| Entries |
| Document | Title | Date |
|---|
| 20080219836 | Fan with heat dissipating outlet guide vanes - A method for designing a fan having a motor which drives an impeller comprises providing an outlet guide vane assembly which includes a hub and a plurality of guide vanes that extend radially outwardly from the hub, attaching the hub to the motor, determining an approximate amount of heat which is generated by the motor during operation of the fan, determining an approximate surface area which is required to dissipate the heat into a surrounding air stream, and configuring the guide vanes to comprise a total surface area which is approximately equal to the required surface area. In this manner, the heat generated by the motor during operation of the fan can be dissipated by the guide vanes. | 09-11-2008 |
| 20080240911 | HEAT INSULATING STRUCTURE FOR EXPANSION TURBINE, AND METHOD OF MANUFACTURING THE SAME - A heat insulating structure for an expansion turbine includes an adiabatic expansion device including an expander body that includes an outlet passage for refrigerant fluid at a central portion thereof and an introduction chamber for refrigerant fluid communicating with an inlet of the outlet passage on an outer peripheral portion thereof, and a turbine impeller that is rotatably provided at the inlet and braked by a braking device. The adiabatic expansion device adiabatically expands refrigerant fluid by rotating the turbine impeller with refrigerant fluid that flows from the introduction chamber to the outlet passage side. A heat-insulating layer, which surrounds the entire periphery of the outlet passage over the entire length of the introduction chamber, is formed between the introduction chamber and the outlet passage. Accordingly, it is possible to improve turbine efficiency by reducing transfer of heat of refrigerant fluid from the introduction chamber to the outlet passage. | 10-02-2008 |
| 20080260524 | HEAT SHIELD FOR SEALING A FLOW CHANNEL OF A TURBINE ENGINE - A heat shield arrangement for local separation of a flow channel within a turbine engine, with respect to a stator housing radially surrounding the flow channel is provided. The heat shield includes two axially opposite joining contours which are each engageable with two components which are axially adjacent along the flow channel. Each provides a complementary reception contour for the joining contours. At least one of the reception contours has an axial clearance, in which the associated joining contour is axially displaceably mounted. At least one seal is provided between the axially displaceable joining contour and the reception contour. The seal is mounted movably within the reception contour or the joining contour in such a way that the seal is deflectable against a surface region of the reception contour or of the joining contour. | 10-23-2008 |
| 20080298957 | INLET AIR CONDITIONING SYSTEM - An embodiment of the present invention provides an air conditioning system located upstream of the inlet system for a gas turbine. The air conditioning system may comprise at least one conditioning module for adjusting the temperature of the airstream. The at least one conditioning module may have a plurality of forms including at least one of the following systems: a chiller, an evaporative cooler; a spray cooler, or combinations thereof. The specific form of the at least one conditioning module may be determined in part the configuration of the gas turbine. | 12-04-2008 |
| 20080310954 | PUMP HAVING HEAT-DISSIPATING MECHANISM - A pump includes a DC motor ( | 12-18-2008 |
| 20090035128 | COOLED TURBINE BLADE FOR A GAS TURBINE AND USE OF SUCH A TURBINE BLADE - An aspect of the invention is a turbine blade for a gas turbine, comprising a blade root, adjoining which one after the other are a platform region having a transversely running platform and then a blade profile curved in the longitudinal direction, comprising at least one cavity which is open on the root side and through which a coolant can flow and which extends through the blade root and the platform region into the blade profile. The cavity is surrounded by an inner wall, on the surface of which structural elements influencing the coolant are provided. In order to prolong the service life of such a turbine blade, the invention proposes that a section, lying at least in the blade profile and adjoining the platform region, of the surface of the inner wall be free of structural elements. Such a turbine blade can preferably be used in a stationary gas turbine | 02-05-2009 |
| 20090041578 | Component of a Steam Turbine Plant, Steam Turbine Plant, Application, and Production Method - The aim of the invention is to provide a superheated component of a steam turbine installation with high thermal and mechanical resistance. To this end, the component comprises a lining applied to a body of the component, on a hot side facing a steam chamber, said lining being adapted to the contour of the component body. According to the invention, the lining comprises a number of moulded parts, each moulded part comprising a metallic and ceramic composite layer formed from at least one metallic layer and at least one ceramic layer. The ceramic layer is used especially as a insulating layer, and the metallic layer is especially used as a support or for protection against abrasion and/or erosion. | 02-12-2009 |
| 20090060725 | Engine with intake air temperature control system - A gas turbine engine system includes a gas turbine engine using vaporized liquefied gas as fuel. The gas turbine engine is configured to ingest intake air from an intake port and direct exhaust gases to an exhaust port. The gas turbine engine system also includes a heat exchanger with a heat transfer fluid therein. The heat exchanger is configured to create at least a part of the fuel by heating the liquefied gas. The gas turbine engine system also includes an intake air temperature control circuit. The intake air temperature control circuit includes conduits configured to direct the heat transfer fluid to the intake port and the exhaust port. The gas turbine engine system also includes a control system configured to selectively direct the heat transfer fluid to one of the intake port and the exhaust port. | 03-05-2009 |
| 20090067999 | EXTENDED IMPINGEMENT COOLING DEVICE AND METHOD - An extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall and the impingement sheet. The baffle has a collector plenum area that receives impingement cooling air from the air supply plenum and a channel in fluid communication with the collector plenum and extending outside the air supply plenum with openings to allow impingement cooling air to pass therethrough and having a series of lands extending into the channel wherein the lands are located in proximity to impingement cooling air outlets in the inner wall. | 03-12-2009 |
| 20090123273 | TURBINE OR COMPRESSOR STAGE FOR A TURBOJET - A turbojet turbine or compressor stage, comprising at least one rotor disk mounted inside a sectorized ring ( | 05-14-2009 |
| 20090136340 | HYDRODYNAMISCHE MASCHINE, INSBESONDERE HYDRODYNAMISCHE KUPPLUNG EINES TURBOCOMPOUNDSYSTEMS - A hydrodynamic machine, and especially a hydrodynamic coupling, for a turbine compound system includes (a) a bladed primary wheel and a bladed secondary wheel which together form an operating space which is filled or can be filled with operating medium, and (b) a housing which encloses the primary wheel and the secondary wheel and which is manufactured from sheet metal. The housing is manufactured from at least two separate sheet metal components which are placed on the primary wheel and/or the secondary wheel, are aligned with each other at a joint abutment location and are welded together. In the area of the welded joint abutment, a relief which is open toward the joint abutment is provided and which extends along the joint abutment in the surface of the primary wheel and/or the secondary wheel. | 05-28-2009 |
| 20090148280 | Turbine Vane for a Gas Turbine Engine - A turbine vane for a gas turbine engine having an outer wall of nonuniform thickness. The turbine vane may be formed from a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned internally of the outer wall. The outer wall may be formed of a non-uniform thickness such that aspects of the outer wall positioned between an outboardmost portion of the outer wall and an inboardmost portion of the outer wall are thinner than the outboardmost and inboardmost portions of the outer wall. | 06-11-2009 |
| 20090185898 | TURBINE CASING WITH FALSE FLANGE - A turbine casing may include an outer surface with a false flange and an inner surface with a heat sink positioned adjacent to the false flange. | 07-23-2009 |
| 20090196744 | FAN AND IMPELLER THEREOF - A fan includes a frame, a motor and an impeller. The motor is disposed on the frame and coupled to the impeller to drive the impeller to rotate. The impeller includes a hub, a plurality of blades and an air exhausting structure. The hub has an opening formed on a top portion of the hub. The blades are disposed around the hub. The air exhausting structure is disposed in the opening for discharging hot airs generated by the motor out of the hub. | 08-06-2009 |
| 20090232644 | CMC VANE INSULATOR AND METHOD OF USE - A method for assembling a gas or steam turbine is provided. The method includes providing an insulator and positioning the insulator between a vane support and a vane such that the insulator facilitates preventing hot gas migration into the vane, and such that during operation, hot gas is channeled from a high pressure side of the vane to a low pressure side of the vane. A vane assembly for a turbine rotor assembly is also provided. The vane assembly includes a vane support and an insulator including a projecting portion. The assembly also includes a vane. The insulator is coupled to the vane support such that the projecting portion is between the vane and a nozzle support strut to facilitate hot gas flow from a pressure side of the projecting portion to a suction side of the projecting portion. | 09-17-2009 |
| 20090232645 | BLOWER APPARATUS - The invention relates to a blower apparatus with an electric motor, which drives a blower wheel, is arranged in a motor housing and has a commutator with at least two brushes, which form in each case an associated brush bearing face with respect to the commutator, wherein a cooling air flow for cooling the electric motor is diverted into a cooling air channel of the motor housing by a blower air flow produced by the blower wheel. The invention is based on the object of designing the motor cooling system of the blower apparatus of the generic type in such a way that it is more efficient. The object is achieved by virtue of the fact that the cooling air channel has an air distributor, which splits the cooling air flow into at least two cooling air subflows, which are in each case supplied to one of the brush bearing faces directly and in targeted fashion. | 09-17-2009 |
| 20090232646 | Use of a Thermal Barrier Coating for a Housing of a Steam Turbine, and a Steam Turbine - The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behaviour of different components based on different heatings of the components. | 09-17-2009 |
| 20090263237 | Coated turbine component and method of coating a turbine component - Turbine components with different types of coatings on different parts thereof are described. The coatings are chosen such that they are especially adapted to the thermal and corrosive conditions being present on the parts of the component during use. A method to coat a turbine component is also described. | 10-22-2009 |
| 20090280005 | Use of a Thermal Barrier Coating for a Housing of a Steam Turbine, and a Steam Turbine - The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behaviour of different components based on different heatings of the components. | 11-12-2009 |
| 20090297342 | GAS TURBINE ENGINE HAVING A COOLING-AIR NACELLE-COWL DUCT INTEGRAL WITH A NACELLE COWL - A gas turbine engine includes an engine core extending along a core axis, a cooling-air delivery duct on the engine core, and a removable nacelle cowl overlying the engine core. A cooling-air nacelle-cowl duct delivers cooling air to the cooling-air delivery duct. At least a portion of the length of the cooling-air nacelle-cowl duct is integral with the nacelle cowl and not directly supported on the engine core. | 12-03-2009 |
