restrictor side and the carrier side. The plate may be rotated about the rod to cause simultaneous movement of the rod, the carrier plate, the carrier block and the restrictor block, thus adjusting the inner casing with respect to the outer casing. | 12-03-2015 |
20150345377 | TURBINE EXPANSION RATIO ESTIMATION FOR MODEL-BASED BOOST CONTROL - A method for controlling a turbine of an engine system to achieve a desired boost pressure is provided. The method determines a desired exhaust gas pressure based on the desired boost pressure by using a model for a power balance between the turbine and a compressor of the engine system. The method generates a base command for controlling a position of a vane of the turbine based on a ratio of the desired exhaust gas pressure to a measured turbine outlet pressure. | 12-03-2015 |
20150345425 | FLOW PATH ROUTING WITHIN A GAS TURBINE ENGINE - An example gas turbine engine with multiple flow paths includes, among other things, a core flow path extending from a compressor section to an exhaust section, a bypass duct providing a bypass flow path radially outside the core flow path, and a flow injection device to selectively communicate a first amount of flow or a second amount of flow from the bypass flow path to the exhaust section, the first amount of flow different than the second amount of flow. | 12-03-2015 |
20150345467 | METHOD FOR MONITORING THE OPERATION OF A WIND ENERGY PLANT AND WIND ENERGY PLANT - A method for monitoring the operation of a wind energy plant having at least one blade angle adjustable rotor blade. Rotor blade vibrations are registered during operation by at least one measuring device, and at least one current natural frequency is established from the registered vibrations. At least one environmental parameter and/or at least one operational parameter, which influence the natural frequency of the rotor blade, is or are additionally registered. At least one natural frequency expected value dependent on the additionally registered parameter(s) and at least one confidence interval are calculated for the at least one established current natural frequency of the rotor blade, and whether the established current natural frequency lies within, or outside of, the confidence interval around the natural frequency expected value is monitored. Also disclosed is an operational control apparatus of a wind energy plant and a corresponding wind energy plant. | 12-03-2015 |
20150354387 | Variable Vane Overlap Shroud - A shroud supports one of an inner and an outer trunnion on a variable vane. The shroud is provided by a first and a second axial half. Each of the axial halves is provided by a plurality of circumferentially spaced segments. Circumferential edges are defined on each of the plurality of circumferentially spaced segments. Edges between adjacent ones of the circumferentially spaced segments on the first half are circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of the second half, such that no direct leakage path exists across an axial width of the shroud. | 12-10-2015 |
20150354441 | WASTEGATE CONTROL - Various methods for operating a wastegate are provided. In one example, a method of controlling a linked valve actuator system comprises adjusting the actuator near an end stop based on a learned uncertainty end stop region, the region based on operating conditions. | 12-10-2015 |
20150354456 | COOLING SYSTEM FOR GAS TURBINE ENGINES - A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment. | 12-10-2015 |
20150354464 | METHOD AND APPARATUS FOR CONTROLLING A COMPRESSOR OF A GAS TURBINE ENGINE - A method of operating a gas turbine engine compressor. The method includes: determining an operating point of the compressor, and modulating mass flow of environmental control system input air to maintain the operating point of the gas turbine engine compressor within predetermined limits. | 12-10-2015 |
20150354582 | Tandem Thrust Bearing with Resilient Bearing Support - An electrical submersible pump assembly has a thrust bearing mechanism with first and second thrust runners axially and rotationally secured to the shaft and located within a housing. First and second thrust receiving structures are rigidly mounted in the housing to receive thrust from the first and second thrust transferring devices. A deflectable member located in the first thrust transfer thrust device decreases in axial thickness in response to thrust of a selected level. The second thrust transfer thrust device has an axial length less than an axial distance from the second thrust receiving structure to the second thrust runner, defining an initial axial gap. During operation of the pump, the shaft and the first and second thrust runners move axially a limited extent, closing the gap and transferring thrust from the second thrust transfer device to the second thrust receiving structure. | 12-10-2015 |
20150354589 | CENTRIFUGAL COMPRESSOR WITH EXTENDED OPERATING RANGE - This disclosure relates to a centrifugal compressor. In a first example, the compressor includes a first impeller provided in a main refrigerant flow path, a second impeller provided in the main refrigerant flow path downstream of the first impeller, and a recirculation flow path. In the first example, the recirculation flow path is provided between a first location and a second location along the main refrigerant flow path. The first location is downstream of the second location, and the second location is downstream of the first impeller. In a second example, the compressor includes an impeller provided in a main refrigerant flow path, and a recirculation flow path provided between a first location and a second location along the main refrigerant flow path. In the second example, the recirculation flow path includes a recirculation volute. Further disclosed is a method for operating a centrifugal compressor. | 12-10-2015 |
20150361819 | VIRTUAL MULTI-STREAM GAS TURBINE ENGINE - A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow. | 12-17-2015 |
20150361824 | Gas Turbine Engine with Low Fan Noise - In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle β | 12-17-2015 |
20150361874 | MULTI-STAGE TURBOCHARGER SYSTEM - A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger and a second relatively large low pressure (LP) turbocharger. The turbine of the LP turbocharger is connected in series downstream of the turbine of the HP turbocharger. A first exhaust bypass flow passage provides a bypass flow path around the HP turbine. A second exhaust bypass flow passage provides a bypass flow path around the LP turbine. A rotary valve is located at a junction of the first and second bypass flow passages and a first exhaust gas flow passage. The rotary valve comprises a valve rotor which is rotatable selectively to permit or block flow to the LP turbine and to permit or block flow to the first and second bypass paths. | 12-17-2015 |
20150361885 | AN ACOUSTICALLY OPTIMIZED AIR INLET - A nacelle structure ( | 12-17-2015 |
20150361888 | GAS TURBINE ENGINE LUBRICATION SYSTEM - A gas turbine engine according to an exemplary aspect of the present disclosure includes, a shaft including at least one bearing, a speed change device in communication with the shaft, a first lubrication system in communication with the at least one bearing and a second lubrication system in communication with the speed change device. | 12-17-2015 |
20150361988 | BLOOD PUMP ROTOR BEARINGS - A bearing assembly for use in a blood pump includes a first component that has a convex bearing surface and a first outer surface proximate the convex bearing surface. The bearing assembly includes a second component that a concave bearing surface and a second outer surface proximate the concave bearing surface, the concave bearing surface being configured to receive the convex bearing surface. A plurality of grooves are defined through the convex bearing surface and first outer surface or through the concave bearing surface and the second outer surface. | 12-17-2015 |
20150362405 | AUTO TESTING SYSTEM FOR A GAS TURBINE - A gas turbine system has a gas turbine engine, control unit, a data acquisition system including a thermodynamic model unit and a test sequence unit, sensor device coupled to the engine for measuring performance parameter of the engine, and comparative unit. The thermodynamic model unit generates computed performance parameter based on mechanical and thermodynamic models of the engine. The test sequence unit generates test sequence data including set point operating data and time schedule data with which a test cycle of the engine is runnable. The data acquisition system generates test control data based on the test sequence data, and is coupled to the control unit for providing test control data thereto to control the engine. The comparative unit is coupled to the data acquisition system such that the measured performance parameter measured by the sensor device is comparable with the computed performance parameter. | 12-17-2015 |
20150369065 | NACELLE AIR SCOOP ASSEMBLY - An air scoop assembly that may be for a nacelle of a turbofan engine includes a surface defining at least in-part a primary flowpath and a hood formed to the surface and projecting into the primary flowpath. The hood includes a distal, leading, edge that is irregular in shape thereby producing air vortices that shed from the leading edge and co-extend in a downstream direction with an airstream in the primary flowpath. The vortices are thereby controlled such that air flow disruption and undesired resonance is minimized or eliminated. | 12-24-2015 |
