21st week of 2016 patent applcation highlights part 29 |
Patent application number | Title | Published |
20160146017 | LEADING EDGE COOLING CHANNEL FOR AIRFOIL - Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil. | 2016-05-26 |
20160146018 | TAPERED COOLING CHANNEL FOR AIRFOIL - The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil. | 2016-05-26 |
20160146019 | COOLING CHANNEL FOR AIRFOIL WITH TAPERED POCKET - The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil. | 2016-05-26 |
20160146020 | BRAZING METHOD FOR REINFORCING THE Z-NOTCH OF TiAl BLADES - The present invention relates to a method for arranging a reinforcement ( | 2016-05-26 |
20160146021 | COMPOSITE BLADES FOR GAS TURBINE ENGINES - A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk. | 2016-05-26 |
20160146022 | HIGH-MODULUS COATING FOR LOCAL STIFFENING OF AIRFOIL TRAILING EDGES - An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed. | 2016-05-26 |
20160146023 | Rotor With Blades Secured by Woven Fiber Attachment System - A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor. | 2016-05-26 |
20160146024 | HYBRID BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME - Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A hybrid bonded turbine rotor comprises a turbine disk and a plurality of turbine blades each metallurgically bonded to a corresponding raised blade attachment surface of a plurality of raised blade attachment surfaces of the turbine disk to define a bond plane located at a selected radial position. Turbine disk has a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with the plurality of raised blade attachment surfaces defining the outer periphery. The selected radial position is outboard of the live rim. Each pair of adjacent turbine blades defines a shank cavity therebetween. The shank cavity extends radially outwardly from the live rim and includes a live rim notch disposed below the bond plane and above the live rim. | 2016-05-26 |
20160146025 | VARIABLE PITCH FAN FOR GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME - A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core. The variable pitch fan has a disk and at least nine fan blades coupled to the disk for rotation together with the disk. The gas turbine engine further includes a rotatable nacelle covering the disk such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4. | 2016-05-26 |
20160146026 | TRANSITION DUCT ARRANGEMENT IN A GAS TURBINE ENGINE - An arrangement for a gas turbine engine includes a combustor for producing a working medium by combustion of a mixture of fuel and an oxidant, a turbine section comprising a stationary vane carrier on which a first row of stationary vanes is arranged, and a transition duct for leading the working medium from the combustor to the turbine section. The transition duct has a forward end that adjoins the combustor and an aft end that adjoins the stationary vane carrier. The transition duct has a transition duct axis extending from the forward end to the aft end along a straight line. The transition duct axis is normal to a vane axis of a stationary vane in the first row of stationary vanes. | 2016-05-26 |
20160146027 | GUIDE VANE RING AND TURBOMACHINE - The invention is directed to a guide vane ring for a turbomachine, in which a vane bearing is produced in the inner ring via platform plates of the vanes and reliability against disintegration is produced via journals that extend radially inward from the platform plates, as well as a turbomachine. | 2016-05-26 |
20160146028 | HIGH STRENGTH JOINTS IN CERAMIC MATRIX COMPOSITE PREFORMS - A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body. | 2016-05-26 |
20160146029 | SEALING BUSH CARRIER FOR A STEAM TURBINE AND STEAM TURBINE - A sealing bush carrier for a steam turbine, the steam turbine at least having a turbine rotor and a turbine housing, whereby the sealing bush carrier is arranged between a shaft of the rotor and the housing. The sealing bush carrier includes at least two hollow passages which extend from the rotor-facing part of the sealing bush carrier to the housing-facing part of the sealing bush carrier and are constructed such that they can be assigned to likewise hollow openings in the housing for an extraction of steam of the turbine through the passages of the sealing bush carrier into the openings of the housing. A steam turbine has a rotor with a shaft, a housing and a sealing bush carrier of this sort. | 2016-05-26 |
20160146030 | NON-METALLIC ENGINE CASE INLET COMPRESSION SEAL FOR A GAS TURBINE ENGINE - A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section. | 2016-05-26 |
20160146031 | TURBINE BLADE OR VANE HAVING A STEPPED AND BEVELED PLATFORM EDGE - A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided. | 2016-05-26 |
20160146032 | Pressure Seal With Non-Metallic Wear Surfaces - A gas turbine engine has a first component and a second component. The first and second components have a high-pressure chamber on one side and a low pressure chamber on an opposed side. A three sided seal has one side facing each of the first and second components, and a third side facing a third component. At least one non-metallic wear surface is between one of the three sides of the seal and the facing component. | 2016-05-26 |
20160146033 | GAS TURBINE ENGINE CLEARANCE CONTROL - A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure. A cover is arranged over the bolted flange joint and discrete from the first and second structures. The cover provides a seal land that engages the piston seal and protects the first structure from the adverse thermal environment. | 2016-05-26 |
20160146034 | ABRADABLE COMPOSITION AND SEAL OF AN AXIAL-FLOW TURBOMACHINE COMPRESSOR CASING - The invention relates to a composition for an abradable seal of a turbomachine, the composition comprising an aluminium base, nickel powder, polyester powder. The invention also relates to an outer casing of a low-pressure compressor of an axial-flow turbomachine with an abradable seal surrounding an annular row of rotor blades. The seal comprises a rounded support covered with a layer of abradable material comprising a metallic phase mainly made of aluminium and with nickel in a lesser proportion. The abradable material additionally comprises from 25% to 55% of additive, such as polyester, methyl methacrylate, hexagonal boron nitride, calcium fluoride. The support is segmented, and forms an organic matrix composite outer casing of the compressor. The invention also proposes a process for producing an abradable seal by plasma spraying an Al—Ni-polyester powder. | 2016-05-26 |