| 20090317243 | HIGH REFLECTIVITY INFRARED COATING APPLICATIONS FOR USE IN HIRSS APPLICATIONS - The present invention is a hover infrared suppression system for a gas turbine engine comprising a hover infrared suppression system having an upstream first stage, a second stage downstream of the first stage and a third stage downstream of the second stage, the engine operating at a temperature sufficient to cause the hover infrared suppression system to emit infrared radiation. The present invention further comprises a high reflectivity coating applied over a preselected area of at least one of the stages of the hover infrared suppression system to reduce the infrared radiation emitted from the engine, the high reflectivity coating being fired after application. | 12-24-2009 |
| 20090317244 | GAS TURBINE ENGINE WITH IMPROVED THERMAL ISOLATION - A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening. | 12-24-2009 |
| 20100003127 | AIR COOLED BUCKET FOR A TURBINE - A bucket for a turbine is described. The bucket includes a dovetail portion configured to couple the bucket to a turbine wheel, the dovetail portion having a lower surface. The bucket also includes a shank portion that extends from the dovetail portion and an airfoil having a root and a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I. The bucket also includes a plurality of cooling passages. The plurality includes no more than five cooling passages that extend between the root and the tip portion of the airfoil. Each of the cooling passages exits the airfoil at the tip portion, the plurality of cooling passages are positioned in a camber line pattern. | 01-07-2010 |
| 20100008770 | PROTECTION OF THERMAL BARRIER COATING BY A SACRIFICIAL COATING - According to an embodiment of the invention, an article of manufacture for use in a gas turbine engine is disclosed. The article comprises a part having a surface covered with a ceramic thermal barrier coating. The thermal barrier coating has an outer surface covered with a sacrificial phosphate coating, wherein the sacrificial phosphate coating reacts with contaminant compositions to prevent contaminant infiltration into the thermal barrier coating. | 01-14-2010 |
| 20100014962 | TURBINE VANE OF A GAS TURBINE - A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable. | 01-21-2010 |
| 20100021289 | Method for applying a NiA1 based coating by an electroplating technique - The present invention provides a coated article made using a plating process, either electroless or electrolytic, whereby nickel is plated on the article using a solution that includes a suspension of powders or containing one or more of the following elements: Ni, Cr, Al, Zr, Hf, Ti, Ta, Si, Ca, Fe, Y and Ga. Optionally, the coating is then heat treated at a temperature above about 1600.degree. F. for an effective amount of time to allow to homogenize the coating by allowing effective interdiffusion between the species. The level of aluminum may be altered to produce a coating of the predominantly beta phase of the NiAl alloy composition. Optionally, a TBC layer is applied over the predominantly beta phase NiAl alloy composition metallic bond coat. | 01-28-2010 |
| 20100028138 | VENTILATION OF A DOWNSTREAM CAVITY OF AN IMPELLER OF A CENTRIFUGAL COMPRESSOR - A system for ventilating a downstream cavity of an impeller of a centrifugal compressor in a turbomachine, this cavity being delimited by the downstream face of the impeller and by an annular end-piece of a diffuser and being ventilated by taking air from the outlet of the compressor, the system comprising at least one annular deflector mounted in this cavity in order to oppose the rise of hot air along the downstream face of the impeller and in order to cause the diverted hot air to be driven by the air taken from the outlet of the compressor. | 02-04-2010 |
| 20100034647 | Processes for the formation of positive features on shroud components, and related articles - A process for the formation of positive features on the surface of a turbine shroud component is described. The process involves applying a feature-forming material to a selected portion of the component surface with a laser consolidation apparatus, according to a pre-selected shape and size for the positive features. A gas turbine engine, comprising a shroud component which contains positive features formed according to embodiments of this process, represents another embodiment of this invention. Methods for modifying the shape of at least one positive feature on a surface of a shroud component are also described. | 02-11-2010 |
| 20100040459 | FILM COOLING STRUCTURE - A film cooling structure | 02-18-2010 |
| 20100047063 | Use of a Tungsten Bronze Structured Material and Turbine Component with s Thermal Barrier Coating - A tungsten bronze structured ceramic material as a thermal barrier coating is described wherein the tungsten bronze structured ceramic coating material has the formula AO—B | 02-25-2010 |
| 20100054925 | Apparatus and Method for Reducing the Pressure on a Joint Between at Least Two Delimiting Parts - An apparatus, especially a steam turbine, including a first delimiting part and a second delimiting part is provided. The delimiting parts are attached to one another forming a joint and enclosing at least a part of a first pressure chamber. A shielding element is also provided on the sides of the delimiting parts facing towards the first pressure chamber and is arranged to form a seal completely covering the joint, so that a cavity is formed between the delimiting parts and the shielding element. A line is routed in the cavity connecting the cavity to a second pressure chamber. In addition, a method for decreasing the force acting on a joint, which is formed by the joining together of a first delimiting part and a second delimiting part of an apparatus, especially a steam turbine, and for reducing the attachment forces acting on the joint is provided. | 03-04-2010 |
| 20100068043 | COOLING STRUCTURE FOR OUTER SURFACE OF A GAS TURBINE CASE - A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached to the outer case surface and extends over the channel portion to define an enclosed cooling passage along the outer case surface. At least one inlet passage and at least one outlet passage are provided in fluid communication with the enclosed cooling passage to convey air to and from the cooling passage. | 03-18-2010 |
| 20100074735 | Thermal Shield at Casing Joint - A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components. | 03-25-2010 |
| 20100086395 | Cooling Fan with Oil-impregnated Bearing - A cooling fan with oil-impregnated bearing includes a base portion, a bearing, a fan hub, and a coil assembly. The base portion has a forward extended bearing housing, into which the bearing is tightly fitted with a colloidal material applied between them. The fan hub is mounted on and around the bearing housing, and has a rearward extended rotary shaft extended through a centered shaft hole of the bearing. An oil receiving space is formed on a wall of the shaft hole at a predetermined position. The coil assembly is externally tightly fitted around the bearing housing with a colloidal material applied between them. With the colloidal material, the bearing and the coil assembly can be associated with the bearing housing without detriment to the effective porosity of the bearing and the dimensional precision of the bearing housing. The oil receiving space also prevents the lubricating oil from leaking out. | 04-08-2010 |
| 20100104429 | DEVICE FOR TAPPING COOLING AIR IN A TURBOMACHINE | 04-29-2010 |
| 20100104430 | Component with a Protective Layer - The invention relates to a component having a substrate and a protective layer, which consists of an intermediate NiCoCrAlY layer zone on or near the substrate and an outer layer zone which is arranged on the intermediate NiCoCrAlY layer zone, which is characterized in that the intermediate NiCoCrAlY layer zone comprises of (in wt %): 11-13% Co, 20-23% Cr, 10.2-11.5% Al, 0.3-0.5 Y, 1.0-2.5% Re and Ni balance. | 04-29-2010 |
| 20100111679 | Asymmetrical gas turbine cooling port locations - A method is disclosed for improving a turbine's thermal response during transient and steady state operating conditions in which the flow of cooling fluid in the turbine's casing is caused to be asymmetrical relative to the horizontal and vertical symmetry planes of the casing so that the turbine's cooling symmetry planes are rotated relative to its geometric symmetry planes and thereby the heat transfer at locations in the casing with increased mass is increased. | 05-06-2010 |
| 20100111680 | Delivery Pump - A delivery pump for conveying a liquid between a pump inlet and a pump outlet, the pump being constructed as a single-stage centrifugal pump with a radial impeller ( | 05-06-2010 |
| 20100129207 | STEAM TURBINE - A steam turbine ( | 05-27-2010 |
| 20100135776 | COOLING SYSTEM FOR A TURBOMACHINE - An embodiment of the present invention may provide an integrated cooling system for multiple compartments of a turbomachine. The cooling system, in accordance with embodiments of the present invention, may provide the following benefits to the user. Improvement on the combined cycle efficiency and an increase in the power output. This may result from reducing the exhaust dilution losses and reducing the parasitic load by requiring fewer air circulation devices. The present invention may also benefit the user by reducing the installation and start-up costs of the cooling system by requiring fewer air circulation devices and integrating the cooling systems. The present invention may circulate a cooling fluid through an integrated cooling circuit, which may be in fluid communication with each compartment of the multiple compartment of the turbomachine. | 06-03-2010 |
| 20100150704 | WIND TURBINE WITH A REFRIGERATION SYSTEM AND A METHOD OF PROVIDING COOLING OF A HEAT GENERATING COMPONENT IN A NACELLE FOR A WIND TURBINE - The invention provides a wind turbine wind turbine with two vessels, each being interchangeably in thermal communication with a heating medium which transfers heat from a heat generating structure to the vessel, and with a cooling medium which transfers heat from the vessel to an ambient space. The vessels form a compression structure which form part of a refrigerating circuit which can circulate a working fluid between the compression structure, a condenser and an evaporator. At the evaporator, cooling effect is obtained based on evaporation of a working fluid, and the cooling can be utilized for cooling a heat generating component in the wind turbine. | 06-17-2010 |
| 20100172746 | METHOD AND APPARATUS FOR COOLING A TRANSITION PIECE - Disclosed is a compressor discharge can including a transition piece and a flow redirector located about the transition piece, defining an airflow space therebetween, the flow redirector configured to reduce recirculation of flow in the airflow space. | 07-08-2010 |
| 20100172747 | PLASMA ENHANCED COMPRESSOR DUCT - A compression system is disclosed, comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a transition duct capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct. | 07-08-2010 |
| 20100178161 | Compressor Clearance Control System Using Bearing Oil Waste Heat - The present application provides a compressor clearance control system for a gas turbine engine having an oil recirculation system with a flow of oil therein 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 a conduit in communication with the casing heat exchanger and the oil recirculation system so as to heat the casing of the compressor with the flow of oil from the oil recirculation system. | 07-15-2010 |
| 20100196148 | TURBOMACHINE - A turbomachine comprises a housing ( | 08-05-2010 |
| 20100221103 | TURBOMACHINE - A turbomachine is provided. The turbomachine includes a rotor, a stator and a plurality of blade discs mounted on the rotor. The rotor includes a turbulator cylinder where a plurality of turbulators are provided on a curved surface of the turbulator cylinder and the stator includes an annular shroud extending around the turbulator cylinder. The plurality of turbulators increase a heat transfer to a coolant flowing between the adjacent opposed surfaces of the turbulator cylinder and the annular shroud. | 09-02-2010 |