20150369071 | GAS TURBINE ENGINE COMPONENT HAVING TIP VORTEX CREATION FEATURE - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a static structure that extends between a radially outer portion and a radially inner portion and at least one vortex creation feature formed on the static structure. | 12-24-2015 |
20150369077 | SUCTION-BASED ACTIVE CLEARANCE CONTROL SYSTEM - A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends. | 12-24-2015 |
20150369078 | PIVOT DOOR THRUST REVERSER WITH VARIABLE AREA NOZZLE - A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area. | 12-24-2015 |
20150369130 | SYSTEMS AND METHODS FOR DISTRIBUTING COOLING AIR IN GAS TURBINE ENGINES - Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section. | 12-24-2015 |
20150377064 | TURBOCHARGER TURBINE HOUSING - A turbocharger turbine housing can include a base that defines a turbine wheel opening that includes an axis that defines an axial direction; an exhaust inlet flange that defines an exhaust inlet; an exhaust outlet flange that defines an exhaust outlet; a wastegate shaft bore, a wastegate passage, a wastegate opening for the wastegate passage and a wastegate seat disposed about the wastegate opening; bosses where each of the bosses defines a coolant opening; a spiral coolant passage in fluid communication with at least two of the coolant openings where the spiral coolant passage includes at least two windings with respect to an axial dimension of the turbocharger turbine housing; and at least one coolant passage that is in fluid communication with at least two of the at least two windings of the spiral coolant passage. | 12-31-2015 |
20150377069 | COATING FOR ISOLATING METALLIC COMPONENTS FROM COMPOSITE COMPONENTS - A barrier coating for isolating a metallic support component from a composite component in a gas turbine engine is provided. The barrier coating may be applied to the metallic support component so that when the ceramic component is mounted on the metallic support component the barrier coating is engaged. | 12-31-2015 |
20150377144 | GAS TURBINE ENGINE GEARED ARCHITECTURE - A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan. | 12-31-2015 |
20150377145 | METHOD AND APPARATUS FOR LOCAL LOOP CLOSURE - A method and apparatus for local loop closure is provided. The apparatus includes a component for use in a gas turbine engine. The component includes at least one of an actuator and a servo-valve or electric motor, at least one sensor, and an electronic module comprising controller electronics and memory. The electronic module is configured to receive and process commands for the at least one of an actuator and a servo-valve and queue received commands in an input buffer. | 12-31-2015 |
20150377243 | Method and apparatus for controlling subrack fans - Disclosed are a method and an apparatus for controlling subrack fans. The method comprises: by installing multiple boards installed with high-power components in different areas of a subrack respectively, forming multiple heat dissipation air channels corresponding to the multiple boards respectively; installing a fan group comprising multiple heat dissipation fans on the subrack; dividing the fan group into multiple fan areas corresponding to the multiple heat dissipation air channels respectively, so that each fan area blows air to a corresponding board through a corresponding heat dissipation air channel; detecting temperature of each board and a rotating speed of a corresponding fan area in real time; adjusting the rotating speed of the fan area according to a detection result, so that the rotating speed of the fan area increases or decreases as the temperature of the corresponding board increases or decreases. Also disclosed is the apparatus for controlling subrack fans. According to the present invention, power consumption and noise of fans can be reduced effectively while ensuring system heat dissipation, and a rotating speed of each fan can be displayed correctly. | 12-31-2015 |
20150377244 | SYSTEM AND METHOD FOR COMPRESSING AIR - A compression train system and method for compressing air for an air separation unit is provided. The system includes at least one initial air compressor configured to receive and compress a flow of ambient pressure air and driven by a variable speed motor. The system further includes a plurality of downstream compressors or compression turbo-machines disposed in a series arrangement with the at least one initial compression stage. The desired flow rates to the compression system is controlled by adjusting the speed of the variable speed motor and the position of inlet guide vanes to increase or decrease the flow rate of the ambient pressure air and keep the speed of the variable speed motor above or below a restricted speed zone. | 12-31-2015 |
20150377249 | DIFFUSER AND METHOD OF OPERATING DIFFUSER - In one aspect, a diffuser for expanding the cross-sectional area of an airstream comprises an inlet comprising an inlet cross-sectional area and an outlet comprising an outlet cross-sectional area. The outlet cross-sectional area is greater than the inlet cross-sectional area. A curved sidewall extends from the inlet to the outlet and at least partially defines an inner passageway. The curved sidewall comprises a convex portion and a concave portion. The convex portion is adjacent the inlet and the concave portion is adjacent the outlet. | 12-31-2015 |
20150377250 | INLET GUIDE VANE MECHANISM - An inlet guide vane assembly ( | 12-31-2015 |
20150377358 | HIGH TEMPERATURE SUBSEA DYNAMIC SEALS - Systems and methods are described for processing a high-temperature process fluid using a processing machine in a subsea location while protecting dynamic seals within the machine. In some examples a small portion of the process fluid is cooled using a cooling system the cooled process fluid is then directed towards the dynamic seals. In other examples the dynamic seals are shielded and isolated from the high temperature process fluid and cooler barrier fluid is circulated within an enclosed volume in proximity to the seal. | 12-31-2015 |
20160003079 | GAS TURBINE ENGINE COMPONENT HAVING VARIABLE WIDTH FEATHER SEAL SLOT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length. | 01-07-2016 |
20160003085 | TURBINE ENGINE ADAPTIVE LOW LEAKAGE AIR SEAL - An air seal includes a sealing gland configured to retain a ferro-fluid and one or more seals. A portion of the one or more seals is configured to extend into the sealing gland. A gas turbine engine, includes the air seal. A method of sealing low pressure air from high pressure air, includes the steps of providing a sealing gland configured to retain a ferro-fluid, distributing the ferro-fluid into the sealing gland, providing one or more seals, wherein a portion of the one or more seals is configured to extend into the sealing gland, and removing the ferro-fluid from the sealing gland. | 01-07-2016 |
20160003091 | NACELLE INTERNAL AND EXTERNAL FLOW CONTROL - A nacelle ( | 01-07-2016 |
20160003093 | Fan Axial Containment System - A gas turbine engine ( | 01-07-2016 |
20160003095 | UNDULATING STATOR FOR REDUCING THE NOISE PRODUCED BY INTERACTION WITH A ROTOR - A stator designed to be placed radially in a flow which passes through one or more rotors which share the same axis of rotation, with a leading edge and a trailing edge. The leading edge and trailing edge are connected by a lower face and an upper face, wherein at least one of the faces of the stator has radial undulations which extend axially from the leading edge to the trailing edge. The radial undulations can have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimeter on at least part of the axial length of the stator. A propulsion assembly formed by the rotor and the stator, and to a turbine engine comprising such assembly is also provided. | 01-07-2016 |
20160003137 | EXHAUST GAS PRESSURE REGULATOR - An exhaust gas pressure regulator for an engine includes an exhaust gas duct delimiting an exhaust was flow path and a regulating member, which is moveable in a first direction in the exhaust gas duct between a first end position, in which the exhaust gas flow path is open for exhaust gas throughflow, and a second end position, in which the regulating member at least substantially closes the exhaust gas flow path for exhaust gas throughflow, wherein the regulating member and the exhaust gas duct are configured for defining an annular gap when the regulating member is positioned in the second end position for allowing exhaust gas to flow through the exhaust gas pressure regulator. | 01-07-2016 |
20160003143 | TURBOMACHINE FAN CLUTCH - A gas turbine engine assembly includes, among other things, a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed. Whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction. When the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction. The clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure. The clutch is removable on-wing. | 01-07-2016 |