20160146035 | HYBRID RAM AIR TURBINE - A ram air turbine is provided that utilizes a hybrid design. The ram air turbine includes a hydraulic power conversion device directly coupled to a turbine shaft and an electric power conversion device coupled to a drive shaft. A gearbox is used to couple the turbine shaft to the drive shaft. | 2016-05-26 |
20160146036 | ENGINE CASING ELEMENT - An engine casing element comprises at least one clearance control cavity, the clearance control cavity being delimited by a clearance control cavity inner wall and having a clearance control cavity longitudinal extent. At least one insert member is arranged inside the clearance control cavity. The insert member is arranged and configured to effect at least one of a flow guide function and a heat transfer enhancement function. | 2016-05-26 |
20160146037 | VARIABLE TURBINE GEOMETRY VANE WITH SINGLE-AXLE, SELF-CENTERING PIVOT FEATURE - A vane pack assembly ( | 2016-05-26 |
20160146038 | TURBOMACHINE INCLUDING A VANE AND METHOD OF ASSEMBLING SUCH TURBOMACHINE - A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion. | 2016-05-26 |
20160146039 | ACOUSTIC ATTENUATION WITH ADAPTIVE IMPEDANCE - An acoustic liner may include a core with a plurality of resonator chambers, a perforated top sheet coupled to the core, and a backskin coupled to the core. A thermoacoustic speaker including nanomaterials may be coupled to at least one of the core, the backskin, and the perforated top sheet. A voltage may be applied to the thermoacoustic speaker. The thermoacoustic carbon nanotube speaker may create a dynamic excitation within a resonator chamber in the core. The dynamic excitation may change the liner acoustic impedance to achieve optimum noise attenuation over a wide range of frequencies or engine operating conditions. | 2016-05-26 |
20160146040 | Alternating Vane Asymmetry - A vane assembly for a gas turbine engine may include a plurality of vanes being arranged in vane groupings symmetrically spaced circumferentially from each other. Each vane grouping may include at least a first and a second vane. The at least first and second vanes may be spaced from each other at a first pitch. Each vane grouping may be spaced from each other at a second pitch. The first pitch may be dissimilar from the second pitch. | 2016-05-26 |
20160146041 | BLADE OR VANE FOR A TURBOMACHINE AND AXIAL TURBOMACHINE - The present invention relates to a blade ( | 2016-05-26 |
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. | 2016-05-26 |
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. | 2016-05-26 |
20160146044 | INTERNALLY COOLED TURBINE PLATFORM - A turbine flowpath component for a gas turbine engine includes a platform defining at least one internal cooling cavity and a turbine flowpath component cover disposed radially outward of the platform. The turbine flowpath component cover defines a radially outward edge of the at least one internal cooling cavity. The turbine flowpath component cover further defines a transition region in which a radial depth of the at least one internal cooling cavity varies from a first depth to a second depth. | 2016-05-26 |
20160146045 | TURBINE ENGINE ROTOR SHAFT COMPRISING AN IMPROVED HEAT EXCHANGE SURFACE - A turbine engine rotor shaft includes at least one portion having an outer periphery having a determined diameter forming a free surface for heat exchange with the environment of said rotor. The outer periphery comprises includes a plurality of irregularities which are designed to provide a heat exchange surface of the shaft of the rotor which is greater than a surface of the periphery of a cylinder having the same determined average diameter. | 2016-05-26 |
20160146046 | RADIALLY STACKED INTERSHAFT BEARING - An exemplary gas turbine engine includes a radially stacked intershaft bearing assembly. The assembly includes an outer stubshaft having outer and inner diameter surface portions disposed concentrically with respect to one another. The outer diameter surface portion is rotatably connected to a body of the engine, and the inner diameter surface portion is rotatably connected to an inner stubshaft of the engine, so as to provide a stacked configuration of the inner stubshaft, the outer stubshaft, and the body along a radial direction orthogonal to a longitudinal axis of the engine. | 2016-05-26 |
20160146047 | TURBOCHARGER ROLLER SUPPORT SYSTEM - Disclosed is an embodiment of a turbocharger roller support system that utilizes roller-shaft interfaces that are slanted to locate a turbocharger shaft with a turbine and compressor. Slanted contact surfaces on the turbocharger shaft are slanted inwardly so that the turbo shaft remains centered in the roller support system. The rollers entirely locate the turbocharger shaft, so that no bearings are necessary directly on the turbocharger shaft. The rollers spin at a slower speed than the turbocharger shaft, so can utilize lower speed bearings. | 2016-05-26 |
20160146048 | LUBRICATION OF JOURNAL BEARING DURING CLOCKWISE AND COUNTER-CLOCKWISE ROTATION - The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counterclockwise. | 2016-05-26 |
20160146049 | SEALING INTERFACE FOR A CASE OF A GAS TURBINE ENGINE - A case assembly for a gas turbine engine, includes a case with an oversized case boss, said oversized case boss including a peripheral wall that defines a first inner diameter in a first condition to receive a piston seal, and a second inner diameter in a second condition, the second condition including enlargement of the first inner diameter to form a second inner diameter and a bushing mounted within the second inner diameter, an inner diameter of the bushing defines a bushing inner diameter about equivalent to the first inner diameter to receive the piston seal. | 2016-05-26 |
20160146050 | FAN CASE LINER REMOVAL WITH EXTERNAL HEAT MAT - A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel. | 2016-05-26 |
20160146051 | TURBINE ENGINE CASING HAVING A CUT-OUT FLANGE - The present invention relates to a turbine engine casing ( | 2016-05-26 |
20160146052 | FORGED CAST FORGED OUTER CASE FOR A GAS TURBINE ENGINE - A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section. | 2016-05-26 |
20160146053 | BLADE OUTER AIR SEAL SUPPORT STRUCTURE - A support structure for a gas turbine engine includes an axially extending portion that forms a loop. A radially extending portion extends radially inward from the axially extending portion. A plurality of retention members are attached to at least one of the axially extending portion and the radially extending portion for retaining a blade outer air seal. | 2016-05-26 |
20160146054 | CASING SUPPORT STRUCTURE - A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing, the structure comprising a shroud having a plurality of sectors ( | 2016-05-26 |