| 20100226761 | Turbine Airfoil with an Internal Cooling System Having Enhanced Vortex Forming Turbulators - A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The cooling channel may also include a plurality of vortex enhancers protruding from an inner surface forming the cooling channel and positioned nonparallel to the turbulators. In one embodiment, the vortex enhancers may be positioned generally orthogonal to the turbulators. The configuration of turbulators and vortex enhancers creates a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance. | 09-09-2010 |
| 20100232944 | METHOD AND APPARATUS FOR GAS TURBINE ENGINE TEMPERATURE MANAGEMENT - A turbine engine has a compressor for delivery of compressed air to a combustor. The combustor delivers hot combustion gas through an outlet to a turbine. The turbine includes a nozzle assembly, downstream turbine blades, and shroud assemblies adjacent radially distal ends of turbine rotor blades. The nozzle and shroud assemblies include internal cooling passages for receiving compressed air from the compressor and, cooling air apertures opening through walls of the vanes and shrouds into the hot gas path to release film cooling air. The number of apertures, the aperture area, and the aperture pattern are varied in relation to the circumferential temperature profile of the combustion gas with a higher aperture area and/or higher number of apertures in high temperature regions and a lower aperture area and/or lower number of apertures in low temperature regions. | 09-16-2010 |
| 20100232945 | TURBOMACHINE INLET HEATING SYSTEM - A turbomachine system includes a compressor having a compressor intake and a compressor extraction outlet, and an inlet system fluidly connected to the compressor intake and the compressor extraction outlet. The inlet system includes a plenum having a first end portion that extends to a second end portion through an intermediate portion. The inlet system also includes a heating system having a plurality of conduits extending horizontally through the intermediate portion of the plenum and arranged in a vertical relationship. Heated air from the compressor extraction outlet passes through the plurality of conduits and raises a temperature of ambient air passing through the plenum and into the compressor intake. | 09-16-2010 |
| 20100232946 | DIVOTED AIRFOIL BAFFLE HAVING AIMED COOLING HOLES - A baffle insert for an internally cooled airfoil comprises a liner, a divoted segment and a plurality of cooling holes. The liner has a continuous perimeter formed to shape a hollow body having a first end and a second end. The divoted segment of the hollow body is positioned between the first end and the second end. The plurality of cooling holes is positioned on the divoted segment to aim cooling air exiting the baffle insert at a common location. | 09-16-2010 |
| 20100232947 | IMPINGEMENT COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE - There is disclosed an impingement cooling arrangement for a gas turbine engine ( | 09-16-2010 |
| 20100260598 | THERMAL CONTROL SYSTEM FOR TURBINES - A thermal control system for a turbine casing ( | 10-14-2010 |
| 20100266394 | FAN SHAFT SEAT STRUCTURE - A fan shaft seat structure including a shaft bushing and a heat dissipation member. The shaft bushing has an open end, a closed end and a, connection section. A receiving space is defined between the open end and the closed end. The connection section extends from the closed end in a direction reverse to the receiving space. The heat dissipation member has a first face and a second face. The first face is flush with a first end of the connection section in contact with the closed end of the shaft bushing. The second face is flush with a second end of the connection section. The shaft bushing is integrally connected with the heat dissipation member to increase heat dissipation area and save working time and manufacturing cost as well as achieve better heat dissipation effect. | 10-21-2010 |
| 20100278640 | TURBINE ENGINE HAVING COOLING GLAND - In one embodiment, a turbine may include a bearing housing for a rotor with a passage along an axis of rotation of the rotor shaft. A cooling gland configured to transfer cooling fluid to the passage may be mounted to the bearing housing with a mounting structure configured to mount the cooling gland substantially in-line with the passage of the rotor. | 11-04-2010 |
| 20100278641 | LINER FOR A TURBINE SECTION, A TURBINE SECTION, A GAS TURBINE ENGINE AND AN AEROPLANE PROVIDED THEREWITH - A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed. | 11-04-2010 |
| 20100284798 | Turbine Airfoil With Dual Wall Formed from Inner and Outer Layers Separated by a Compliant Structure - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer. | 11-11-2010 |
| 20100284799 | METHOD AND APPARATUS FOR TURBINE ENGINES - A method for sealing a gas turbine engine includes coupling a turbine bucket to a rotor wheel and forming an interface region therebetween. A cooling air passage is defined in a portion of the rotor wheel and a cooling air manifold is defined in a portion of the turbine bucket. The method also includes inserting a seal tube within at least a portion of the cooling air passage. The method further includes coupling the cooling air passage, the seal tube, and the cooling air manifold in flow communication to at least partially define a turbine bucket cooling system. The method also includes operating the gas turbine engine such that the rotor wheel and the turbine bucket are rotated, thereby inducing a pressure on the seal tube to substantially decrease air flow discharged from the turbine bucket cooling system through the interface region. | 11-11-2010 |
| 20100316491 | THERMAL INSULATION STRUCTURE FOR STRUCTURAL MEMBER, AND SCROLL STRUCTURE - To provide a thermal insulation structure for a structural member and a scroll structure which can be easily used even in integrally constructed structural members and which can ensure reliability and thermal insulation properties. Provided are securing portions ( | 12-16-2010 |
| 20110008155 | HEAT TRANSFER PASSAGE - This invention relates to heat transfer passage ( | 01-13-2011 |
| 20110014036 | HEAT SHIELD AND TURBOCHARGER HAVING A HEAT SHIELD - A heat shield, in particular for a turbocharger, has a disk or a pot shape which is stepped once or multiple times. The disc or pot shape has an outer edge, and the outer edge is provided with at least one opening section. The opening section forms a web section with the outer edge, said web section being bent outward in order to form a spring arm. The web section is either designed as closed or as open at one point. | 01-20-2011 |
| 20110033284 | STRUCTURALLY DIVERSE THERMAL BARRIER COATINGS - A coated article includes an article having at least one surface and a thermal barrier coating system disposed upon the at least one surface. The thermal barrier coating system has at least two layers, with each layer having a different microstructure. The microstructure of each layer may be any one of the following: columnar, amorphous, randomized, and splat-like. The thermal barrier coating system typically exhibits a thermal conductivity of no more than 16 BTU in/hr ft | 02-10-2011 |
| 20110038719 | SIMPLIFIED HOUSING FOR A FUEL CELL COMPRESSOR - A compressor includes a shaft assembly including a thrust disk disposed on a main shaft and a housing having a first portion and a second portion, the first and second portions adapted to receive the shaft assembly and enclose the shaft assembly therebetween, wherein the shaft assembly is rotatably disposed within the housing, and wherein at least one of the first portion and the second portion includes a shaft assembly retention feature for receiving the thrust disk to regulate a motion of the shaft assembly. | 02-17-2011 |
| 20110038720 | FAN AND FAN ASSEMBLY - An assembly includes a fan and a heat sink for detachably fixing the fan. The fan includes a pair of first and a pair of second sidewalls, with two pair of rims respectively extending from the first and second sidewalls. Ends of the rims of the first sidewalls, which are directed toward and are adjacent to a same one of the second sidewalls, each have a latch flange. Ends of the rims of the second sidewalls, which are directed toward and are adjacent to a same one of the first sidewalls, each have a latch flange. The heat sink includes a channel for slidably receiving one pair of rims of the first or second sidewalls, a blocking member disposed at one end of the channel to block a corresponding sidewall of the fan, and a latch member disposed at the other end of the channel to latch the corresponding latch flanges. | 02-17-2011 |
| 20110044805 | COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas. | 02-24-2011 |
| 20110058934 | Cooled Turbine Airfoil Fabricated From Sheet Material - A turbine airfoil ( | 03-10-2011 |
| 20110070075 | FASTBACK TURBULATOR STRUCTURE AND TURBINE NOZZLE INCORPORATING SAME - A heat transfer apparatus, includes a member defining a wall exposed to fluid flow in a predetermined direction of flow; and a plurality of turbulators disposed on the wall. Each turbulator includes an upright front face which generally faces the direction of flow, and a back face which defines a ramp-like shape tapering from the front face to the wall. | 03-24-2011 |
| 20110097199 | SYSTEM AND METHOD TO INSULATE TURBINES AND ASSOCIATED PIPING - An insulation system includes at least one turbine insulation compartment configured to enclose at least a portion of a turbine; an insulation storage compartment configured to store a supply of insulation; a plurality of first pipes that connect to the turbine insulation compartment and the insulation storage compartment; and a blower configured to generate a flow of air in at least one first pipe to pneumatically convey insulation between the insulation storage compartment and the at least one turbine insulation compartment. A method of insulating at least a portion of a turbine includes enclosing at least a portion of the turbine in a compartment; and conveying insulation into the compartment. | 04-28-2011 |
| 20110110771 | AIRFOIL HEAT SHIELD - Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil. | 05-12-2011 |
| 20110110772 | Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same - A turbine airfoil has an airfoil-shaped core and a skin extending about the outer peripheral surface of the core. The core and/or the skin are configured such that a plurality of cooling channels is formed between them. In one embodiment, the cooling channels are formed by a plurality of radially extending channels in the core. In another embodiment, the cooling channels are formed by providing a wave-shaped skin such that, when the skin is attached to the outer peripheral surface of the core, the cooling channels can be formed in the space between the outer peripheral surface of the core and each wave of the skin. Such airfoil constructions can allow the inclusion of different materials in the airfoil. Further, such constructions can allow greater flexibility in the formation of cooling channels. Moreover, such constructions can help to achieve thinner outer walls and near surface cooling of the airfoil. | 05-12-2011 |
| 20110116912 | ZONED DISCONTINUOUS COATING FOR HIGH PRESSURE TURBINE COMPONENT - A turbine component has an airfoil extending between a leading edge and a trailing edge, and has an outer surface. A coating includes at least two discontinuous areas that are spaced from each other such that there is an area of uncoated surface between the discontinuous areas of coating. In addition, a method of providing such a coating is disclosed. | 05-19-2011 |
| 20110123318 | HEAT TRANSFER DEVICE IN A ROTATING STRUCTURE - A cooling system includes a moving rotor system which in turn includes: a rotating disk on which a plurality of heat conducting structures are distributed, the heat conducting structures including an inner arrangement of spiral blades; an air flow generating fan element; and an outer arrangement of heat transfer pins distributed along a perimeter of the rotating disk, the heat transfer pins having a high aspect ratio that maximizes a surface area to footprint area; wherein the spiral blades generate a mass fluid flow of ambient fluid toward the heat transfer pins such that the heat transfer pins are persistently cooled. | 05-26-2011 |