20160003148 | METHOD AND DEVICE FOR REGULATING THE COOLING OF OIL IN A TURBOMACHINE - A method for regulating oil cooling within an oil cooling device of a turbomachine including a first heat exchanger mounted in series with a second heat exchanger, the first heat exchanger being an oil/air exchanger while the second heat exchanger is an oil/fuel exchanger, each heat exchanger having an oil inlet and an oil outlet, a bypass directly connecting the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow regulator to regulate the flow rate of oil flowing through the bypass. Circulation of oil though the bypass is allowed by means of the flow regulator when the oil temperature is less than or equal to a predetermined temperature comprised between 70° C. and 90° C., preferably equal to about 80° C. | 01-07-2016 |
20160003187 | GAS TURBINE ENGINE INCLUDING A THIRD FLOWPATH EXHAUST NOZZLE - A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation. | 01-07-2016 |
20160010484 | RING-SHAPED COMPLIANT SUPPORT | 01-14-2016 |
20160010486 | AERO-ACTUATED VANES | 01-14-2016 |
20160010490 | FAN DRIVE THRUST BALANCE | 01-14-2016 |
20160010498 | Intercooled Compressor for a Gas Turbine Engine | 01-14-2016 |
20160010553 | METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER FLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS | 01-14-2016 |
20160010561 | GAS TURBINE ENGINE ACCESSORY GEARBOX | 01-14-2016 |
20160017715 | FAN EXIT GUIDE VANE PLATFORM CONTOURING - A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed. | 01-21-2016 |
20160017743 | ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL - A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position. | 01-21-2016 |
20160017744 | ASSEMBLY - Stator vane assembly includes plurality of vanes arranged in circumferential array, radially proximal mounting portion, radially distal mounting portion, and first latching mechanism. Each of plurality of vanes extends radially between radially proximal mounting portion and radially distal mounting portion, with each of plurality of vanes being pivotally mounted between radially proximal mounting portion and radially distal mounting portion. Plurality of vanes is movable between first arrangement allowing gas to flow across vanes, and second arrangement blocking gas flow across vanes. Pivot axis of each of plurality of vanes is offset from the line of aerodynamic centre of pressure of vane towards trailing edge of vane, and first latching mechanism holds plurality of vanes in first arrangement. Upon receipt of signal, first latching mechanism releases plurality of vanes so that gas flow through vane assembly causes plurality of vanes to move from first arrangement to second arrangement. | 01-21-2016 |
20160017746 | GEARED ARCHITECTURE TO PROTECT CRITICAL HARDWARE DURING FAN BLADE OUT - A turbofan engine including a fan section including a plurality of fan blades rotatable about an axis, a compressor including a plurality of compressor blades, a turbine including a plurality of turbine blades and a geared architecture driven by the turbine for driving the fan section at a speed and direction different than the turbine is disclosed. A rub strip proximate at least one of the compressor blades, the turbine blades and the fan blades slows rotation when engaged. The rub strip generates a torque opposing rotation when in an engaged condition that is between 2 and 6 times a torque encountered in a non-engaged condition. | 01-21-2016 |
20160017812 | GEARED GAS TURBINE ENGINE WITH OIL DEAERATOR - A gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction. The lubrication system includes a lubricant pump supplying a mixed air and oil to a deaerator inlet. The deaerator includes a separator that for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank. The separator includes a member having lubricant flow paths on both of two opposed sides. A method of designing a gas turbine engine is also disclosed. | 01-21-2016 |
20160017862 | INTAKE ASSEMBLIES FOR WIND-ENERGY CONVERSION SYSTEMS AND METHODS - An intake assembly for a wind-energy conversion system has a substantially vertical converging nozzle, an object extending into the nozzle, and a converging flow passage between the object and the nozzle. For some embodiments, the object may be another nozzle. There may be vanes in one or both nozzles in further embodiments. The object may be configured to move in yet other embodiments. | 01-21-2016 |
20160017890 | BEARING ISOLATOR OIL CONTAINMENT CUP - An oil leak prevention device for use on a pump assembly having a non-contacting bearing isolator. The device has an annular surface having a central opening and a second surface extending from the first surface. The second surface covers an opening of an outside leak path between the rotor and the stator of the bearing isolator when the central opening is placed about the shaft of the pump. A method for preventing the leakage of oil from the pump assembly includes forming an oil containment cup and then placing the oil containment cup in contact with the bearing isolator such that a shaft of the pump assembly passes through the central opening and the second surface of the oil containment cup covers the opening of the leak path. Preferably, the cup is removed from the pump before operation of the pump. | 01-21-2016 |
20160024956 | FLOATING BLADE OUTER AIR SEAL ASSEMBLY FOR GAS TURBINE ENGINE - A blade outer air seal (BOAS) assembly for an engine case of a gas turbine engine includes a multiple of supported air seal segments and a multiple of floating air seal segments circumferentially alternate with the multiple of supported air seal segments. | 01-28-2016 |
20160024959 | VARIABLE VANE DRIVE SYSTEM - An example section of a gas turbine engine includes a plurality of variable vanes circumferentially disposed about an engine axis, a first moveable annular ring disposed on an upstream side of the variable vanes, a second movable annular ring disposed on a downstream side of the variable vanes, and a plurality of vane arms, each including a first end secured to the first annular ring and a second end secured to the second annular ring. Movement of the first and second annular rings moves the vane arms, thereby actuating the plurality of variable vanes. An example variable vane assembly includes a vane arm including a portion that engages a variable vane, a first end configured to be secured to a first movable annular ring, and a second end configured to be secured to a second movable annular ring. | 01-28-2016 |
20160024960 | GAS TURBINE AND METHOD FOR OPERATING THE GAS TURBINE - A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced. | 01-28-2016 |
20160024964 | GAS TURBINE ENGINE WITH AIR-OIL COOLER OIL TANK - A thermal management system according to one disclosed non-limiting embodiment of the present disclosure includes an at least partially annular oil tank; and a fan airflow diverter upstream of the cooling fins. | 01-28-2016 |
20160025037 | THRUST REVERSER UNIT - A thrust reverser unit (TRU) | 01-28-2016 |
20160032737 | TURBINE BLADE TIP TREATMENT FOR INDUSTRIAL GAS TURBINES - A method of preventing transfer of metal of a gas turbine rotor blade having a metal tip to a blade outer air seal coating on a gas turbine case includes forming a coating on the metal tip. The coating comprises a bond coat layer on the metal tip and a ceramic filled metallic layer having a ceramic component in a matrix of a metal MCr, MCrAl, MCrAlY or a refractory modified CMCrAlY where M is nickel, cobalt, iron or mixtures thereof. | 02-04-2016 |
20160032758 | SYSTEMS, METHODS, AND APPARATUS FOR ROTARY VANE ACTUATORS - Systems, methods, and devices are disclosed for implementing hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor. | 02-04-2016 |
20160032760 | HOUSING FOR A GAS TURBINE, AIRCRAFT ENGINE, AND A PROCESS FOR OPERATING A GAS TURBINE - A housing for a gas turbine is disclosed. At least one wall element is housed on the housing so as to move, which limits a flow channel of the housing in the radial direction from a rotational axis of a rotor of the gas turbine toward the exterior. The housing includes at least one variably adjustable guide blade which extends through the wall element into the flow channel. The wall element can be moved between a sealing setting, in which the wall element makes contact at least in a partial area of a side of a blade leaf of the guide blade facing toward the wall element, and an open setting, in which the blade leaf and the wall element are spaced some distance apart from one another. A gas turbine as well as a process for operating a gas turbine is also disclosed. | 02-04-2016 |
20160032932 | SYSTEM AND METHOD FOR DETECTING STALL OR SURGE IN RADIAL COMPRESSORS4 - A system and method are provided for detecting an impending stall or surge in a radial compressor. The system and method may include a plurality of detection devices configured to detect a transition of a low momentum zone of a gas flow through the diffuser from a first position adjacent a shroud wall of the diffuser to a second position adjacent a hub wall of the diffuser. The system and method may also include a control system electrically coupled to the plurality of detection devices and configured to receive a plurality of information signals. Each information signal may be transmitted by a respective one of the plurality of detection devices and may correlate to a location of the low momentum zone. The control system may be configured to process the plurality of information signals and detect the impending stall or surge based on the location of the low momentum zone. | 02-04-2016 |