20160146055 | LINER HANGER WITH SPHERICAL WASHERS - A liner assembly for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A hanger assembly supports the liner relative to the duct. The hanger assembly includes a body segment attached to the liner and first and second washers defining a gap therebetween that receives a portion of the body segment. The gap between the washers and the body segment provides for relative movement caused by differences in thermal growth within the liner. An attachment member extending between the body section and the duct includes spherical ends that are seated on the first and second washers to accommodate misalignments during assembly. | 2016-05-26 |
20160146056 | DEVICE AND METHOD FOR SEPARATING DIRT PARTICLES FROM THE WORKING MEDIUM OF A TURBINE - The invention relates to a device and a method for separating dirt particles from the working medium of a turbine ( | 2016-05-26 |
20160146057 | WATER REMOVAL DEVICE FOR STEAM TURBINE - A hollow portion is formed inside a stator blade. A slit having an inlet opening on a pressure surface of the stator blade facing wet steam flow is formed that communicates with the hollow portion in the axial direction of the stator blade. The hollow portion communicates with a region having a lower pressure than the flow field of the wet steam flow. The pressure in the hollow portion is reduced to introduce water film flow formed from water drops on the pressure surface of the stator blade to the slit. The slit is formed at a downstream side end, in the flow direction of the wet steam flow, of the hollow portion, and the stator blade trailing edge side wall surface of the slit is at an acute angle to a leading edge side reference plane of the pressure side of the stator blade. | 2016-05-26 |
20160146058 | Method for Energy Saving - Method for coupling a first heat-requiring industrial process to a second cold-requiring industrial process, whereby a first circuit for energy recovery ( | 2016-05-26 |
20160146059 | METHOD AND DEVICE FOR CONTROLLING THE SPRAYING OF WATER INTO THE FLUE GAS DUCT OF A GAS AND STEAM TURBINE INSTALLATION - A method for operating a gas and steam turbine installation, wherein the heat contained in the expanded flue gas of the gas turbine is used to generate steam for the steam turbine. If a critical operating state arises, the temperature of the expanded flue gas is reduced by introducing water into the expanded flue gas in the flue gas duct between the gas turbine and the waste-heat steam generator connected downstream with regard to flow, wherein the amount of water to be introduced is determined in dependence on the flue gas temperature. The flue gas temperature is measured before water is introduced into the flue gas, an average combustion temperature of the combustion chamber of the gas turbine is determined from the flue gas temperature, and the amount of water to be introduced is set on the basis of the combustion temperature. | 2016-05-26 |
20160146060 | METHOD FOR OPERATING A COMBINED CYCLE POWER PLANT - A method for operating a combined cycle power plant, according to which shortly before the planned start-up of a parked load, the steam turbine is lowered to a very low output, the gas turbine is then operated in parked load, and next the steam turbine is powered up to a parked output. The GT operating power can be the rated power of the gas turbine. The ST operating power can be the rated power of the steam turbine. | 2016-05-26 |
20160146061 | ELECTROTHERMAL ENERGY STORAGE SYSTEM AND AN ASSOCIATED METHOD THEREOF - An electrothermal energy storage and discharge system is provided including a charging cycle and a discharging cycle. The charging cycle includes a refrigeration unit and a thermal unit, and the discharging cycle includes a power unit. The refrigeration unit is driven by an excess electric power and is configured to generate a cold energy storage having a solid carbon dioxide. The thermal unit is driven by a thermal energy and is configured to generate a hot energy storage and/or provide a hot source. The power unit operates between the cold energy storage and at least one of the hot energy storage and hot source so as to retrieve the energy by producing a high pressure carbon dioxide and a hot supercritical carbon dioxide, and generating an electric energy using the hot supercritical carbon dioxide. | 2016-05-26 |
20160146062 | CAMSHAFT ASSEMBLY FOR AN INTERNAL COMBUSTION ENGINE - A camshaft assembly for an internal combustion engine includes a camshaft, a first lobe set, and a second lobe set, extending along, and rotatable about, a cam axis. The first lobe set includes a first, second, and third lobe. The second lobe set includes a first and second lobe. The first lobe set is movable along the cam axis between a first, second, and third position. The second lobe set is movable along the cam axis between a first and second position. The first and second position of each of the first and second lobe sets corresponds to lift of a respective valve stem in the engine. The third position of the first lobe set corresponds to zero lift of the respective valve stem to provide cylinder deactivation of a corresponding cylinder within the engine. | 2016-05-26 |
20160146063 | ROCKER ARM FOR ENGINES - A method for repairing a rocker arm including smoothing out a bore in an injector arm of the rocker arm to remove at least a portion of worn threads within the bore, and securing a threaded insert within the bore. The threaded insert may include threads on an internal surface of the threaded insert, a smooth portion on an external surface of the threaded insert, and a flange on an end of the threaded insert. | 2016-05-26 |
20160146064 | LATCH INTERFACE FOR A VALVE ACTUATING DEVICE - A novel latch seat for a switching rocker arm assembly used in variable valve actuation (VVA) systems for internal combustion engines. The seat is formed interactively in the assembled switching rocker arm using a novel fixture and press. The press interactively creates a curved dimple of the correct curvature, position and depth while measuring several lash dimensions. Since the latch seat is formed on the assembled rocker arm assembly, the latch seat depth is designed to account for the inaccuracies in the rocker arm assembly parts which create lash. Therefore all of the parts may be made with less precision since the latch seat is sized to compensate for the inaccuracies of all of the parts. The rocker arm assembly parts now may be manufactured to less stringent standards, but result in a rocker arm assembly with same accuracy of rocker arm assemblies manufactured to previous standards. | 2016-05-26 |