| 20110206501 | COMBINED FEATHERSEAL SLOT AND LIGHTENING POCKET - A segmented engine component has multiple segments which are connected to each other via a featherseal arrangement. Each of the components has a combined featherseal slot and lightening pocket. | 08-25-2011 |
| 20110206502 | TURBINE SHROUD SUPPORT THERMAL SHIELD - A turbine shroud assembly includes an annular thermal shield around an annular shroud support. A honeycomb layer is attached to the shroud support along an inner side of the honeycomb layer and a heat shield is attached to an outer side of the honeycomb layer. The honeycomb layer may be brazed to the shroud support and the heat shield may be brazed to the honeycomb layer. A lip may depend inwardly from a forward end of the heat shield and an axial extension may extend beyond an aft end of the honeycomb layer. The thermal shield may be segmented. The shroud assembly may include axially spaced apart first and second stage thermal shields circumferentially disposed around an annular shroud support and may be incorporated in a high pressure turbine including first and second stage shrouds coupled to shroud hangers that are inwardly supported by hooks of the shroud support. | 08-25-2011 |
| 20110236190 | TURBINE ROTOR WHEEL - A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication. | 09-29-2011 |
| 20110236191 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger includes a bearing flange for securement of the exhaust-gas turbocharger to a bearing housing of a turbine wheel. The bearing flange is provided with an outer circumferential fin having a base portion which terminates in a free end. The base portion is defined by a width which is greater than a width of the free end. An outer housing is welded to the outer circumferential fin of the bearing flange, and accommodates an impeller housing. | 09-29-2011 |
| 20110236192 | COMPRESSOR HOUSING RESISTANT TO TITANIUM FIRE, HIGH-PRESSURE COMPRESSOR INCLUDING SUCH A HOUSING AND AIRCRAFT ENGINE FITTED WITH SUCH A COMPRESSOR - A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream. | 09-29-2011 |
| 20110243717 | DEAD ENDED BULBED RIB GEOMETRY FOR A GAS TURBINE ENGINE - A component within a gas turbine engine includes a dead ended rib which at least partially defines an internal cooling circuit flow path, the dead ended rib defines a bulbed rib profile. | 10-06-2011 |
| 20110274535 | TURBOCHARGER ASSEMBLY HAVING HEAT SHIELD-CENTERING ARRANGEMENTS - A turbocharger for internal combustion engines, having a heat shield disposed between a turbine housing and center housing of the turbocharger for shielding the center housing from exhaust gases passing through the turbine. The heat shield in one embodiment is centered on a generally conical surface of the center housing, by engagement between the conical surface and a centering portion of the heat shield. In another embodiment, the heat shield has a generally conical portion that is non-axisymmetric, having a plurality of radially enlarged lobes that engage a radially inwardly facing surface of the turbine housing for centering the heat shield. | 11-10-2011 |
| 20110280716 | GAS TURBINE ENGINE COMPRESSOR COMPONENTS COMPRISING THERMAL BARRIERS, THERMAL BARRIER SYSTEMS, AND METHODS OF USING THE SAME - Gas turbine engine compressor disks having a hot flowpath side; a shaft having a first surface positioned in the hot flowpath side; and a thermal barrier applied to at least the first surface of the shaft where the thermal barrier is operable to maintain the temperature of the shaft below about 700° C. (1300° F.) when the hot flowpath side experiences a service operating temperature of from about 700° C. (1300° F.) to about 788° C. (1450° F.). | 11-17-2011 |
| 20110305559 | HEAT DISSIPATION DEVICE AND CENTRIFUGAL FAN THEREOF - An exemplary heat dissipation device includes a centrifugal fan and a fin assembly. The centrifugal fan includes a fan frame and an impeller mounted in the fan frame. The fan frame includes a base plate, a cover plate and a side wall extending between the base plate and the cover plate. An air outlet is defined in the side wall. | 12-15-2011 |
| 20120014784 | RAM AIR FAN MOTOR COOLING - A ram air fan assembly includes a ram air fan disposed at a fan inlet and a ram air fan motor operably connected to the ram air fan. A blower is operably connected to the ram air fan and is configured to redirect a cooling flow across the ram air fan motor from a substantially axially directed flow to a substantially radially directed flow thereby increasing the cooling flow across the ram air fan motor. A method of cooling a ram air fan assembly includes urging a cooling flow toward the ram air fan motor and is directed across the ram air fan motor thus removing thermal energy from the ram air fan motor. The cooling flow proceeds across a blower operably connected to the ram air fan motor, thus directing the cooling flow substantially radially outwardly toward the fan inlet. | 01-19-2012 |
| 20120063890 | WIND TURBINE NACELLE WITH COOLER TOP - The present invention relates to a wind turbine nacelle having a first face with a longitudinal extension in a wind direction, comprising a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face, the cooling device being enclosed by the first face of the nacelle and the inner face of the cover. A first distance between at least one of the faces and the cooling area is at least 30 mm. | 03-15-2012 |
| 20120076643 | Sealing System for Centrifugal Pumps - A centrifugal pump for delivering hot fluids, having a contacting shaft seal, a seal housing ( | 03-29-2012 |
| 20120107104 | COMPRESSION SYSTEM FOR TURBOMACHINE HEAT EXCHANGER - An example turbomachine cooling arrangement includes a pump configured to pressurize a first turbomachine fluid that is then communicated through a heat exchanger assembly to remove thermal energy from a second turbomachine fluid. A portion of the pump is configured to be housed within a gearbox housing of a turbomachine. | 05-03-2012 |
| 20120141256 | ANNULAR GAS TURBINE HOUSING COMPONENT AND A GAS TURBINE COMPRISING THE COMPONENT - The invention relates to an annular gas turbine housing component ( | 06-07-2012 |
| 20120141257 | SEGMENTED TURBINE RING FOR A TURBOMACHINE, AND TURBOMACHINE FITTED WITH SUCH A RING - The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises:
| 06-07-2012 |
| 20120156013 | AIR CYCLE MACHINE COMPOSITE INSULATOR PLATE - An air cycle machine including a housing with a compressor housing portion and a turbine housing portion secured to one another by fasteners. The compressor and turbine housing portions each provide a surface. An insulator plate is provided between and engages the surfaces. The fasteners extend through circumferentially arranged holes in the insulator plate. The insulator plate has an axial width, an inner diameter and an outer diameter. The outer diameter to the inner diameter provides a first ratio of 1.19-1.21, and the inner diameter to the width provides a second ratio of 53-59. In one example, the insulator plate is a composite structure constructed from 9-12 carbon fiber laminations with each layer having directional carbon fibers oriented transversely relative to the carbon fibers of an adjacent layer. | 06-21-2012 |
| 20120189436 | TEMPERATURE CONTROL RING FOR VEHICLE AIR PUMP - An annular device for the temperature control of a pump is provided. That device is in fluid communication with the radiator coolant system of a vehicle, and the engine-warmed coolant flows through the annular device to warm the pump and thaw ice buildup. The device is removable and can be added on to an existing pump without any redesign of the existing pump housing. | 07-26-2012 |
| 20120201662 | CORE RUNOUT CEILING FOR TURBINE COMPONENTS - A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed. | 08-09-2012 |
| 20120243979 | MIXING FAN - The invention relates to a fan comprising a housing and a fan wheel arranged on a motor shaft and being drivable by a motor. According to the invention, the fan is designed as a mixing fan for transporting and mixing a combustible medium with air, wherein at least the fan wheel is designed in an insulating manner. | 09-27-2012 |
| 20120263581 | Heating pump - A heating pump includes an electric motor, a pump housing fixed to the motor, an impeller driven by the motor, and a ring heater with an inner hole for heating fluid in the pump housing. The pump housing has a pump chamber and a pump inlet and a pump outlet which are in fluid communication with the pump chamber. The impeller is received in the pump housing and having an impeller inlet and a plurality of impeller outlets. The ring heater is disposed inside the pump chamber and between the pump inlet and the impeller. The impeller inlet is in fluid communication with the pump inlet via the inner hole. | 10-18-2012 |
| 20120288362 | INSULATING A CIRCUMFERENTIAL RIM OF AN OUTER CASING OF A TURBINE ENGINE FROM A CORRESPONDING RING SECTOR - A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim. | 11-15-2012 |
| 20120328420 | TURBOFAN AND INDOOR UNIT OF AIR-CONDITIONING APPARATUS INCLUDING THE SAME | 12-27-2012 |
| 20130011246 | Gas-Turbine Aircraft Engine With Structural Surface Cooler - The present invention relates to a gas-turbine aircraft engine with a core engine surrounded by a bypass duct, with a substantially annular cooling element being provided in the area of a radially inner wall of the bypass duct downstream of stator vanes of the bypass duct. | 01-10-2013 |
| 20130039747 | EXHAUST-GAS TURBOCHARGER - The invention relates to an exhaust-gas turbocharger ( | 02-14-2013 |
| 20130084170 | GAS TURBINE ENGINE MOUNTING ARRANGEMENTS - A clamp suitable for use in an anti-icing system of a gas turbine engine is provided is disclosed. The clamp has a clasping portion for clasping a heating element. Two resilient arms extend from the clasping portion to a substantially rigid outer collar. Translational movement of the clasping portion, which may be created by radial expansion of an annular heating element being clasped thereby, can be accommodated by the clamp by elastic deformation of the resilient arms. This allows radial expansion of the heating element to be accommodated without relative rotation between the clasping portion and the heating element. | 04-04-2013 |
| 20130089413 | Screw Compressor - A screw compressor includes a compressor body and a shell and tube heat exchanger for cooling of a compressed air discharged from the compressor body. A tube provided in the shell and tube heat exchanger has both ends each having a cylindrical shape, and a center part formed as a multi-lobate tube to have a corrugated shape with crest portions and trough portions alternately arranged in a circumferential direction. The multi-lobate tube provided at the center part of the tube is formed to have a multi-lobate spiral shape through twisting. Size reduction of the shell and tube heat exchanger may make the screw compressor compact as a whole. | 04-11-2013 |
| 20130115061 | INLET BLEED HEAT SYSTEM - An embodiment of the present invention takes the form of an IBH system that has two conduits, which are positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air. | 05-09-2013 |
| 20130115062 | INLET BLEED HEAT SYSTEM - An embodiment of the present invention takes the form of an IBH system that has a single conduit, which is positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air. | 05-09-2013 |
| 20130115063 | OIL MANAGEMENT SYSTEM FOR A COMPRESSOR - The invention relates to an oil management system for a compressor in a refrigeration system comprising: an oil temperature sensor; a heater arranged to heat oil in a crank case of the compressor; and a controller operatively associated with the temperature sensor and the heater, the controller arranged to control operation of the heater on the basis of ambient air temperature and oil temperature to maintain the oil temperature within a range Tmax≧R≧Tmin where Tmax>Tmin. | 05-09-2013 |
| 20130115064 | INSULATOR, AND STATOR AND MOTOR PROVIDED WITH SAME - An insulator includes a main body, a latching portion, and a slot. The main body covers a portion of a stator core around which a coil is wound to insulate the stator core from the coil. The latching portion is disposed at an end of a portion of the main body around which the coil is wound to latch the coil onto the main body. The slot is formed so as to expose the coil at a portion of the latching portion on a side where cooling oil for cooling the coil is supplied to the coil. | 05-09-2013 |