20160040550 | VARIABLE VANE CONTROL SYSTEM - A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes about a second vane axis, the first array of variable vanes axially spaced from the second array of variable vanes, and adjusting the angular deflection of one of the first and second arrays of variable vanes, based on the sensed angular deflections from the other of the first and second arrays of variable vanes. A compressor including the variable vane assembly and a method of operating the variable vane assembly for a compressor are also disclosed. | 02-11-2016 |
20160040552 | MODULATED TURBINE COOLING SYSTEM - A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers , the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath. | 02-11-2016 |
20160040598 | LOW NOISE COMPRESSOR FOR GEARED GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine section having a low pressure turbine, the low pressure turbine for driving the low pressure compressor and the fan; a gear reduction effecting a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor; and at least one stage of the compressor section having a ratio of vanes to blades that is greater than or equal to 1.8. The corrected tip speed of the blades is greater than or equal to 480 ft/sec at an approach speed. | 02-11-2016 |
20160040627 | AERODYNAMIC TRACK FAIRING FOR A GAS TURBINE ENGINE FAN NACELLE - A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent-divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing. | 02-11-2016 |
20160040680 | METHODS AND SYSTEMS FOR ANTISURGE CONTROL OF TURBO COMPRESSORS WITH SIDE STREAM - A method is described for providing antisurge control in a system comprising a compressor having at least an upstream compressor stage, a downstream compressor stage and a side stream bringing flow into a flow passage between the upstream compressor stage and the downstream compressor stage. The method provides for estimating a temperature of a flow delivered by the upstream compressor stage using a non-dimensional performance map of the upstream compressor stage and further estimating a temperature of a flow entering the downstream compressor stage based on the mass flow and flow temperature of the flow delivered by the downstream compressor stage and the mass flow and the flow temperature of the side stream. The method further provides for performing antisurge control of the downstream compressor stage based on the temperature of the flow entering the downstream compressor stage. | 02-11-2016 |
20160047258 | INNER STAGE TURBINE SEAL FOR GAS TURBINE ENGINE - A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal. | 02-18-2016 |
20160047266 | MOVABLE AIR SEAL FOR GAS TURBINE ENGINE - A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment. | 02-18-2016 |
20160047272 | ROTARY MACHINE AIR DEFLECTOR - A rotary machine includes a shaft extending through the rotary machine; a bearing positioned around the shaft; and an air deflector mounted on the shaft between the bearing and the shaft, wherein the air deflector has a first cylindrical body portion that is connected to a second cylindrical body portion with a ramp portion. A method for cooling a bearing positioned around a rotating shaft includes providing air to a cavity that surrounds a rotating shaft; deflecting the air towards an inner surface of a bearing that is positioned radially outward of the rotating shaft, wherein the air is deflected with an air deflector that is mounted on the rotating shaft; and flowing the air between an outer surface of the air deflector and the inner surface of the bearing. | 02-18-2016 |
20160047360 | Method and apparatus to utilize the push-pull power of an upwards flow of wind energy within a structure - Method and apparatus to utilize the push-pull power of an upwards flow of wind energy within a structure with one or more open tops; for ventilation, moisture condensing and producing mechanical energy for useful work, which will include producing electricity. Including a unique application of “Bernoulli's Principal” that allows the maximum amount of wind energy to be captured, channeled and/or concentrated within that structure over its height; to directly operate any number, type, form, size and/or shape of wind powered devices to transform this wind energy into mechanical energy. Then this mechanical energy can be used by machine devices to produce useful work, propel vehicles and/or to condense moisture from humid wind energy through momentum with geometric moisture condensing devices. | 02-18-2016 |
20160047392 | METHODS AND SYSTEMS FOR CONTROLLING TURBOCOMPRESSORS - A method for regulating a turbocompressor to prevent surge, is described. The method comprises the following steps: providing at least one surge limit line of turbocompressor; continuously determining an actual value of a corrected speed of the turbocompressor; continuously determining at least a maximum admissible pressure ratio on the surge limit line, corresponding to the actual value of the corrected speed; continuously determining an actual pressure ratio; acting upon an antisurge arrangement, if the actual pressure ratio is equal to or higher than the maximum admissible pressure ratio. | 02-18-2016 |
20160053626 | GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM WITH AIR SEAL SEGMENT INTERFACE - An active clearance control system of a gas turbine engine includes an air seal segment with a bridge hook having a lugged aperture. | 02-25-2016 |
20160053628 | RAPID RESPONSE CLEARANCE CONTROL SYSTEM FOR GAS TURBINE ENGINE - An active clearance control system for a gas turbine engine includes an air seal segment and a puller engageable with the air seal segment. | 02-25-2016 |
20160053629 | RING SEAL FOR BLADE OUTER AIR SEAL GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM - An active clearance control system for a gas turbine engine includes a ring seal engageable with a multiple of air seal segments. | 02-25-2016 |
20160053692 | ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES - An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move a multiple of contra-rotating variable vanes between an open position and a closed position to throttle an airflow through said multiple of contra-rotating variable vanes. | 02-25-2016 |
20160053739 | SYSTEM AND METHOD FOR ARTIFICIAL GRAVITY FUELED FLUID DYNAMIC ENERGY GENERATOR OR MOTOR - An Artificial Gravity Fueled Fluid Dynamic Day Energy Generator/Motor that initially uses external power to spin a partially submerged low drag fluid distributor rotor that uses centrifugal force to cause fluid to flow from the center of rotation, through a plurality of Euler contoured penstocks, in a true radial direction through a high “g” artificial gravity field, which dramatically increases the fluid's kinetic energy and releases available power, before it is guided out tangentially from the distributor via a plurality of nozzles symmetrically located at a small height just above the reservoir surface (near zero lift). As the frequency of the rotor is increased linearly the fuel Artificial Gravity increases exponentially, as does the fluid dynamic available power Pa. Turbine runners on the rotor assembly capture the available power, and a positive feedback mechanical transmission couples the captured rotational power to the I/O shaft in its initialized direction. | 02-25-2016 |
20160053766 | SURGE PREVENTION APPARATUS AND METHOD FOR CENTRIFUGAL COMPRESSOR - Disclosed herein are a surge prevention apparatus and method for a centrifugal compressor. The surge prevention apparatus includes a control unit for controlling a gas provision operation based on a flow rate and pressure on an inlet side of a compressor and pressure on an outlet side of the compressor, and a gas provision unit for storing a part of gas flowing into the inlet side of the compressor and providing the stored gas to the inlet side in response to a control signal from the control unit. | 02-25-2016 |
20160053767 | INLET BELLMOUTH WITH COATING IN MEASUREMENT ANNULUS REGION - An airflow inlet may include a bellmouth component having a substantially uneven internal surface, and a variable thickness coating in a measurement annulus region of the substantially uneven internal surface. The measurement annulus region includes only an annulus about the internal surface of the bellmouth component. The variable thickness coating is configured to present a more even internal surface than the substantially uneven internal surface. | 02-25-2016 |
20160061053 | OPERATION OF AIRCRAFT ENGINES DURING TRANSIENT CONDITIONS - Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system. | 03-03-2016 |
20160061115 | CORE COWL FOR A TURBOFAN ENGINE - A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described. | 03-03-2016 |
20160068245 | High maneuverability steering system for work boats and other watercraft - A combined Kort nozzle and rudder steering system for vessels requiring a high degree of maneuverability. A Kort nozzle is mounted around the propeller to direct the wash to generate a first turning source, and a rudder is mounted behind the Kort nozzle to react with the wash exiting the nozzle to produce a second turning force. The nozzle and rudder are pivoted in the same directions simultaneously, but with the rudder being pivoted at a faster rate than the nozzle. The nozzle is pivoted to an optimal maximum angle relative to the wash generated by the propeller and the rudder is pivoted to an optimal maximum angle to the wash exiting the nozzle. | 03-10-2016 |