20160146065 | SUPPORT PIN FOR SPRING GUIDANCE IN A CAMSHAFT PHASER - A camshaft phaser including: an axis of rotation; a drive sprocket arranged to receive torque; a stator non-rotatably connected to the drive sprocket; a rotor; and a positioning spring. The rotor is at least partially rotatable with respect to the stator and is arranged to non-rotatably connect to a camshaft. The rotor includes: first and second radially disposed sides facing, respectively, in first and second opposite axial directions parallel to the axis of rotation; a non-circular bore connecting the first and second radially disposed sides; and a support pin including a first portion disposed in the bore and configured to contact an inner radial surface of the bore at a plurality of lines parallel to the axis of rotation less than the entire circumference of the bore; and a second portion extending past the second radially disposed side in the second axial direction. The positioning spring is engaged with the second portion and urges the rotor in a circumferential direction. | 2016-05-26 |
20160146066 | SPRING ARRANGEMENT FOR A VARIABLE VALVE DRIVE OF AN INTERNAL COMBUSTION ENGINE - A spring arrangement for a variable valve drive of an internal combustion engine includes an intermediate lever, a control shaft, a control shaft roller, a working cam contour, and a spring element. The intermediate lever comprises a contact surface, a camshaft roller which bears against a camshaft, and a slot roller which bears against a slotted guide. The control shaft roller is arranged on the intermediate lever to face away from the slotted guide. The control shaft roller bears against the control shaft. The working cam contour is formed at an end of the intermediate lever opposite the camshaft roller. The spring element comprises a force component on the contact surface in the direction of the camshaft and the slotted guide, and an end leg. The spring element loads the camshaft roller against the camshaft and the slot roller against the slotted guide. The end leg bears against the contact surface. | 2016-05-26 |
20160146067 | CAMSHAFT PHASER WITH POSITION CONTROL VALVE - A camshaft phaser includes an input member connectable to the crankshaft of the internal combustion engine; an output member connectable to the camshaft of the internal combustion engine and defining an advance chamber and a retard chamber with the input member; a valve spool coaxially disposed within the output member such that the valve spool is rotatable relative to the output member and the input member, the valve spool defining a supply chamber and a vent chamber with the output member; and an actuator which rotates the valve spool in order to change the position of the output member relative to the input member by supplying pressurized oil from the supply chamber to one of the advance chamber and the retard chamber and venting oil to the vent chamber from the other of the supply chamber and the advance chamber. | 2016-05-26 |
20160146068 | CAMSHAFT PHASER WITH POSITION CONTROL VALVE - A camshaft phaser includes an input member; an output member defining an advance chamber and a retard chamber with the input member; a valve spool coaxially disposed within the output member such that the valve spool is rotatable relative to the output member and the input member, the valve spool defining a supply chamber and a vent chamber with the output member; an actuator which rotates the valve spool in order to change the position of the output member relative to the input member by supplying pressurized oil from the supply chamber to one of the advance chamber and the retard chamber and venting oil to the vent chamber from the other of the supply chamber and the advance chamber; and a check valve which allows oil to flow from the vent chamber to the supply chamber and prevents oil from flowing from the supply chamber to the vent chamber. | 2016-05-26 |
20160146069 | METHOD AND SYSTEM FOR RELEASING JAMMING OF LOCKING PIN BY USE OF HOLDING CONTROL - A method for releasing jamming of a locking pin by use of holding control may include preparing the rotation of a camshaft so that the camshaft rotates in a target direction in a state in which the locking pin is jammed in a locking pin hole; applying a signal for releasing the locking pin from the locking pin hole; performing holding control so that a signal for rotating the camshaft is not applied for a predetermined reference time; and rotating the camshaft in the target direction after the locking pin is released by the performing of the holding control. | 2016-05-26 |
20160146070 | CONTROL DEVICE FOR INTERNAL COMBUSTION ENGINE - A control device for an engine includes a variable valve timing mechanism. The control device performs learning a holding control amount of a hydraulic valve when actual valve timing is held at a fixed timing in each of spring and non-spring regions, and an updating. The updating includes updating the control amount for the non-spring region whenever the control amount for the spring region learned drops below the control amount for the non-spring region to satisfy a relationship with the control amount for the non-spring region being less than or equal to the control amount for the spring region, and/or updating the control amount for the spring region whenever the control amount for the non-spring region learned exceeds the control amount for the spring region to satisfy a relationship with the control amount for the spring region being greater than or equal to the control amount for the non-spring region. | 2016-05-26 |
20160146071 | METHOD AND SYSTEM FOR DETECTING MALFUNCTION OF FASTENING BOLT IN CVVT - A method for detecting malfunction of a fastening bolt in a continuous variable valve timing (CVVT) includes: deciding whether a camshaft position sensor is operating normally; learning the most retarded angle position of the camshaft using the camshaft position sensor; deciding whether the learning of the most retarded angle position of the camshaft is normal; and comparing a PWM duty value used in the learning with a set first reference value when the learning of the most retarded angle position of the camshaft is normal. | 2016-05-26 |
20160146072 | ENGINE SYSTEM AND OPERATION METHOD USING ENGINE BRAKING MECHANISMS FOR EARLY EXHAUST VALVE OPENING - A valve actuation system for an internal combustion engine is disclosed. The engine has a first set of cylinders having a first set of exhaust valves and a second set of cylinders having a second set of exhaust valves. The valve actuation system for the exhaust valves includes one or more first cams having a compression-release lobe and a main exhaust lobe adapted to transfer valve actuation motion to the first set of exhaust valves, and one or more second cams having an early exhaust valve opening (EEVO) lobe and a main exhaust lobe adapted to transfer valve actuation motion to the second set of exhaust valves. The valve actuation system may provide any combination of (i) main exhaust valve actuation with or without compression release actuation with (ii) main exhaust valve actuation with or without EEVO for the two sets of cylinders. | 2016-05-26 |