| 20130136584 | SEGMENTED THERMALLY INSULATING COATING - A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions. | 05-30-2013 |
| 20130142631 | EXHAUST GAS HOUSING FOR A GAS TURBINE AND GAS TURBINE HAVING AN EXHAUST GAS HOUSING - An exhaust gas housing for a gas turbine, in which an annular gas passage, through which exhaust gas discharges from the gas turbine to the outside, is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and have in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the gas passage, and wherein the struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining towards the gas passage, wherein the lining of the struts is at least partially mechanically decoupled from the lining of the inner casing and/or of the outer casing for reducing thermal stresses on the periphery of the struts. | 06-06-2013 |
| 20130149120 | GAS TURBINE ENGINE WITH OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM - A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface. | 06-13-2013 |
| 20130183146 | TURBO COMPRESSOR - A turbo compressor is provided that has first, second and third stage compressor blades rotated by a large gear shaft via an acceleration device, and includes a cast integral casing ( | 07-18-2013 |
| 20130189088 | TURBINE EXHAUST DIFFUSER SYSTEM MANWAYS - A turbine exhaust diffuser system includes a plurality of manways. The plurality of manways each extend between an outer wall of the turbine exhaust diffuser system and an interior access tunnel of the turbine exhaust diffuser system. The plurality of manways extend between the outer wall and the access tunnel at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system. | 07-25-2013 |
| 20130202420 | Turbine Shell Having A Plate Frame Heat Exchanger - A turbine shell is provided, and includes a body portion and at least one plate. The body portion has a forward portion and an aft portion. The plate is located between the forward portion and the aft portion. The plate is part of a plate frame heat exchanger, which is part of the body portion of the turbine shell. | 08-08-2013 |
| 20130216363 | SURFACE AREA AUGMENTATION OF HOT-SECTION TURBOMACHINE COMPONENT - An example turbomachine hot-section component protrusion extends away from a base surface of a hot-section component along a longitudinal axis. A radial cross-section of the protrusion has a profile that is non-circular. | 08-22-2013 |
| 20130230390 | LEADING EDGE STRUCTURE, IN PARTICULAR FOR AN AIR INLET OF AN AIRCRAFT ENGINE NACELLE - A leading edge structure for an air inlet of an aircraft nacelle includes a leading edge and an inner partition defining a longitudinal compartment that is located inside the leading edge and accommodates a de-icing and/or anti-icing mat. The leading edge structure includes a multi-axial composite structure placed on top of a heating element for anti-icing and/or de-icing. | 09-05-2013 |
| 20130236299 | TUBULAR HEAT EXCHANGE SYSTEMS - A heat exchange system includes a first flow passage and a second flow passage. The heat exchange system is configured to transfer heat between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage. The first flow passage includes an inlet header, a plurality of tubes, and an outlet header. The inlet header includes a plurality of header-tube transition portions configured to allow the first fluid to flow from the inlet header and into the tubes, the plurality of header-tube transition portions each including a smoothly curved inlet portion and a tapered tube connection portion. | 09-12-2013 |
| 20130259662 | ROTOR AND WHEEL COOLING ASSEMBLY FOR A STEAM TURBINE SYSTEM - A rotor and wheel cooling assembly for a steam turbine system includes a rotor operably connected to a plurality of rotating buckets. Also included is a flow diverting member having an inner radius and operably coupled to at least one nozzle stage, wherein the flow diverting member directs flow in at least one direction within the steam turbine system. Further included is a cooling flow dispenser disposed radially outwardly of a portion of the rotor and having at least one aperture, wherein the cooling flow dispenser is operably coupled to the inner radius of the flow diverting member. | 10-03-2013 |
| 20130287554 | PINEAPPLE PUMP - A pineapple pump is provided. The pineapple pump includes a rotor chamber and a rotor. The rotor chamber may include a plurality of cooling columns for thermal management. The rotor is rotatably disposed in the rotor chamber and the cooling columns are located at a fluid outlet of the rotor. The rotor has a rotary shaft to deliver a tangential torque. When the rotor rotates with the rotary shaft to guide a fluid, the fluid has a radial displacement perpendicular to the tangential torque of the rotor, thereby de-coupling the tangential torque and a pressure gradient of the fluid caused by the rotor. | 10-31-2013 |
| 20130294898 | TURBINE ENGINE COMPONENT WALL HAVING BRANCHED COOLING PASSAGES - A component wall in a turbine engine includes a substrate and at least one cooling passage that extends through the substrate for delivering cooling fluid from a chamber associated with an inner surface of the substrate to an outer surface of the substrate. Each cooling passage is divided into at least two branches that receive cooling fluid from an entrance portion of the cooling passage that is in communication with the chamber. The branches each include an intermediate portion that extends transversely from the entrance portion and that receives cooling fluid from the entrance portion, and an exit portion that extends transversely from the respective intermediate portion. The exit portions receive the cooling fluid from the intermediate portions and deliver the cooling fluid out of the respective branch through exit portion outlets. | 11-07-2013 |
| 20130294899 | DEVICE AND METHOD FOR COOLING ELECTRIC DEVICE HAVING MODULAR STATORS - An annular stator assembly includes a plurality of stator segments. Each stator segment includes a plurality of laminates having magnetic permeable properties; a plurality of thermally conductive laminates positioned between the permeable laminates; and a cooling pipe extending through the laminates for transferring heat from the laminates to coolant flowing through the cooling pipe. The stator segments are constructed independently. Coils are wound on each segment. The stator segments with the wound coils are subsequently arranged to form the annular stator assembly. | 11-07-2013 |
| 20130294900 | MOUNTING SYSTEM FOR A NACELLE FIRE DETECTION SYSTEM - A mounting system for a fire detection system for a turbofan engine propulsion system is provided to mount fire detection sensors on the inner fixed structure (IFS) of the nacelle. The mounting system mounts to an inner, engine facing surface of the IFS. Two IFS halves cooperate to form a substantially enclosed space around an engine core. The mounting system includes part of a fastening system mounted to the IFS, and an orientation clip mounted to a thermal blanket. Brackets for mounting the fire detection system sensing wires are positioned on the orientation clip, and the fastening system fixes the bracket to the IFS and traps the thermal blanket therebetween. | 11-07-2013 |
| 20130315720 | ELECTRICAL COMPRESSOR HOUSING COMPRISING A DISSIPATION DEVICE, AND COMPRESSOR INCLUDING SUCH A HOUSING - The invention relates to a housing | 11-28-2013 |
| 20130323036 | HEAT SHIELD FOR A LOW-PRESSURE TURBINE STEAM INLET DUCT - The present invention relates to an assembly comprising a duct, preferably a turbine duct, and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element at least one boss per shell which boss is fixed to the duct and against which boss the shell rests, such that at least one orifice and one boss face one another, and that the fixing element passes through the orifice facing the boss and is fixed to the boss. | 12-05-2013 |
| 20130343880 | TURBINE END INTAKE STRUCTURE FOR TURBOCHARGER, AND TURBOCHARGER COMPRISING THE SAME - A turbine end intake structure for a turbocharger includes a turbine housing, a turbine having multiple blades and located in a turbine shell, and thermal insulation located between the turbine end of the turbocharger and another part. A flow-guiding channel for engine exhaust gases is provided on the turbine housing in communication with the interior of the turbine housing. An inner surface of the turbine housing matching peripheral edges of the blades is a cylindrical surface coaxial with the turbine, while the shape of the peripheral edges of the blades follows the cylindrical surface. Angle-cut portions are provided on the blades at positions corresponding to an intake port of the flow-guiding channel. The thermal insulation has an outwardly extending flow-guiding part, and a flow-guiding path for engine exhaust gases formed by the flow-guiding channel and the flow-guiding part is perpendicular to the angle-cut portions of the blades. | 12-26-2013 |
| 20130343881 | TURBINE HOUSING OF AN EXHAUST TURBOCHARGER - A turbine housing of the exhaust turbocharger, having an inlet, which is adjoined by a spiral; having an outlet; and having a coolant arrangement; wherein the coolant arrangement has a plurality of coolant ducts, which branch off from an inlet duct section and open into an outlet duct section. | 12-26-2013 |
| 20140003920 | FLOW METERING ANTI-ROTATION OUTER DIAMETER (OD) HEX NUT | 01-02-2014 |
| 20140010639 | GAS TURBINE ENGINE OIL TANK WITH INTEGRATED PACKAGING CONFIGURATION - A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources. | 01-09-2014 |
| 20140017073 | SUBMERGED ROTOR ELECTRIC WATER PUMP WITH STRUCTURAL WETSLEEVE - An electric pump comprising: a rotor, a wet sleeve surrounding the rotor; and a stator surrounding the wet sleeve and the rotor; wherein the rotor and stator have a magnetic air gap of about 2 mm or less. | 01-16-2014 |
| 20140030073 | CLOSED LOOP COOLING SYSTEM FOR A GAS TURBINE - A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine. | 01-30-2014 |
| 20140064940 | CASING OF A TURBOCHARGER - A casing of a turbocharger has a main body and a heat dissipating layer disposed on an outer surface of the main body. When heat inside the main body is conducted to the outer surface of the main body, the heat dissipating layer dissipates the heat quickly. Since the heat does not accumulate in the main body, temperature of the main body is low and the casing does not oxidize under high temperature. Therefore, the casing of the turbocharger has low manufacturing cost and is economical. | 03-06-2014 |
| 20140064941 | FAN MODULE FOR A HEAT EXCHANGER - A fan module ( | 03-06-2014 |
| 20140099192 | COOLING PUMP FOR A COOLING SYSTEM - A cooling pump receives fluid from a heating system and supplies cooled fluid to an engine. The cooling pump includes a body housing and a cover housing. The cover housing is attached to the body housing to define an internal pumping chamber. The internal pumping chamber is defined between an inlet passage and an outlet passage of the body housing. A chamber outlet opening is defined between the internal pumping chamber and the outlet passage such that fluid flows from the internal pumping chamber and into the outlet passage. The cover housing includes a sloped wall which extends into the outlet passage between the chamber outlet opening and a terminus. The sloped wall has a concave portion and a convex portion disposed such that the concave portion is between the chamber outlet opening and the convex portion to direct fluid through the outlet passage and into the engine. | 04-10-2014 |
| 20140119903 | Gas Turbine Engine With Inlet Particle Separator and Thermal Management - A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet. | 05-01-2014 |
| 20140140829 | TURBINE ENGINE COOLING SYSTEM WITH AN OPEN LOOP CIRCUIT - A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit. | 05-22-2014 |
| 20140154063 | AIRFOIL AND A METHOD FOR COOLING AN AIRFOIL PLATFORM - An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform. | 06-05-2014 |
| 20140161598 | IMPELLER BACKFACE ROTATING HEAT SHIELD - A gas turbine engine, a rotor assembly for a gas turbine engine, and a method for thermally insulating an impeller in a gas turbine engine are provided. In one embodiment, the gas turbine engine includes an impeller having a front face configured to modify a direction of air flow through the gas turbine engine. The impeller further includes backface to which a heat shield is mounted. A closed cavity is defined between the heat shield and the backface of the impeller, and is configured to insulate the backface of the impeller from a high temperature environment. | 06-12-2014 |