20160069204 | GEARED ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES - An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes. | 03-10-2016 |
20160069205 | TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED UPSTREAM OF THE FAN - Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:
| 03-10-2016 |
20160069268 | ENGINE-INDUCED AIRCRAFT CABIN RESONANCE REDUCTION SYSTEM AND METHOD - A system and method of reducing engine induced aircraft cabin resonance includes sensing the core engine speed of a first turbofan gas turbine engine, and sensing the core engine speed of a second turbofan gas turbine engine. In a control system, the core engine speed of the first turbofan gas turbine engine and the core engine speed of the second turbofan gas turbine engine are processed to determine a core engine speed difference between the first and second turbofan gas turbine engines. The core engine speed difference is processed to supply a variable inlet guide vane (VIGV) offset value. The VIGV offset value is applied to a VIGV reference command associated with one of the first or second turbofan gas turbine engine to thereby cause the VIGVs of one of the first or second turbofan gas turbine engine to move to a more closed position. | 03-10-2016 |
20160069269 | Vibration Damping Apparatus for Hydrostatic Seal of Gas Turbine Engine - A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups. At operational temperatures, the control ring is adapted to become separated from the hydrostatic sea. | 03-10-2016 |
20160069275 | TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED UPSTREAM OF THE FAN - Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:
| 03-10-2016 |
20160084110 | COMPRESSOR WITH A THERMAL SHIELD AND METHODS OF OPERATION - A compressor includes a compressor bundle and an outer casing. Between the outer casing and the compressor bundle a thermal shield is provided, for reducing thermal stress and visco-plastic deformation of the casing under severe operating conditions. | 03-24-2016 |
20160084111 | METHODS AND SYSTEMS FOR PREVENTING LUBE OIL LEAKAGE IN GAS TURBINES - A sump pressurization system comprising an off-board source of pressurized air is provided to supplement pressurized air to a bearing sump arrangement when the operating conditions of the gas turbine engine are such that the on-board pressurized air source, e.g. the compressor of the gas generator, are such that the air pressure generated thereby is insufficient to pressurize a sump pressurization cavity. A gas turbine engine comprising such a sump pressurization system is also provided, as is a corresponding method for operating a gas turbine engine to facilitate reducing leakage of lubrication oil. | 03-24-2016 |
20160084162 | GAS TURBINE ENGINE INLET - An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed. | 03-24-2016 |
20160084218 | Systems and Methods for Hydromotive Machines - Hydromotive machines, e.g. hydroturbines and pumps with integral low head loss shut off valves are described. Arrays of such hydroturbines facilitate power generation within the limited space available at pre-existing gated water control structures. An adjustable pitch hydroturbine runner particularly suited for use with the integral loss shut-off valve provides higher power output and higher specific speed than prior art hydroturbines at low head hydroelectric projects. Arrays of pumps in accordance with the present invention provide high discharge capacity in a limited space, with each individual pump within the array having an integral low head loss valve for shut off and backflow prevention. | 03-24-2016 |
20160084219 | A SUBMERSIBLE HYDROELECTRIC GENERATOR APPARATUS AND A METHOD OF EVACUATING WATER FROM SUCH AN APPRATUS - This invention relates to a submersible hydroelectric generator apparatus ( | 03-24-2016 |
20160084265 | GAS TURBINE ENGINE WITH PARTIAL INLET VANE - A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed. | 03-24-2016 |
20160084268 | SYSTEM AND METHODS FOR REDUCING NOISE IN AN AIR MOVING SYSTEM - A centrifugal blower system includes a centrifugal blower assembly for generating airflow. The centrifugal blower assembly includes a housing, a motor coupled to the housing, and at least one impeller coupled to the motor. A motor controller is coupled to the motor. The motor controller is configured to receive at least one feedback parameter and to transmit instructions to the motor to control an operation of the motor based on the at least one feedback parameter. The operation of the motor is configured to reduce noise in the centrifugal blower system. | 03-24-2016 |
20160090864 | MULTI-FLUID CARGO PUMPS - A submerged electrical pump for liquefied hydrocarbon gasses that is adapted for use encompassing a range of different temperatures and viscosities is disclosed. Notable elements of some embodiments of multiple fluid pumps include bearings and bearing liners made from the same material, a motor larger enough to pump the most vicious and dense fluid, extra thick bearing liners, and a trial-and-error process for choosing other pump design specifications, such as impeller wear rings, bushings, and other critical radial clearances. | 03-31-2016 |
20160090918 | METHOD OF STOPPING A ROTORCRAFT ENGINE IN OVERSPEED, AND A SYSTEM AND A ROTORCRAFT ASSOCIATED THEREWITH - A method of stopping an engine of a rotorcraft in overspeed, the engine comprising a gas generator and a power assembly. When the engine is in operation, the engine is automatically stopped when the following three conditions are satisfied simultaneously: a torque (Tq) measured on the power assembly is below a predetermined torque threshold (Tq | 03-31-2016 |
20160090989 | BLOWER FILTER SYSTEM - A blower filter system ( | 03-31-2016 |
20160097286 | INTERNAL COOLING OF ENGINE COMPONENTS - A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor. | 04-07-2016 |
20160097296 | SYSTEM AND METHOD FOR BLADE TIP CLEARANCE CONTROL - A system includes a turbomachine rotor having a shaft and turbomachine blades coupled to the shaft. The system also includes a turbomachine stator having a shroud surrounding the turbomachine blades of the turbomachine rotor. Further, the system includes a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the system, where the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor. | 04-07-2016 |
20160097328 | ACCESSORY DRIVE SYSTEM FOR A GAS TURBINE ENGINE - The described accessory drive system for a gas turbine engine includes a gearbox driving a plurality of accessories including a cabin air compressor to provide cabin air and an engine starter to start the gas turbine engine. An electrical power supply separate from a main electrical power supply of the gas turbine engine is electrically coupled to the accessories. A clutch selectively engages an output of the gas turbine engine to mechanically couple the output to the gearbox. The clutch operates between an electrical drive state where it disengages from the output and only the electrical power supply provides electrical power to the cabin air compressor and the engine starter, and a mechanical drive state where the clutch engages the output and the gearbox drives at least one of the accessories. | 04-07-2016 |
20160102499 | Improved Turbine - An improved turbine or motor, such as a fluid or liquid driven turbine or motor or hydraulic turbine or motor including a downhole turbine for the oil/gas and geothermal industries, such as a drilling turbine or downhole drilling turbine. The turbine or motor provides a fluid passage comprising at least one portion or zone arranged to cause a drive fluid to be moved or diverted, such as at least partly radially. The turbine or motor may comprise a rotor having a rotor blade extending within the fluid passage. The turbine or motor may comprise a stator having a stator blade extending within the fluid passage. The stator ( | 04-14-2016 |
20160102566 | POWER TURBINE AIR STRUT - A power turbine section for a gas turbine engine includes an inlet case along an axis. An inlet duct within the inlet case is along the axis and an air strut is mounted to the inlet case transverse to the axis to extend through the inlet duct, the air strut includes a multiple of passages. | 04-14-2016 |
20160102571 | AXIAL TURBOMACHINE COMPRESSOR OUTER CASING WITH SEAL - The invention relates to an axial turbomachine compressor outer casing. The casing comprises a sealing device collaborating with a row of rotor blades. The casing comprises a wall with an annular groove in which the sealing device is housed. The sealing device comprises a segmented outer shroud and a plurality of piezoelectric actuators moving the shroud radially in the groove so as to open or close the functional clearance. The invention also proposes a method for controlling a sealing device for a turbojet engine, the method comprising a step of measuring the altitude and a step of adjusting a clearance according to the altitude. | 04-14-2016 |