20160146073 | VARIABLE VALVE GEAR - A variable valve gear for adjusting inlet or exhaust valves of at least two cylinder banks of an internal combustion engine comprising
| 2016-05-26 |
20160146074 | ENGINE BRAKE LASH ADJUSTER DEVICE AND METHOD - A compression brake device and method are provided that include a lash member coupled to a rocker arm. The lash member has a first position that forces opening of the valve when the rocker arm is at the lower position. The brake also includes a lost motion cylinder at least partially defined within the rocker arm. The cylinder is biased towards a position of greatest internal displacement volume. The lost motion cylinder has a first operational mode wherein the lost motion cylinder permits compression thereof such that the ability of the rocker arm to open an exhaust valve is a function of the position of the lash member. The lost motion cylinder has a second operational mode wherein the lost motion cylinder retards compression thereof such that the ability of the rocker arm to open an exhaust valve is independent of the position of the lash member. | 2016-05-26 |
20160146075 | OIL COOLER FOR VEHICLE HAVING BYPASS VALVE OPERATED BY TEMPERATURE OF WORKING FLUID - An oil cooler for a vehicle includes an inflow tank through which a working fluid flows in. An outflow tank is spaced apart from the inflow tank by a predetermined interval and has a discharge hole at one side which faces the inflow tank. A plurality of tubes connect the inflow tank with the outflow tank longitudinally such that the working fluid flows therethrough. A bypass valve is integrally mounted at an outer side of the one end portion of the inflow tank and connected to an inner side of the inflow tank to bypass or flow the working fluid flowed therein into the inflow tank by selectively opening and closing according to a temperature of the working fluid. An outflow pipe has one end mounted to the discharge hole and another end thereof mounted to the bypass valve to connect the outflow tank with the bypass valve. | 2016-05-26 |
20160146076 | VEHICLE WITH INTEGRATED TURBOCHARGER OIL CONTROL RESTRICTION - A vehicle incorporates a turbocharged internal combustion engine and a crankcase ventilation system. That crankcase ventilation system includes a first vent line connecting a cam cover at a first spigot to an air inlet duct at a second spigot. In addition the system includes a second vent line connected between the crankcase and the intake manifold of the engine. A one-way valve is provided in the second vent line. A restriction is integrated into either the first spigot, the second spigot or a quick connect that connects the first vent line to the first or second spigot. | 2016-05-26 |
20160146077 | EXHAUST SYSTEM USING ASH-COMPENSATING REGENERATION MANAGEMENT - An exhaust system for an engine having a throttle is disclosed. The exhaust system may include an exhaust passage connectable to the engine, a particulate filter disposed in the exhaust passage, a sensor configured to generate a signal indicative of a total pressure differential across the particulate filter caused by soot and ash accumulation, a load actuator configured to selectively adjust a load on the engine, and a control module electronically connected to the load actuator and the sensor. The control module may be configured to determine a compensated pressure differential indicative of an amount of the total pressure differential caused by soot accumulation, a soot load of the particulate filter based on the compensated pressure differential, cause the load actuator to initiate a first engine load increase based on the soot load, track a time elapsed since initiation of the first engine load increase, and cause the load actuator to initiate a subsequent engine load increase when the time elapsed is greater than an elapsed time limit and the soot load is greater than a target soot load. | 2016-05-26 |
20160146078 | Pump for pumping a liquid - A pump for pumping a liquid has a pump housing with at least one inlet and at least one outlet. The pump housing has an eccentric rotatable relative to the pump housing by an axle. A deformable element is arranged between the pump housing and the eccentric, and by the deformable element, at least one pump path from the at least one inlet to the at least one outlet is delimited and at least one movable pump path seal is formed, which separates at least one closed pump volume in the pump path. The at least one movable seal is movable in a pump direction from the inlet to the outlet by a movement of the eccentric to pump the fluid along the pump path. The pump has at least one adjustable axial calibrating device, by which the deformable element is clamped in the axial direction parallel to the axle. | 2016-05-26 |
20160146079 | MACHINE BODY AND WORKING MACHINE - A machine body including an exhaust after-treatment apparatus that executes a reduction treatment on a predetermined oxide in exhaust gas from an engine using a liquid reducing agent. A reducing agent tank provided at a position distant from the engine stores the liquid reducing agent, and a working fluid tank positioned between the exhaust after-treatment apparatus and the reducing agent tank stores a working fluid having a high temperature at least during operation of the machine. A reducing agent supply line is arranged along the working fluid tank at a position above a level of the fluid stored in the working fluid tank to supply the liquid reducing agent from the reducing agent tank to the exhaust after-treatment apparatus. Accordingly, the liquid reducing agent stored in reducing agent tank is unlikely to be thermally affected by the engine, and the liquid reducing agent flowing through the reducing agent supply line is unlikely to be thermally affected by the fluid stored in the working fluid tank. | 2016-05-26 |
20160146080 | METHOD AND APPARATUS FOR MONITORING FLUID REDUCTANT FOR INTERNAL COMBUSTION ENGINE EXHAUST - A method and means of determining the quality of a fluid reductant used in selective catalytic reduction to reduce NOx emissions from an internal combustion engine. Short and long term average of NOx conversion efficiency are compared with thresholds, in order to determine if failure of selective catalytic reduction is due to incorrect reductant, or to failure of the catalyst device. | 2016-05-26 |