| 20140178184 | FAN AND MOTOR BEARING HEAT DISSIPATION STRUCTURE THEREOF - A motor bearing heat dissipation structure includes a metal base, a heat conducting element connected to the metal base and including a wall portion and an extended portion, and a plastic bearing cup located around an outer side of the wall portion of the heat conducting element and fixed to the metal base. The plastic bearing cup internally defines a bearing receiving hole. The extended portion is horizontally extended from an upper end of the wall portion toward a center of the plastic bearing cup. A bearing is received in the bearing receiving hole and seated on the extended portion, so that heat produced by the bearing when it rotates along with a rotary shaft of a motor is transferred from the extended portion of the heat conducting element to the metal base for dissipation. A fan using such motor bearing heat dissipation structure is also disclosed. | 06-26-2014 |
| 20140186165 | ADHESIVE PATTERN FOR FAN CASE CONFORMABLE LINER - A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive. The adhesive covers at least a portion of the liner surface area, and can have interruptions used to tune the compliance of the adhesive layer. | 07-03-2014 |
| 20140193247 | IMPELLER PUMP - An impeller pump has a pump casing including a pump chamber and an inlet and an outlet thereon and an impeller therein, and including a heating device for heating the conveyed medium, which heating device forms an external wall of the pump chamber. The pump chamber extends annularly around the impeller and away from the pump chamber floor, wherein the outlet leads off on a region of the pump chamber which, viewed in the axial direction of the impeller pump, is pointing away from the pump chamber floor. The cross-sectional area of the pump chamber decreases in the axial direction of the longitudinal center axis of the impeller pump away from the pump chamber floor toward the outlet by virtue of an obliquely inwardly inclined external wall. | 07-10-2014 |
| 20140205447 | PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY - A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall. | 07-24-2014 |
| 20140234088 | MODULAR BLADE OR VANE FOR A GAS TURBINE AND GAS TURBINE WITH SUCH A BLADE OR VANE - The invention relates to a modular blade or vane for a gas turbine, which includes the modular components of a platform element with a planar or contoured surface defining a platform level and a through-opening therein, and an airfoil, extending through the platform element. The airfoil includes a load carrying structure extending along a longitudinal axis of the airfoil, having a root portion for fastening on a blade or vane carrier of the gas turbine, having a tip portion, and having at least one interior passage, extending from the root portion to the tip portion of the airfoil. An aerodynamically shaped shell extends in a distance over the carrying structure and defining the outer contour of the airfoil. A longitudinally extending gap, is disposed between the carrying structure and the shell. A number of through-holes in the carrying structure direct a cooling medium from the interior passage into the gap. The shell is integrally joined to said carrying structure by a first joint in a region below the platform level of the platform element. The shell is joined to the carrying structure by at least one additional joint, wherein said at least one additional joint is a form-fit joint, allowing relative movement in longitudinal direction between shell and carrying structure. | 08-21-2014 |
| 20140255172 | LOW PROFILE PUSH-LOCK DEVICE - A push-lock device for connecting a tile to a gas turbine engine wall includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including portions of both a push-down pop-up mechanism and a locking-bracket mechanism, the locking-bracket mechanism moveable to a locked position such that the locking-bracket mechanism limits movement of a tile away from a gas turbine engine wall; and a biasing member to be positioned closer to the tile than the locking-bracket mechanism. | 09-11-2014 |
| 20140271152 | TURBINE ENGINE TEMPERATURE CONTROL SYSTEM WITH HEATING ELEMENT FOR A GAS TURBINE ENGINE - A turbine engine temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine airfoil assembly during shutdown of a gas turbine engine and for preheating an engine during a cold startup 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. The turbine engine temperature control system may also be used for cold startup conditions to heat engine components such that gaps between turbine airfoil tips and adjacent blade rings can be made larger from thermal expansion, thereby reducing the risk of damage. The turbine engine temperature control system may operate during turning gear system operation after shutdown of the gas turbine engine or during a cold startup. | 09-18-2014 |
| 20140271153 | COOLED CERAMIC MATRIX COMPOSITE AIRFOIL - One aspect of the present disclosure includes a ceramic matrix composite airfoil having a shaped ceramic matrix composite core, a cooling fluid flow network having ceramic foam components, and a ceramic lamina skin disposed about the shaped core and the cooling fluid flow network. | 09-18-2014 |
| 20140321997 | Internal airfoil component electroplating - Method and apparatus are provided for electroplating a surface area of an internal wall defining a cooling cavity present in a gas turbine engine airfoil component. | 10-30-2014 |
| 20140328674 | COMPRESSOR - A compressor that includes a rotor assembly, a stator assembly and a heat sink assembly. The rotor assembly includes a shaft to which a bearing assembly and a rotor core are secured. The heat sink assembly is then secured to the bearing assembly and to the stator assembly. | 11-06-2014 |
| 20150016974 | METHOD OF PRODUCING AN INSULATION ELEMENT AND INSULATION ELEMENT FOR A HOUSING OF AN AERO ENGINE - The invention relates to a process for producing an insulation element ( | 01-15-2015 |
| 20150016975 | FAN ASSEMBLY - A fan assembly includes a motor-driven impeller for creating an air flow, a casing including an interior passage for receiving the air flow, and a plurality of air outlets for emitting the air flow from the casing. The casing defines and extends about an opening through which air from outside the casing is drawn by the air flow emitted from the air outlets. The fan assembly also includes at least one heater for heating at least a first portion of the air flow, and means for diverting at least a second portion of the air flow away from said at least one heater. The plurality of outlets includes at least one first air outlet for emitting the relatively hot first portion of the air flow and at least one second air outlet for emitting the relatively cold second portion of the air flow. | 01-15-2015 |
| 20150044037 | TURBOCHARGER BEARING HOUSING WITH INTEGRATED HEAT SHIELD - A system and method is provided in which a turbocharger includes a heat shield wall that is formed together with the bearing housing as a unitary structure. The wall can extend from a main body portion of the bearing housing in a generally radially outward direction. The wall can be spaced from the main body and attached by a plurality of ribs such that chambers are defined therebetween. A circumferential passage can extend through the bearing housing to permit fluid communication between the chambers and outside of the bearing housing. In this way, a fluid outlet from the chambers is provided. As a result of such an arrangement, the need for a separate heat shield is eliminated, which can facilitate the assembly process and special attachment methods associated with a separate heat shield. | 02-12-2015 |
| 20150050131 | TURBINE HOUSING - A turbocharger system may include a turbine housing and a tongue insert. The turbine housing may include an inlet, an outlet, and a gas pathway between the inlet and outlet. The gas pathway may include a volute portion and an inlet portion extending approximately tangent to the volute portion. The turbine housing may be formed from a first material. The tongue insert may be received in the turbine housing and may at least partially define the volute portion and the inlet portion. The tongue insert may be formed from a second material that is more heat resistant than the first material. | 02-19-2015 |
| 20150050132 | SCREW COOLING FOR A FLUID FLOW MACHINE - A fluid flow machine is provided having a housing composed of a housing upper part and a housing lower part, wherein the housing upper part is connected to the housing lower part via a pin screw and has a cooling duct which is connected, on the one hand, to the flow duct with a vapour at a relative high pressure and, on the other hand, to a cooling duct outlet which is connected to the exhaust steam space. | 02-19-2015 |
| 20150071772 | METHOD FOR PRODUCING AND RESTORING CERAMIC HEAT INSULATION COATINGS IN GAS TURBINES AND ASSOCIATED GAS TURBINE - Through the use of different ceramic heat insulation coatings ( | 03-12-2015 |
| 20150086345 | TURBO CHARGER HAVING COOLING STRUCTURE - A turbocharger having a cooling structure may include a center housing on which a shaft is rotatably fitted, a turbine impeller disposed at one end of the shaft, a compressor impeller disposed at the other end of the shaft, a turbine housing fastened to the center housing and covering the turbine impeller such that an exhaust gas flows into the turbine impeller, a compressor housing fastened to the center housing and covering the compressor impeller such that an intake air flows into the compressor impeller, and a coil type heat exchanger formed in a rotational direction of the shaft and in a space between the center housing and the turbine impeller. | 03-26-2015 |
| 20150292356 | HEAT SHIELD BASED AIR DAM FOR A TURBINE EXHAUST CASE - A turbine exhaust case employed in an industrial gas turbine engine includes a frame, a fairing and a heat shield. The frame includes an outer ring, an inner ring, and struts connected between the outer ring and the inner ring. The fairing includes a fairing outer ring, a fairing inner ring, and fairing struts connected between the fairing outer ring and the fairing inner ring. The heat shield is located between the frame outer ring and the fairing outer ring and provides a thermal barrier between the fairing outer ring and the frame outer ring, wherein the heat shield includes an aft portion having a flange that interfaces with the frame outer ring to form an air dam that directs cooling airflow forward along the frame outer ring within an outer diameter cavity formed between the frame outer ring and the heat shield. | 10-15-2015 |
| 20150292357 | AIRCRAFT GAS TURBINE HAVING A CORE ENGINE CASING WITH COOLING-AIR TUBES - An aircraft gas turbine having a core engine casing for a core engine, said core engine casing including at least a compressor area, a combustion chamber area and a turbine area, wherein the core engine casing is provided on its outer wall with several cooling-air tubes which are designed in one piece with said outer wall and extend in the axial direction relative to an engine axis. | 10-15-2015 |
| 20150300360 | AIR CONDITIONING APPARATUS - An air conditioning apparatus includes a casing having intake and blow-out ports, a partition member dividing an interior of the casing, a heat exchanger, a centrifugal fan, a heater and a fan heat shield. The centrifugal fan includes a bladed wheel mounted in the fan compartment such that a rotary shaft of the bladed wheel is oriented along an opening direction of the fan entrance and an opening direction of the blow-out port, and the bladed wheel being made of resin. The heater is mounted in a blow-out port opposed space opposed to the blow-out port within a fan downwind space located on a downwind side of the bladed wheel within the fan compartment. The fan heat shield member is mounted in the fan downwind space in order to cover a part of the bladed wheel that is opposed to the heater. | 10-22-2015 |