20160102577 | POWER TURBINE COOLING AIR METERING RING - A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support to form a first annular compartment and a second annular compartment. | 04-14-2016 |
20160102671 | METHOD FOR OPERATING A COMPRESSOR, AND ARRANGEMENT WITH A COMPRESSOR - A method for operating a compressor and arrangement. The method includes: feeding an intake flow into an inlet of the compressor, compressing the intake flow by the compressor to give an outlet flow, introducing at least one first part flow of the outlet flow into a bypass station as first bypass flow, controlling the feeding-in of the first bypass flow from the bypass station into the inlet of the compressor, depending on operating parameters of the compressor, cooling at least one second part flow of the outlet flow, and controlling the feeding-in of the cooled second part flow as second bypass flow into the inlet of the compressor, depending on operating parameters of the compressor. | 04-14-2016 |
20160102676 | FAN AND METHOD OF COOLING A MOTOR - A fan comprises a hub and at least one blade coupled to the hub. The blade comprises an inlet portion and an outlet portion. The inlet portion is defined by a longitudinal axis, an inlet edge, and a portion of a distal edge. The outlet portion is defined by the longitudinal axis, an outlet edge, and another portion of the distal edge. | 04-14-2016 |
20160108751 | A SEAL ASSEMBLY - A seal assembly for restricting fluid leakage flow through a fluid leakage cavity defined between a first component and second component that is rotatable about an axis relative to the first component, the seal assembly comprising a fluid jet outlet configured to admit a fluid jet into the fluid leakage cavity in an upstream direction which is inclined to the axis, a first flow restriction located downstream of the fluid jet outlet and at a location such that the fluid jet admitted from the fluid jet outlet would impinge on the first flow restriction once the fluid jet has turned to flow in an axial direction, and a second flow restriction located downstream of the first flow restriction. An axial flow turbine comprising a turbine rotor mounted within a housing may incorporate such a seal assembly in a fluid leakage cavity defined between the turbine rotor and the housing. | 04-21-2016 |
20160108753 | Insulating Test Engine Hood for a Turbine Engine on a Test Bench - The present application concerns a test engine hood for a turbine engine, such as a double flow turbine. The test hood allows replacement of a flight engine hood during tests on a test bench on the ground where the temperature conditions could damage the flight hood. The test hood includes a tubular wall of carbon-fibre epoxy composite, and metal flanges upstream and downstream. To provide thermal protection, the test hood includes a layer of silicone with a majority of polysiloxane. The layer covers the entire inner surface of the wall to create a barrier. The present application also concerns a method for testing a turbine engine on a test bench, where the turbine engine is fitted with a test casing. The present application also concerns a use of silicone for thermal insulation of the inside of the test hood of the turbine engine on a test bench on the ground. | 04-21-2016 |
20160108756 | TURBO MACHINE AND METHOD FOR OPERATING SUCH TURBO MACHINE - A turbo machine, especially gas turbine, comprises a rotor, which rotates about a horizontal machine axis, and which is enclosed by a coaxial enclosure comprising a metal casing, whereby an electrical heating system is provided on the lower half of said metal casing. A safe operation is achieved by having said heating system configured as a redundant system. | 04-21-2016 |
20160108757 | INTEGRATED OUTER FLOWPATH DUCTING AND FRONT FRAME SYSTEM FOR USE IN A TURBOFAN ENGINE AND METHOD FOR MAKING SAME - A system and method is provided for an integrated aircraft turbofan engine outer flowpath ducting and front frame that minimizes assembly interfaces and reduces overall aircraft engine weight. The system and method provide an integrated turbofan engine outer flowpath ducting and front frame system that decouples the fairing/aerodynamic duties from the struts/weight bearing duties thereby enabling efficient distribution of mechanical load. | 04-21-2016 |
20160108926 | CARTRIDGE SEAL FOR A CENTRIFUGAL PUMP - A cartridge seal for centrifugal pump comprises a shaft tube assembly attached to a structure. A shaft tube of the shaft tube assembly receives a shaft of the centrifugal pump. A shaft collar of the cartridge seal attached to a second end of the shaft tube is in communication with a second end of the structure. A chamber tube of the shaft tube assembly and the shaft tube collectively define a chamber that contains compressed gas. A spring is located in the chamber of compressed gas. The compressed gas and the spring cause the shaft tube assembly to substantially prevent movement of fluids between the shaft and the structure in the centrifugal pump. | 04-21-2016 |
20160115856 | Engine Fan Control System and Method - This document discloses an adaptive fan control system for controlling a fan that cools an engine of a machine. Many machines carry out repetitive tasks or work cycles. The cooling requirements of the engine vary for each portion or segment of a work cycle. The disclosed system includes a controller with a memory having a plurality of stored work cycle patterns. Using a variety of sensors, the system and controller identities the work cycle that the machine is carrying out and, using one of the stored work cycle patterns, the system anticipates the cooling requirements of the machine as the machine progresses through the work cycle and the system proactively changes the fan speed for upcoming segments of the work cycle. | 04-28-2016 |
20160123165 | VARIABLE AREA GAS TURBINE ENGINE COMPONENT HAVING MOVABLE SPAR AND SHELL - A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivot to change a positioning of the shell. | 05-05-2016 |
20160123173 | SYSTEMS AND METHODS FOR CONTROLLING ROTOR TO STATOR CLEARANCES IN A STEAM TURBINE - Systems and methods for controlling a clearance between a rotor and a stator of a steam turbine during transient operations rely upon heating or cooling a shell support structure of the steam turbine that supports the stator of the steam turbine. Selectively heating or cooling the shell support structure makes it possible for thermal growth/contraction rates and magnitudes of the shell support structure to better match the thermal growth/contraction rates and magnitudes of a bearing support structure of the steam turbine during transient operations. As a result, the clearance between the rotor and the stator of the steam turbine can be maintained. | 05-05-2016 |
20160123235 | ARRANGEMENT AND METHOD FOR BLOWING-OFF COMPRESSOR AIR IN A JET ENGINE - An assembly and a method for bleeding of compressor air in an engine is provided. The assembly includes a bleed channel for bleeding compressor air. It is provided that the channel geometry of the bleed channel is adjustable. | 05-05-2016 |
20160123238 | SYSTEM AND METHOD FOR TURBOMACHINERY VANE PROGNOSTICS AND DIAGNOSTICS - One embodiment includes a system including an actuation system of a gas turbine system including an actuator, a positioner including one or more sensors, a motor, and a controller communicably coupled to the positioner and the motor. The actuator is coupled to one or more inlet guide vanes (IGVs) or variable stator vanes (VSVs) and configured to move the IGVs or VSVs, the positioner is configured to position the actuator so that the actuator moves the IGVs or VSVs to a desired angle, the motor is configured to drive the actuator, and the controller is configured to establish one or more baselines for one or more types of data obtained by the sensors at initialization of the gas turbine system, derive a deviation from the baselines, and perform a preventative action if a deviation that meets or exceeds a threshold is derived. | 05-05-2016 |
20160123340 | METHOD OF CONTROLLING AIR BLOWER OF FUEL CELL VEHICLE - A method for controlling an air blower of a fuel cell vehicle includes operating the air blower with a low limit revolutions per minute (RPM), which is calculated based on a vehicle hill-climbing gradient during hill-climbing, without regenerative braking. Accordingly, when reacceleration and additional acceleration are required during hill climbing of the fuel cell vehicle, the fuel cell vehicle ensures high responsibility and launching characteristics. | 05-05-2016 |
20160123341 | CORRECTED RPM CALCULATION METHOD FOR COMPRESSOR, CONTROL METHOD FOR COMPRESSOR, AND DEVICES FOR IMPLEMENTING THESE METHODS - An RPM of a compressor is sensed by an RPM meter, and a sound velocity of an inlet gas sucked into the compressor is sensed by a sound velocity meter. A corrected RPM computation unit finds a corrected RPM of the compressor using a reference state quantity determined by a reference specific heat ratio, a reference gas constant, and a reference temperature of the inlet gas; the RPM sensed by the RPM meter, and the sound velocity sensed by the sound velocity meter. | 05-05-2016 |