20160146081 | SILENCER FOR MID-BED AIR INJECTION MIXING - A system includes an exhaust aftertreatment system configured to treat emissions from a combustion engine. The exhaust aftertreatment system includes a first catalyst assembly having an outlet. The exhaust aftertreatment system also includes an ammonia slip catalyst (ASC) assembly configured to receive a fluid from the first catalyst assembly and to convert ammonia (NH3) within the fluid into nitrogen (N2), wherein the ASC assembly has an inlet. The exhaust aftertreatment system further includes a silencer disposed between the outlet of the first catalyst assembly and the inlet of the ASC assembly, wherein the silencer is configured to receive the fluid and an oxidant for mixing with the fluid provide sufficient oxygen in the fluid flowing into the inlet of the ASC assembly to enable the catalytic activity in the ASC assembly that coverts NH3 into N2, and the silencer is configured to mix the fluid and the oxidant. | 2016-05-26 |
20160146082 | Module for the metered provision of a liquid - A module for the metered provision of a liquid includes a chamber having a chamber wall enclosing, at least partially, a chamber space of the chamber. The chamber is surrounded at least partially by a hood. At least one cavity is arranged between the hood and the separated chamber and the hood is heatable. | 2016-05-26 |
20160146083 | CLAMP MOUNTED THERMOELECTRIC GENERATOR - In one embodiment, a system is disclosed that includes a clamp that defines a substantially cylindrical aperture. One or more thermoelectric generator (TEG) layers are coupled to the clamp and receive heat from the clamp. The TEG layers may be formed using thermoelectric nanostructures. One or more heat sinks are also coupled to the one or more TEG layers that provide cooling to the TEG layers. | 2016-05-26 |
20160146084 | THERMOELECTRIC POWER GENERATION APPARATUS - A thermoelectric power generation apparatus includes a heat transfer module configured to be attached to an exhaust manifold or an exhaust pipe; a thermoelectric module configured to be supplied with heat from the heat transfer module; and a cooling module configured to absorb heat from the thermoelectric module. Thus, it is possible to implement a thermoelectric power generation system in the vehicle without changing a shape of an exhaust system and a shape of the thermoelectric module. | 2016-05-26 |
20160146085 | SOx CONCENTRATION DETECTION DEVICE OF INTERNAL COMBUSTION ENGINE - The object of the invention is to detect a concentration of a SOx included in an exhaust gas of an internal combustion engine easily and accurately by a limiting current type sensor. The invention relates to a SOx concentration detection device of the engine having a limiting current type sensor. The device of the invention comprises a detecting part for detecting the concentration of the SOx included in the exhaust gas by using an output current of the sensor while lowering a voltage applied to the sensor from a predetermined voltage. | 2016-05-26 |
20160146086 | EXHAUST SYSTEM STRUCTURE FOR IMPROVING NOISE PROBLEM - An exhaust system structure includes an exhaust manifold discharging exhaust gas through at least one runner towards an exhaust pipe. A front pipe is connected to a front end of the exhaust pipe. A collector connects the at least one runner and the front pipe. The collector comprises at least one inlet communicating with an exit of the at least one runner. An outlet communicates with the front pipe such that the outlet discharges the exhaust gas into the front pipe through the at least one inlet. An extended portion has a radius greater than or equal to that of the exit of the at least one runner. | 2016-05-26 |
20160146087 | MUFFLER SHIELD AND MUFFLER ASSEMBLY EMPLOYING THE SAME - In one or more embodiments, a muffler shield includes a shield body extending in a longitudinal direction and defining a middle portion positioned between first and second side portions along a transverse direction, a cross-section of the middle portion and at least one of the first and second side portions respectively defining a middle profile and a side profile shorter than the middle profile. | 2016-05-26 |
20160146088 | Cooling Fan Assembly - A cooling fan assembly for replacing a vehicle's radiator cooling fan so the vehicle's radiator is cooled more efficiently includes a hub that may be coupled to the vehicle's water pump. A plurality of blades is coupled to and radiates outwardly from the hub. Each of the plurality of blades has a twisted shape. The plurality of blades urges air at a high velocity through the vehicle's radiator when the hub is rotated by the vehicle's water pump. The assembly improves an efficiency of the vehicle's radiator. | 2016-05-26 |
20160146089 | COMPRESSOR COOLING - A cooling arrangement for a compressor drive cone ( | 2016-05-26 |
20160146090 | APPARATUS AND METHOD FOR CONTROLLING COOLING FAN SPEED - An apparatus for controlling a cooling fan speed includes a cooling fan motor operating a cooling fan. A pump is connected to the cooling fan motor in series. A relay has one side connected to the cooling fan motor or the pump and another side connected a battery so that power of the battery may be supplied to any one of the cooling fan motor or the pump. | 2016-05-26 |
20160146091 | APPARATUS AND METHOD FOR CONTROLLING COOLING FAN OF VEHICLE - An apparatus and method for controlling a cooling fan of a vehicle are provided. The apparatus includes an information detector that is configured to detect information for operating the cooling fan and a blower assembly including a motor driving the cooling fan and a resistor adjusting a speed of the motor. A relay unit is configured to selectively supply power to the blower assembly. A connecting unit includes a high speed connector that is directly connected to the motor, a low speed connector that is connected to the motor via the resistor, and a ground connector that connects the motor to a ground. Additionally, a controller is configured to operate the relay unit based on the information detected by the information detector. | 2016-05-26 |
20160146092 | ENGINE SYSTEM HAVING COOLANT CONTROL VALVE - An engine system having a coolant control valve includes a coolant pump pumps a coolant. A cylinder head receives the coolant by a first exhaust side water jacket and discharges the received coolant to a first intake side water jacket. An intake cylinder block receives the coolant by a second exhaust side water jacket and discharges the received coolant to a second intake side water jacket. A coolant control valve selectively blocks the coolant discharged from the first intake side water jacket of the cylinder head and the coolant discharged from the second intake side water jacket of the cylinder block, and separately controls coolants supplied to at least two heat exchangers. The heat exchangers include an oil cooler cooling oil, an exhaust gas recirculation (EGR) cooler cooling a recirculation exhaust gas, a heater core for indoor heating, or a radiator releasing heat of the coolant to outside. | 2016-05-26 |