| 20150308455 | WALL RING FOR AN AXIAL FAN - The present invention relates to a wall ring for receiving in particular an axial fan, comprising an annular body with a flow inlet opening and a flow outlet opening and a central longitudinal axis X-X as well as an annular wall extending between both openings. The annular wall has a cavity which is enclosed by an outer wall and an inner wall, in which an electrical heating element may be secured at least over a partial area of the periphery of the annular wall. The annular body consists of at least two partial bodies which are formed by a division of the annular body in a separating plane that extends perpendicular to its longitudinal axis and are detachably connected to one another. | 10-29-2015 |
| 20150315931 | DEVICE FOR CONNECTING A FIXED PORTION OF A TURBINE ENGINE AND A DISTRIBUTOR FOOT OF A TURBINE ENGINE TURBINE | 11-05-2015 |
| 20150322818 | VANE SEGMENT FOR A GAS TURBINE COATED WITH A MCRALY COATING AND TBC PATCHES - A vane device for a gas turbine is provided. The vane device includes a first airfoil having a first suction side and a first pressure side, a second airfoil having a second suction side and a second pressure side, an inner shroud and an outer shroud. The first airfoil and the second airfoil are arranged between the inner shroud and the outer shroud, wherein the first airfoil and the second airfoil are at least partially coated with a MCrAIY coating. At least the first suction side has a first coated surface section which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side. At least the inner shroud or the outer shroud has a further coated surface section which is coated with a further thermal barrier coating. A corresponding method of manufacturing is also provided. | 11-12-2015 |
| 20150322850 | TURBOCHARGER AND CASING - Various methods and systems are provided for a turbocharger comprising a turbine disc rotatable about a rotational axis of the turbocharger, a compressor wheel mechanically coupled to the turbine disc via a shaft, a compressor casing including an air inlet and a blower casing formed as one piece, the air inlet configured to admit air to the compressor wheel, and a turbine casing housing the turbine disc, the turbine casing including a shroud surrounding the turbine disc. | 11-12-2015 |
| 20150330250 | TURBINE EXHAUST CASE ARCHITECTURE - A turbine exhaust case ( | 11-19-2015 |
| 20150330403 | AIR CONDITIONING APPARATUS - An air conditioning apparatus includes a casing having intake and blow-out ports, a partition member dividing an interior of the casing, a heat exchanger and a centrifugal fan. The centrifugal fan includes a hub and a bladed wheel having a plurality of rearward blades and sucks air existing in the heat exchanger compartment into the fan compartment through the fan entrance. The bladed wheel is mounted in the fan compartment such that a rotary shaft of the bladed wheel is oriented along an opening direction of the fan entrance and an opening direction of the blow-out port. The hub connects blow-out port side ends of the plural rearward blades and is configured to be rotated about the rotary shaft. The hub has an outer diameter smaller than an outer diameter of the rearward blades. | 11-19-2015 |
| 20150337859 | Heater Pump - A heater pump includes a motor and a pump assembly. The pump assembly includes a pump housing having an inlet and an outlet. An impeller and a heater are disposed within the pump housing. The heater includes a heater housing having an inner wall, an outer wall, a lower wall and an upper wall forming a heating chamber. A heating element is disposed within the heating chamber. The inner wall defines an inlet channel connecting the impeller with the inlet of the water pump. Water flowing through the pump is heated by contact with the heater housing and/or the heating element. | 11-26-2015 |
| 20150345329 | HEAT SHIELD FOR A CASING - A gas turbine engine includes a casing, a fairing, and a heat shield. The fairing is annularly shaped and disposed adjacent the casing. The heat shield is connected to the casing and includes a first portion and a second portion. The first portion is generally cylindrically shaped and extends between the fairing and the casing and the second portion extends generally radially away from the casing and the first portion toward the fairing. | 12-03-2015 |
| 20150345330 | MULTI-PIECE HEAT SHIELD - An assembly for a gas turbine engine includes a first casing, a fairing, and a multi-piece heat shield assembly. The fairing is disposed adjacent the first casing. The multi-piece heat shield assembly includes a first shield mounted to the first casing and extending between the first casing and the fairing, and a second shield mounted to the fairing and extending between the fairing and the first casing. | 12-03-2015 |
| 20150345338 | TURBINE FRAME ASSEMBLY AND METHOD OF DESIGNING TURBINE FRAME ASSEMBLY - A structural case assembly comprises a frame, fairing and heat shield. The frame is fabricated from a material having a temperature limit below an operating point of a gas turbine engine, and comprises an outer ring, an inner ring and a plurality of struts extending therebetween to define a flow path. The fairing is fabricated from a material having a temperature limit above the operating point of the gas turbine engine, and comprises a ring-strut-ring structure that lines the flow path. The heat shield is disposed between the frame and the fairing to inhibit radiant heat transfer therebetween. The heat shield may block all line-of-sight between the fairing and the frame. The frame may be produced from CA-6NM alloy. A method for designing a turbine case structure includes selecting a frame material having a temperature limit below the operating point of an engine. | 12-03-2015 |
| 20150345499 | VACUUM PUMP - A vacuum pump comprises a cylindrical rotor; a cylindrical stator which discharges gas in cooperation with the rotor; a base housing at least a part of the stator and having a through hole formed at a position facing an outer periphery of the stator; a heating member passing through the through hole from an atmosphere side to a vacuum side to have thermal contact with an outer peripheral surface of the stator to heat the stator; and an axial seal member which vacuum-seals a gap between the through hole and the heating member. | 12-03-2015 |
| 20150345509 | WALL RING WITH WALL RING HEATING ELEMENT FOR AXIAL FANS - The invention relates to a wall ring for receiving an axial fan in particular, comprising an annular body with a central longitudinal axis, a flow inlet opening, a flow outlet opening, and an electric heating element in particular, said heating element being arranged on at least some sections of the circumference of the annular body. A profiled covering section made of a thermally insulating material is removably fixed to an outer surface of the annular body at least in some sections of the circumference, said profiled covering section together with the annular body forming a receiving area in the region of the annular wall of the annular body in order to receive the electric heating element. | 12-03-2015 |
| 20150354383 | TURBINE AND METHODS OF ASSEMBLING THE SAME - A turbine operable with a first fluid and a second fluid is provided. The turbine includes a shaft and having a dry gas seal area, a balance area, and a shaft surface. The turbine also includes a stationary component coupled to a housing and having a first side and a second side and defining a channel in flow communication with the shaft surface. A heat exchange assembly is coupled to the housing and in flow communication with the shaft and the stationary component. The heat exchange assembly includes a first flow path coupled in flow communication with the dry gas seal area and the channel and configured to direct the first fluid along the first side. Heat exchange assembly also includes a second flow path coupled in flow communication with the balance area and channel and configured to direct the second fluid along the second side. | 12-10-2015 |
| 20150354406 | BLADE OUTER AIR SEAL AND METHOD OF MANUFACTURE - The present disclosure relates to gas turbine engine components, such as blade outer air seals and methods of manufacture. In one embodiment, a gas turbine engine component includes a retention interface formed by an additive manufacturing process. The gas turbine engine component can include a retention interface having a pattern, and a thermal barrier layer formed to the retention interface. | 12-10-2015 |
| 20150354410 | MECHANICAL LINKAGE FOR SEGMENTED HEAT SHIELD - A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing. | 12-10-2015 |
| 20150354457 | Splitter for Air Bleed Manifold - A splitter for protecting parts of a gas turbine engine is provided. The splitter segregates the flow of hot and cold gases into the air bleed manifold around the high compressor section to reduce maximum temperatures and minimize the temperature gradients of engine parts, especially inner case flanges The splitter divides the air bleed manifold into an annular inner cavity and an outer cavity. The splitter directs relatively cold air from the high compressor bleed ducts into the inner cavity and relatively hot air from the aft hub into the outer cavity, away from the inner case flanges. | 12-10-2015 |
| 20150369082 | MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE - A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger, wherein the second lubricant circuit is fluidly separate from the first lubricant circuit. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second turbine engine component includes a bearing. The shaft is supported by the bearing and connected to one of the engine stages. | 12-24-2015 |
| 20150369257 | MOTOR FAN - A motor fan | 12-24-2015 |
| 20160003074 | GAS TURBINE ENGINE STATOR VANE PLATFORM COOLING - An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces. | 01-07-2016 |
| 20160003096 | TURBOCHARGER INTERNAL TURBINE HEAT SHIELD HAVING AXIAL FLOW TURNING VANES - A turbocharger internal heat shield ( | 01-07-2016 |
| 20160003161 | HEAT SHIELD MOUNT CONFIGURATION - An attachment interface assembly for a gas turbine engine has a component configured for attachment to an engine static structure. A fastener has a threaded body portion and an enlarged head portion. The threaded body portion is inserted through aligned holes in the component and engine static structure. A clip has a center opening that receives the threaded body portion such that the clip is positioned between the enlarged head portion and the component. | 01-07-2016 |
| 20160003261 | HEAT MODULE - The fan includes an impeller, a motor, and a housing. The housing includes a side wall portion and a lower plate portion. at least one of the lower plate portion and an upper plate portion arranged to cover an upper side of the impeller includes an air inlet. The upper plate portion, the side wall portion, and the lower plate portion are arranged to together define an air outlet on a lateral side of the impeller. At or near an opposite end of the heat pipe, the heat pipe includes a contact portion arranged to be in contact with one of an upper surface of the lower plate portion and a lower surface of the upper plate portion. A longitudinal direction of at least a portion of the heat pipe extends at an angle with respect to the air outlet. | 01-07-2016 |
| 20160010473 | COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT | 01-14-2016 |
| 20160017714 | A TECHNIQUE FOR COOLING A ROOT SIDE OF A PLATFORM OF A TURBOMACHINE PART - A platform cooling device directs a cooling fluid onto a root side of a platform of a turbomachine part. The platform cooling device includes a first segment to be positioned at a root of the turbomachine part and a second segment, at an angle to the first segment, to be positioned at the root side of the platform of the turbomachine part. The second segment may include at least one impingement channel having an inlet for receiving at least a part of the cooling fluid and an outlet for releasing the received cooling fluid onto the root side of the platform. The first segment and the second segment may define a path for the cooling fluid via the impingement channel. A turbomachine component includes the platform cooling device. | 01-21-2016 |