20160123347 | LINKAGE TO ACTUATE INLET GUIDE VANES - An actuation linkage assembly may include a first lever arm connected to one end of a shaft, a second lever arm connected at one end to another end of the shaft, a transition linkage connected to the other end of the second lever arm, and a bracket connected to the transition linkage. The transition linkage is configured to connect the bracket on a driver ring and to the shaft to transfer rotational motion about the axis of the shaft, from a linear motion received by an actuator, to a linear motion through the bracket causing rotational motion of the driver ring. The actuation linkage assembly is configured with high mechanical advantage. The actuation linkage assembly can be part of a movable inter-stage vane guide assembly in a compressor such as for example a centrifugal compressor, which may be part of a chiller such as in a HVAC system. | 05-05-2016 |
20160123351 | BOOSTING SYSTEM, AND BOOSTING METHOD OF GAS - A boosting system which boosts a target gas to a pressure which is equal to or greater than a target pressure higher than a critical pressure includes a compression portion which compresses the target gas to an intermediate pressure which is equal to or greater than the critical pressure and is less than the target pressure to generate an intermediate supercritical fluid, a cooling portion which cools the intermediate supercritical fluid generated by the compression portion to a temperature near to a critical temperature to generate an intermediate supercritical pressure liquid, a pump portion which boosts the intermediate supercritical pressure liquid generated by the cooling portion to a pressure which is equal to or greater than the target pressure, and a cooling temperature adjusting portion which adjusts a temperature of the intermediate supercritical pressure liquid generated by the cooling portion in an upstream side of a pump. | 05-05-2016 |
20160130964 | GAS TURBINE ENGINE FLOW CONTROL DEVICE - A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up protruding from the radially outer surface and configured to seal an interrupted surface. | 05-12-2016 |
20160131147 | TURBOCHARGER - A turbocharger for an internal combustion engine has a housing ( | 05-12-2016 |
20160131159 | GAS TURBINE COMPRISING A COMPRESSOR CASING WITH AN INLET OPENING FOR TEMPERING THE COMPRESSOR CASING AND USE OF THE GAS TURBINE - A gas turbine includes at least one rotor assembly and at least one compressor casing. The compressor casing has at least one inner compressor casing chamber for arranging the rotor assembly and at least one outer compressor casing chamber for tempering the compressor casing. The inner and outer compressor casing chambers are separated from each other by a separating casing wall. The outer compressor casing chamber has at least one boundary casing wall. The boundary casing wall and the separating casing wall are oppositely spaced such that the outer compressor casing chamber is formed. The boundary casing wall has at least one inlet opening for leading in an inlet tempering gas flow with tempering gas into the outer compressor casing chamber such that a tangential material temperature variation of the compressor casing is reduced in comparison to a non tempered compressor casing. | 05-12-2016 |
20160138412 | SHROUD SEAL AND WEARLINER - A stator assembly includes a first stator vane sub-assembly with a first platform and a first airfoil extending from the first platform, and a second stator vane sub-assembly with a second platform and a second airfoil extending from the second platform. A gap is defined circumferentially between the first stator vane sub-assembly and the second stator vane sub-assembly. The stator assembly also includes a shroud structure, a first chamber defined between the first platform and the shroud structure, a second chamber defined between the second platform and the shroud structure, and a damper spring seal structure. Also included is a plate having a first portion within the first chamber and a second portion within the second chamber, such that the plate extends from the first chamber across the gap to the second chamber. | 05-19-2016 |
20160138417 | TURBINE AND METHOD FOR DETECTING RUBBING - A turbine, in particular a gas turbine, includes a rotor, a housing spaced from the rotor by a gap, and a system for monitoring structure-borne noise, permit rubbing of the rotor and the housing to be localised with the least possible technical complexity. In both a first and second axial region, one or more inwardly directed rubbing teeth of the housing and one or more outwardly directed rubbing edges of the rotor are arranged, wherein the one or more rubbing teeth and the one or more rubbing edges are distributed along the circumference such that contact of the particular rubbing teeth and rubbing edges at a specified rotational frequency of the rotor occurs at a different frequency in the first axial region than in the second axial region. | 05-19-2016 |
20160138595 | SUBSEA FLUID PROCESSING SYSTEM WITH INTERMEDIATE RE-CIRCULATION - A fluid processing system is provided containing a pump and a fluid reservoir. The pump includes a casing, one or more pump stages, a pump inlet, and a pump outlet. The casing includes one or more slots, with at least one slot configured to extract at least a portion of a multiphase fluid flowing within the pump. The fluid reservoir encompasses at least a portion of the casing and is configured to receive and separate the portion of the multiphase fluid into an extracted liquid phase and an extracted gaseous phase. The fluid reservoir includes a re-circulation conduit disposed proximate to the pump inlet and a discharge device coupled to the re-circulation conduit. The discharge device regulates re-circulation of at least a portion of the extracted liquid phase to the pump via the pump inlet for reducing a gas volume fraction of the multiphase fluid being fed to the pump. | 05-19-2016 |
20160138600 | Fuel Cell System and Method for Controlling Rotational Speed of Air Compressor - A fuel cell system includes an air compressor that supplies oxidant gas to a fuel cell installed in a fuel cell vehicle, a measured rotational speed acquirer that acquires a measured value of rotational speed of the air compressor, and a controller that calculates a rotational speed command value of the air compressor based on required generated power of the fuel cell, calculates a torque command value of the air compressor based on the calculated rotational speed command value and current rotational speed of the air compressor, and controls rotational speed of the air compressor based on the calculated torque command value. The controller estimates the current rotational speed of the air compressor baaed on the measured value of the rotational speed acquired by the measured rotational speed acquirer and a history of the calculated torque command value, and calculates the torque command value by using the estimated rotational speed. | 05-19-2016 |
20160146100 | SYSTEMS AND METHODS FOR A VARIABLE GEOMETRY TURBINE NOZZLE - Various systems and methods are described for a variable geometry turbine. In one example, a nozzle vane includes a stationary having a first cambered sliding surface and a sliding vane having a second cambered sliding surface where the second cambered sliding surface includes a flow disrupting feature in contact with the first sliding cambered surface. The sliding vane may be positioned to slide in a direction from substantially tangent along a curved path to an inner circumference of the turbine nozzle and selectively uncover the flow disrupting feature. | 05-26-2016 |
20160146214 | Nozzle-Shaped Slots in Impeller Vanes - A well fluid centrifugal pump has a number of stages, each of the stages having an impeller and a diffuser. The impeller has vanes curving outward from a central intake area to a periphery of the impeller. Each of the vanes has a convex side and a concave side. An upstream slot and a downstream slot extend through the vane from the convex side to the concave side. Each of the slots has an entrance on the convex side and an exit on the concave side, with the entrance being located upstream from the exit. The entrance has a greater cross-sectional area than the exit to divert well fluid flowing along the convex side to the concave side to remove accumulated gas. | 05-26-2016 |
20160146218 | FAN MODULE - A fan module is provided herein. The fan module includes a fan, a fan diverter, and a guide pin. The fan diverter is formed in the fan module. The fan diverter includes a diverter wall and a torsion spring along the diverter wall to position the diverter wall. The guide pin is connected to the diverter wall. The guide pin is formed to engage with a guide path formed along a chassis bay to position the diverter wall. | 05-26-2016 |
20160146223 | COOLING RACK FAN MODULE AND METHOD OF COOLING - A fan module for a cooling unit includes a housing configured to be secured within the cooling unit. The housing has a first open end and a second open end spaced from the first open end. The fan module further includes a fan assembly secured within the housing at the first open end of the housing. The fan assembly includes a fan support, a fan rotatably coupled to the fan support, and a motor coupled to the fan to drive rotation of the fan. The fan support is configured to support the fan assembly within the housing. The fan module further comprises a noise reduction assembly disposed in the housing adjacent the fan assembly to reduce noise generated by the fan assembly. | 05-26-2016 |