20160146093 | RADIATOR RESERVOIR TANK AND RADIATOR STRUCTURE - There is provided a radiator reservoir tank including: a tank body that is connected to a radiator and that includes an inlet section and an accumulation section for cooling water; a first rib that is disposed inside the tank body, and that extends out from a side wall at one side of facing side walls of the tank body toward another side, and that partitions between the inlet section and the accumulation section, and that is provided with a gap to the side wall at the other side; and a second rib that is provided further toward the inlet section side or the accumulation section side than the first rib, that extends out from the side wall at the other side toward the one side, and that is provided with a gap to the side wall at the one side. | 2016-05-26 |
20160146094 | SAFETY CAP DEVICE FOR CONTROLLING PRESSURE IN RADIATOR AND METHOD FOR CONTROLLING PRESSURE USING THE SAME - A safety cap device for controlling a pressure in a radiator includes a valve seat provided with a valve receiving space in which a first communicating hole is formed. A negative pressure valve is provided movably in the first communicating hole. A seal is disposed on a receiving surface of the valve seat and disposed movably with the negative pressure valve. The seal has a second communicating hole formed at a central portion thereof. A positive pressure valve is disposed on the seal and has a third communicating hole formed at a central portion thereof. A cap covers an upper portion of the valve seat. A spring is interposed between the positive pressure valve and the cap. A fluid receiving part is in the valve seat to prevent cavitation caused when an internal fluid expands. | 2016-05-26 |
20160146095 | INTAKE-AIR COOLING APPARATUS FOR VEHICLE - An intake-air cooling apparatus for a vehicle includes an intercooler of a turbocharger, and an intake line to which compressed air is supplied from the intercooler. A fluid moving unit is connected at a first side thereof to the intercooler and connected at a second side thereof to the intake line, cools indoor air via a Peltier element. | 2016-05-26 |
20160146096 | ECCENTRIC PLANETARY TRACTION DRIVE SUPER-TURBOCHARGER - Disclosed are embodiments of eccentric planetary traction drives for use in a driven turbocharger. The eccentric planetary provides torque-based loading of the traction interfaces in the traction drive. A loading planet has a larger outer diameter and has translative movement when torque is applied to the traction drive so that it is forced into a wedge gap between the turbo shaft and outer ring of the planetary drive. The torque capacity of the traction drive increases with an increase of torque demand. | 2016-05-26 |
20160146097 | Exhaust System with Exhaust Gas Recirculation and Multiple Turbochargers, and Method for Operating Same - An exhaust system includes a first turbine having an inlet that is fluidly coupled to an exhaust conduit; a valve assembly having an inlet port, a first outlet port, and a second outlet port, the inlet port of the valve assembly being in fluid communication with the exhaust conduit; a second turbine having an inlet that is fluidly coupled to the first outlet port of the valve assembly via a first outlet port conduit, and fluidly coupled to an outlet of the first turbine via a first turbine outlet conduit; and a controller operatively coupled to the valve assembly. The valve assembly has a first configuration that blocks fluid communication between the inlet port and the first outlet port, and the valve assembly has a second configuration that effects fluid communication between the inlet port and the first outlet port. | 2016-05-26 |
20160146098 | Device For Actuating The Wastegate Flap Of An Exhaust Gas Turbocharger - A device actuates a waste gate flap of an exhaust gas turbocharger of an internal combustion engine. The device has an actuator which has an actuator rod, a lever which is connected to the actuator rod and a spindle which is connected to the lever and to which the waste gate flap is secured. A resiliently mounted ball head rod is provided between the actuator rod and the lever. | 2016-05-26 |
20160146099 | ADJUSTABLE-TRIM CENTRIFUGAL COMPRESSOR, AND TURBOCHARGER HAVING SAME - A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry conical mechanism comprising a plurality of vanes that in the closed position collectively form a frusto-conical inlet member having a trailing edge inner diameter that is smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel such that an effective diameter of the air inlet at the inducer portion is determined by the trailing edge inner diameter of the variable-geometry conical mechanism. The vanes in the open position are pivoted radially outwardly so as to increase the trailing edge inner diameter of the inlet member and thereby increase the effective diameter of the air inlet at the inducer portion. | 2016-05-26 |
20160146100 | SYSTEMS AND METHODS FOR A VARIABLE GEOMETRY TURBINE NOZZLE - Various systems and methods are described for a variable geometry turbine. In one example, a nozzle vane includes a stationary having a first cambered sliding surface and a sliding vane having a second cambered sliding surface where the second cambered sliding surface includes a flow disrupting feature in contact with the first sliding cambered surface. The sliding vane may be positioned to slide in a direction from substantially tangent along a curved path to an inner circumference of the turbine nozzle and selectively uncover the flow disrupting feature. | 2016-05-26 |
20160146101 | GAS TURBINE WITH PLURALITY OF TIE RODS AND METHOD OF ASSEMBLING THE SAME - Disclosed herein is a gas turbine with a plurality of tie rods. The gas turbine includes a compressor section having a plurality of compressor-side rotor disks, a turbine section having a plurality of turbine-side rotor disks arranged downstream of the compressor-side rotor disks, a first tie rod penetrating central portions of the rotor disks provided in the compressor section to press the compressor-side rotor disks against each other, a plurality of second tie rods penetrating vicinities of edges of the rotor disks provided in the turbine section to press the turbine-side rotor disks against each other, and a torque transfer member coupled to the first and second tie rods so as to transfer rotational torque generated by the turbine section to the compressor section. | 2016-05-26 |