| 20160025098 | CENTRIFUGAL PUMP AND METHOD OF PRODUCING CENTRIFUGAL PUMP - A centrifugal pump includes a metallic main body casing in which a rotating blade member is accommodated. The metallic main body casing includes an upper main body casing, a lower main body casing which is fixed to the upper main body casing, and a blade casing, which partitions an interior space formed by the upper main body casing and the lower main body casing so that a fluid introducing passage is formed at an upper portion, and a rotating accommodating space that accommodates the rotating blade member is formed at a lower portion. An edge of the blade casing is airtightly fixed to the upper main body casing or the lower main body casing. | 01-28-2016 |
| 20160025101 | PROPELLER FAN, BLOWER DEVICE, AND OUTDOOR EQUIPMENT - A propeller fan, including: a boss; and a plurality of blades, each of the plurality of blades including a pressure surface and a suction surface, in which: when a connecting portion between the pressure surface and a side surface of the boss is defined as a pressure surface-side boundary portion, and a connecting portion between the suction surface and the side surface of the boss is defined as a suction surface-side boundary portion, a curvature of the suction surface-side boundary portion is smaller than a curvature of the pressure surface-side boundary portion; and as a blade area projected on a plane orthogonal to the rotation axis, a blade area of the suction surface is larger than a blade area of the pressure surface. | 01-28-2016 |
| 20160032768 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 02-04-2016 |
| 20160032780 | Triple Flange Arrangement for a Gas Turbine Engine - A flange arrangement for a gas turbine engine includes a case flange between a forward flange and an aft flange. | 02-04-2016 |
| 20160040686 | Heating Pump - A heating pump includes a pump housing with an inlet, an outlet, a heater, an impeller, and a motor for driving the impeller. The impeller is received in the pump housing. The heater includes connecting heads and a main body for generating heat. The main body is bent into an arc. The pump housing includes a cylindrical sidewall extending in an axial direction of the motor and a top plate sealed to an axial opening of the sidewall. The top plate is made of metal. The heater extends through and is fixed to the top plate. The connecting heads extend to an exterior of the pump housing. The main body is located in an interior of the pump housing and in contact with the top plate. | 02-11-2016 |
| 20160047311 | GAS TURBINE ENGINE COOLING FLUID METERING SYSTEM - A cooling fluid system for a gas turbine engine includes a fluid source. A turbine section includes first and second components. A fluid supply system has a primary pipe that is configured to provide a cooling supply fluid from the fluid source to a fluid fitting having a fluid junction. The fluid junction is in fluid communication with and is configured to supply a first cooling fluid to the first component. The fluid junction is in fluid communication with and is configured to supply a second cooling fluid to the second component. A flow meter is upstream from the fluid junction and is configured to receive the cooling supply fluid. | 02-18-2016 |
| 20160053633 | SEAL WITH COOLING FEATURE - A seal may be used in a shroud ring of a turbine. The seal includes a first strip, a second strip, and a flow-control band that extends between and interconnects the first and second strips to control the flow of a fluid through the seal. | 02-25-2016 |
| 20160053688 | GAS TURBINE ROTORS - A rotor for a gas turbine engine includes a cold shell, a hot shell, and a spoke. The spoke is connected to and extends radially outward from the cold shell. The hot shell is connected to the cold shell by the spoke and includes an axially extending outboard segment and an axially extending inboard segment. The outboard segment is connected to the inboard segment and the inboard segment is disposed radially inboard of the outboard segment for sealably engaging a stator blade shroud. | 02-25-2016 |
| 20160069210 | WINDBACK HEAT SHIELD - A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion. A compressor section and a gas turbine engine including the heat shield are also disclosed. | 03-10-2016 |
| 20160076555 | Remanufactured Center Housing and Method - A system and method for remanufacturing a turbocharger center housing include performing a machining operation on an original center housing to remove a portion of a parent material from the original center housing. A ring having a generally rectangular cross section is attached to the center housing blank in place of the removed material to produce a rebuilt center housing. In one embodiment, the ring forms an annular surface onto which a seal is engaged to avoid external leakage of turbine exhaust gas through an interface between a turbine housing and the remanufactured center housing. | 03-17-2016 |
| 20160090861 | STEAM TURBINE - A steam turbine in an embodiment includes a casing, a turbine rotor, a rotor blade cascade, a stationary blade cascade, and a spray unit, the rotor blade cascade and the stationary blade cascade being each arranged at a plurality of stages alternately in an axial direction of the turbine rotor. The turbine rotor is housed inside the casing. In the rotor blade cascade, a plurality of rotor blades are arranged in a circumferential direction of the turbine rotor. In the stationary blade cascade, a plurality of stationary blades are arranged in the circumferential direction of the turbine rotor between a diaphragm inner ring and a diaphragm outer ring. The spray unit sprays spray water to a space located upstream from a rotor blade cascade at a final stage among the rotor blade cascades at the plurality of stages inside the casing. | 03-31-2016 |
| 20160102678 | HEAT SHIELD WITH CENTERING FEATURES - A turbocharger ( | 04-14-2016 |
| 20160108738 | GAS TURBINE COMPONENT WITH PLATFORM COOLING - A gas turbine engine component includes an airfoil that extends from a first side of a platform and a cooling passage that extends through the platform and includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the airfoil. | 04-21-2016 |
| 20160108748 | GAS TURBINE ENGINE WITH DOVE-TAILED TOBI VANE - A combustor assembly for a gas turbine engine includes a TOBI module which includes a TOBI housing. The TOBI housing has a slot. A vane including a dovetail is removably received within the slot. | 04-21-2016 |
| 20160108929 | AIR-GUIDING COVER AND FAN HAVING THE SAME - The present invention relates to provide an air-guiding cover, comprising: an inner ring; an outer ring being arranged around the inner ring and defining a windward plane between the outer ring and the inner ring; and a plurality of air-guiding fins being arranged in the inner ring. The air-guiding fins have an inclination with respect to a normal axis of the windward plane, and the inclination increases progressively as the air-guiding fins extend from the inner ring toward the outer ring. | 04-21-2016 |
| 20160114898 | CIRCUIT FOR DE-ICING AN AIR INLET LIP OF AN AIRCRAFT PROPULSION ASSEMBLY - Propulsion assembly, comprising a turbine engine surrounded by a nacelle comprising an annular air inlet lip, the propulsion assembly further comprising a circuit for lubricating elements of the turbine engine and a circuit for de-icing the air inlet lip, characterised in that said de-icing circuit comprises a heat exchanger comprising a primary circuit of oil supplied by said lubrication circuit and a secondary circuit of a heat transfer fluid for supplying at least one de-icing channel extending into said air inlet lip, said de-icing circuit further comprising a pump for circulating the heat transfer fluid into said at least one channel. | 04-28-2016 |
| 20160131039 | GAS TURBINE ENGINE HEAT EXCHANGER MANIFOLD - A heat exchanger manifold for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a manifold body extending between a first face and a second face, a first seal land defining a first fluid port extending through the manifold body between the first face and the second face, and a first seal received within the first fluid port. | 05-12-2016 |
| 20160138462 | ENGINE - The object of the present invention is to provide a compact engine. An engine has a two-stage turbocharger provided with a high-pressure turbocharger and a low-pressure turbocharger. The high-pressure turbocharger and the low-pressure turbocharger are separately disposed on the gear case side and the flywheel side in along direction of a main body respectively. An intake pipe and an exhaust pipe connecting the high-pressure turbocharger with the low-pressure turbocharger are separately and respectively disposed on right side and left side in a transverse direction of the main body. | 05-19-2016 |
| 20160146042 | GAS TURBINE AND HEAT SHIELD FOR A GAS TURBINE - A gas turbine includes a number of annular rotor blade rows coaxially mounted in a heating gas channel and a number of annular stator blade rows mounted between the rotor blade rows, wherein at least between two immediately adjacent stator blade rows a heat shield is positioned, which circumferentially surrounds the rotor blade row positioned between the two adjacent stator blade rows, and which has multiple ring segments, wherein at least one of the ring segments has an abrasion coating and at least one of the ring segments has no abrasion coating. | 05-26-2016 |
| 20160146043 | COOLING APPARATUS FOR TURBOMACHINERY WITH METHOD OF INSTALLATION - Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit. | 05-26-2016 |
| 20160160681 | PLATED POLYMER NACELLE - Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure. | 06-09-2016 |
| 20160177758 | ANGLED RAIL HOLES | 06-23-2016 |
| 20160177959 | FRACTURE-RESISTANT SELF-LUBRICATING WEAR SURFACES | 06-23-2016 |
| 20160186779 | COMPRESSOR COVER WITH INTEGRATED HEAT SHIELD FOR AN ACTUATOR - The disclosure describes a compressor housing for a turbocharger system. A scroll section of a collecting volute may be defined by a wall of the compressor housing. The scroll section may extend around the axis of the compressor from an inlet of the volute to a scroll discharge stage. A plate section of the compressor housing may extend from the wall in a radial direction outward from the axis and may extend in a circumferential direction around a substantial portion of the collecting volute. The plate section may be configured to shield heat and may advantageously be formed integral with the compressor housing. | 06-30-2016 |
| 20160201472 | VANE, GAS TURBINE PROVIDED WITH THE SAME, METHOD OF MANUFACTURING VANE, AND METHOD OF REMODELING VANE | 07-14-2016 |
| 20160201485 | Support Buttress | 07-14-2016 |
| 20160201489 | CRIMPED INSERT FOR IMPROVED TURBINE VANE INTERNAL COOLING | 07-14-2016 |
| 20160201565 | METHOD AND SYSTEM FOR SEALING AN ANNULUS | 07-14-2016 |
| 20160376897 | LOW LOSS BAFFLED SERPENTINE TURNS - A vane includes a forward rib and an aft rib positioned axially aft of the forward rib. The vane also includes a middle rib positioned axially between the forward rib and the aft rib, such that the forward rib and the middle rib define a forward passage configured to receive a forward baffle and the middle rib and the aft rib define an aft passage configured to receive an aft baffle. The vane also includes an inner surface extending axially from the forward rib to the aft rib, being radially separated from the middle rib via a gap such that air can flow between the aft passage and the forward passage via the gap, and having a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the aft rib. | 12-29-2016 |
| 20160377085 | FAN MODULE AND HAT WITH FAN MODULE - A fan module and a hat with a fan module are disclosed. The fan module includes a case, a fan, and an air guide tube. The case includes a connecting portion, wherein the case is detachably engaged with a visor of a hat. The case has a receiving space and an air outlet, wherein the air outlet communicates with the receiving space. The fan is rotatably provided in the receiving space of the case. An airflow is generated when the fan rotates, wherein the airflow is exhausted out of the case through the air outlet. The air guide tube is connected to the case, and guides the airflow to a space between the head of a wearer and the main body. Whereby, the hat with the fan module could provide not only sunscreen protection, but also a cooling effect. | 12-29-2016 |
| 20170234154 | Turbine stator vane with closed-loop sequential impingement cooling insert | 08-17-2017 |
| 20180023417 | MULTI-PLY HEAT SHIELD ASSEMBLY WITH INTEGRAL BAND CLAMP FOR A GAS TURBINE ENGINE | 01-25-2018 |
| 20190145318 | DENDRITIC HEAT EXCHANGERS AND METHODS OF UTILIZING THE SAME | 05-16-2019 |