20160152309 | PROPELLING OBJECTS USING A CAUDAL CYCLE | 06-02-2016 |
20160153282 | Stress Reduction For Film Cooled Gas Turbine Engine Component | 06-02-2016 |
20160153291 | COOLING SYSTEM OF A STATOR ASSEMBLY FOR A GAS TURBINE ENGINE HAVING A VARIABLE COOLING FLOW MECHANISM AND METHOD OF OPERATION | 06-02-2016 |
20160153296 | FLOW DISCOURAGER FOR VANE SEALING AREA OF A GAS TURBINE ENGINE | 06-02-2016 |
20160153305 | TUNED ROTOR DISK | 06-02-2016 |
20160153307 | TURBINE BLADE TIP CLEARANCE CONTROL | 06-02-2016 |
20160153311 | BLEED VALVE RESONATOR DRAIN | 06-02-2016 |
20160153362 | TURBOMACHINE BYPASS FLOW DIVERTING ASSEMBLY AND METHOD | 06-02-2016 |
20160153466 | Variable Vane for Gas Turbine Engine | 06-02-2016 |
20160160674 | GAS TURBINE ENGINE FORWARD BEARING COMPARTMENT ARCHITECTURE - A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure is mounted to the front center body case structure to rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed. | 06-09-2016 |
20160160676 | GAS TURBINE ENGINE VARIABLE STATOR VANE - A gas turbine engine includes a stator stage arranged in a core flow path that includes a vane that is configured to be retractable from the core flow path during engine operation. | 06-09-2016 |
20160160685 | ELIMINATIN OF UNFAVORABLE OUTFLOW MARGIN - A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow. | 06-09-2016 |
20160160866 | AIR CYCLE MACHINE SPEED DIAGNOSTIC - A method and apparatus for operating an air cycle machine is disclosed. The apparatus includes a detector for measuring a rotational speed of a component of the air cycle machine. A processor estimates a rate of change of rotational speed of the component from the measured rotational speed and shuts down the air cycle machine when the estimated rate of change of the rotational speed of the component is greater than a selected rate threshold. | 06-09-2016 |
20160160868 | METHODS AND SYSTEMS FOR REAL-TIME COMPRESSOR SURGE LINE ADAPTATION - Methods and systems are provided for adapting a compressor surge line in real-time. In one example, a method may include retarding a surge line in response to a number of surge events greater than a threshold number of surge events, and advancing the surge line in response to a number of aggressive tip-out events, that do not result in surge, greater than a threshold number of tip-out events. | 06-09-2016 |
20160160881 | INLET RAMPS FOR PRESSURE EXCHANGE DEVICES - A system includes a rotary isobaric pressure exchanger (IPX) having an oblique ramp disposed within a fluid inlet of an end cover at an oblique angle configured to direct a fluid toward an interior surface of a channel within a rotor to facilitate rotation of the rotor. In addition, the system may include one or vanes disposed within the fluid inlet to further direct the fluid toward the interior surface. Further, the system may include one or more passages extending from the fluid inlet toward a surface of the end cover that interfaces with the rotor, where the one or more passages utilize the fluid to apply additional force to the rotor to facilitate rotation. | 06-09-2016 |
20160167525 | Cooling Fan Vane Assembly for a Resistor Grid | 06-16-2016 |
20160169003 | COOLING OF ENGINE COMPONENTS | 06-16-2016 |
20160169026 | TIP CLEARANCE CONTROL FOR TURBINE BLADES | 06-16-2016 |
20160169036 | GAS TURBINE ENGINES WITH HEATED CASES | 06-16-2016 |
20160169037 | TURBINE SHROUD SEALING ARCHITECTURE | 06-16-2016 |
20160177757 | AIRFOIL PROFILE-SHAPED SEALS AND TURBINE COMPONENTS EMPLOYING SAME | 06-23-2016 |
20160177772 | THERMAL INSPECTION SYSTEM | 06-23-2016 |
20160177781 | SYSTEM AND METHOD FOR CONTROLLING AN ENVIRONMENTAL CONDITION OF AN ENGINE ELECTRONIC COMPONENT | 06-23-2016 |
20160177814 | Removal of Heat in Exhaust Shielding with Jacket Fluid Cooled Components | 06-23-2016 |
20160177829 | MICROCHANNEL HEAT EXCHANGERS FOR GAS TURBINE INTERCOOLING AND CONDENSING | 06-23-2016 |
20160177833 | ENGINE AND METHOD FOR OPERATING SAID ENGINE | 06-23-2016 |
20160177958 | OPERATING METHOD FOR A PUMP, IN PARTICULAR FOR A MULTIPHASE PUMP, AND PUMP | 06-23-2016 |
20160186587 | BAFFLE FOR GAS TURBINE ENGINE VANE - A vane structure includes an airfoil section with a first inner airfoil wall surface and a second inner airfoil wall surface. A baffle is mounted within the airfoil section between the first inner airfoil wall surface and the second inner airfoil wall surface. | 06-30-2016 |
20160186596 | CLEARANCE CONTROL ASSEMBLY - A clearance control assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clearance control ring to position a blade outer air seal assembly radially relative to a blade tip. The clearance control ring is compression fit to the blade outer air seal assembly. | 06-30-2016 |
20160186600 | VARIABLE AREA TURBINE ARRANGEMENT FOR A GAS TURBINE ENGINE - A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section. | 06-30-2016 |
20160186666 | METHOD AND ASSEMBLY FOR REDUCING SECONDARY HEAT IN A GAS TURBINE ENGINE - A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly. | 06-30-2016 |
20160186667 | GAS TURBINE ENGINE WITH TWO-SPOOL FAN AND VARIABLE VANE TURBINE - A method of operating a gas turbine engine includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust. | 06-30-2016 |
20160186781 | COMPRESSOR SYSTEM WITH FLOAT DRAIN - A compressor system having at least one fluid compressor for compressing a working fluid is disclosed herein. The compressor system can include at least one heat exchanger for removing heat from compressed working fluid. At least one moisture separator can be coupled to the compressor system to separate condensed liquid from the compressed working fluid. A float drain module can be positioned within the moisture separator for receiving the condensed liquid. A float valve and a check valve housed within the float drain module are movable between open and closed positions and cooperate to remove condensed liquid from the working fluid without permitting discharge of gaseous working fluid. | 06-30-2016 |
20160194980 | GAS TURBINE ENGINE COMPONENT PROVIDING PRIORITIZED COOLING | 07-07-2016 |
20160195092 | PERFORMANCE MAP CONTROL OF CENTRIFUGAL PUMPS | 07-07-2016 |
20160195096 | THREE SPOOL GEARED TURBOFAN WITH LOW PRESSURE COMPRESSOR DRIVE GEAR SYSTEM AND MECHANICAL CONTROLLER | 07-07-2016 |
20160201491 | VARIABLE AREA TURBINE ARRANGEMENT WITH SECONDARY FLOW MODULATION | 07-14-2016 |
20160201500 | METHOD FOR OPERATING A STEAM TURBINE WITH TWO STEAM SUPPLY LINES | 07-14-2016 |
20160201511 | SHIELDING POCKETS FOR CASE HOLES | 07-14-2016 |
20160201568 | GEARED GAS TURBINE ENGINE WITH REDUCED OIL TANK SIZE | 07-14-2016 |
20160201648 | SAFETY SYSTEM FOR A WIND TURBINE | 07-14-2016 |
20160252098 | SYSTEMS AND METHODS FOR AXIAL COMPRESSOR WITH SECONDARY FLOW | 09-01-2016 |
20160377026 | EXHAUST NOZZLE CONTROL FOR A GAS TURBINE ENGINE - An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed. | 12-29-2016 |
20160377045 | ENERGY-GENERATING PUMP - A pumping apparatus includes a container positioned over a left column and a right column that contains a first fluid, left and right intake valves that respectively connect the left and right columns to the container, left and right pumps respectively associated with the left and right columns, upper and lower connecting pipes that connect the left and right columns below the container, a plurality of gates positioned at entrances of the upper and lower connecting pipes in each of the left and right columns, a turbine positioned to be driven by fluid flowing through the upper and lower connecting pipes, and a third fluid disposed in the upper and lower connecting pipes, and the left column and a right column. The turbine generates electric power due to the flow of the third fluid through the left and right columns and the upper and lower connecting pipes. | 12-29-2016 |
20170232639 | ACTIVE AND PASSIVE SELF-EVACUATION OF A SELF-PRIMING WATER PUMP | 08-17-2017 |
20170234131 | STEAM TURBINE AND METHOD FOR OPERATING A STEAM TURBINE | 08-17-2017 |
20170234148 | METHOD FOR CARRYING OUT WORK ON A ROTOR AND ASSOCIATED FOIL | 08-17-2017 |
20170234155 | TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN A GAS TURBINE ENGINE | 08-17-2017 |
20170234220 | Acoustic Nozzles For Inlet Bleed Heat Systems | 08-17-2017 |
20170234239 | Acoustic Nozzles for Inlet Bleed Heat Systems | 08-17-2017 |
20170234302 | INNOVATIVE WIND TURBINE CONSTRUCTION FOR 100% ENERGY INDEPENDENCE OR EVEN BEING ENERGY POSITIVE | 08-17-2017 |
20170234321 | Load Sharing Spring for Tandem Thrust Bearings of Submersible Pump Assembly | 08-17-2017 |
20170234330 | FAN NOISE REDUCTION USING AN ADAPTIVE HELMHOLTZ CHAMBER | 08-17-2017 |
20180023407 | GAS TURBINE ENGINE TURBINE VANE BAFFLE AND SERPENTINE COOLING PASSAGE | 01-25-2018 |
20180023410 | ENGINE, ROTARY DEVICE, POWER GENERATOR, POWER GENERATION SYSTEM, AND METHODS OF MAKING AND USING THE SAME | 01-25-2018 |
20180023416 | SYSTEMS AND METHODS FOR COOLING COMPONENTS WITHIN A GAS TURBINE ENGINE | 01-25-2018 |
20180023595 | HIGH PRESSURE CYCLONIC SEPARATOR FOR TURBOMACHINERY | 01-25-2018 |
20190145419 | Controlling a Wet Gas Compression System | 05-16-2019 |
20220136458 | Cooling Method for a High-Temperature Radial Gas Turbine Engine - A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction. | 05-05-2022 |