20160146102 | GEARED ARCHITECTURE GAS TURBINE ENGINE WITH OIL SCAVENGE - A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed. | 2016-05-26 |
20160146103 | GAS TURBINE ENGINE SHAFT MEMBERS AND MAINTENANCE METHOD - A gas turbine engine includes first and second shaft members in an interference fit relationship with one another at an interface. The first and second shaft members respectively include first and second flanges that are arranged adjacent to the interface. The first and second flanges respectively include first and second threads that are configured to cooperate with a tool during disassembly of the first and second shaft members. | 2016-05-26 |
20160146104 | Angled Core Engine - A system, which may be used as a propulsion system, includes a propulsor section having a fluid operated device or free turbine, a fluid source such as a gas generator for creating an exhaust gas, and a fluid passageway for delivering the exhaust gas to the fluid operated device or free turbine. The fluid operated device may be used to drive a rotary device such as a fan. | 2016-05-26 |
20160146105 | Method and Device for Converting Municipal Waste Into Energy - A method and device for converting municipal waste into energy. This method involves heating the waste in multiple sections of a chamber to produce syngas and biochar. The syngas is removed with a vacuum pump and the biochar advances to the next section and is heated to a higher temperature to release more syngas. All of the collected syngas is then transferred to a bio-reactor that removes dangerous carbon monoxide from the syngas mixture by combining the syngas with hydrogen, causing the carbon monoxide to react with the hydrogen and produce methane and water. The resulting syngas can then be used for electricity production or stored as dimethyl ether. | 2016-05-26 |
20160146106 | REDUCTION OF TURBOFAN NOISE - The invention relates to an aircraft turbofan type engine ( | 2016-05-26 |
20160146107 | Variable Supersonic Engine Inlet - Systems and methods for generating an oblique shock in a supersonic inlet are disclosed. The system can comprise an inlet with a slot disposed at an oblique angle to the main incoming air stream. High-pressure air can be provided through the slot into the main air stream. The high-pressure air can be introduced at a high enough pressure ratio—i.e., the ratio of pressure of the air stream from the slot to the pressure for the main flow—such that an aerodynamic ramp is created in the main air flow. The aerodynamic ramp, in turn, can cause one or more oblique shock waves to eventually slow the main air stream velocity to a subsonic speed prior to the face of the engine. Systems and methods for controlling the slot pressure ratio to create these shocks are also disclosed. | 2016-05-26 |
20160146108 | FUEL PUMPING UNIT - A fuel pumping unit has a low pressure centrifugal pump and a high pressure centrifugal pump. In use, the low pressure pump supplies fuel at a boosted pressure to the high pressure pump for onward supply to a fuel metering unit. The pumping unit further has a drive input which drives the low and high pressure pumps. A gear arrangement is operatively located between the drive input and the low and high pressure pumps such that the low and high pressure pumps are driven at different speeds by the drive input. | 2016-05-26 |
20160146109 | COMPACT AERO-THERMO MODEL BASED CONTROL SYSTEM ESTIMATOR STARTING ALGORITHM - Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. The model processor may include an input object for processing model input and setting a model operating mode, the model operating mode being a starting mode if the model input is within a data range associated with a starting operation of the control device. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of the open loop model. | 2016-05-26 |
20160146110 | OPTIMIZATION OF COLD STARTS IN THERMAL POWER STATIONS, IN PARTICULAR IN STEAM-ELECTRIC POWER PLANTS OR IN COMBINED CYCLE POWER PLANTS (CCPPS) - A thermal power plant, in particular to a steam-electric power plant or a combined cycle power plant (CCPP), and a method for operating a thermal power plant is adapted to accelerate, or to technically and/or economically optimize the start-up of the thermal power plant, in particular to accelerate/optimize a cold-start phase of the thermal power station. The thermal power plant has an auxiliary energy store integrated into the power plant. The store, during the start-up of the thermal power plant, delivers energy for heating/pre-heating components and/or media of the thermal power plant, or supplies an electrical power distribution network. | 2016-05-26 |
20160146111 | COMPACT STRUCTURE FOR ACCESSORY GEARBOX OF AN AIRCRAFT TURBINE ENGINE - An aircraft drive chain including a plurality of main gears engaging with each other, a first main gear including a wall defining an inner space, an outer set of gear teeth being placed on an outer surface of the wall, the outer set of gear teeth engaging with at least one second main gear, a gear system being built into the inner space, the first main gear and the gear system being jointly configured so as to form a gearbox or reducer and ensure mechanical power transfer between a drive member and a slave member, the gear system being mounted onto the wall with a decoupling member. | 2016-05-26 |
20160146112 | LIGHTWEIGHT GEAR ASSEMBLY FOR EPICYCLIC GEARBOX - An epicyclic gearbox comprises a gearbox housing including an inner cavity receiving an input shaft from a low pressure turbine and an output shaft connected to a fan. A sun gear is disposed within the housing and at least one planetary gear engages and orbits the sun gear. The at least one planetary gear is formed of a first material and an insert is disposed between a gear rim of the at least one planetary gear and a journal. The insert is formed of a second material distinct from the first material and of a weight which is lighter than the first material. The gearbox may include but is not limited to both star gearbox and planetary gearbox configurations. | 2016-05-26 |
20160146113 | GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME - A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct for airflow generated by the fan. The fan cowl includes an aft edge that defines a physical flow area of the bypass duct, and a deflection device configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine. | 2016-05-26 |
20160146114 | ENVIRONMENTAL AIR CONDITIONING SYSTEM - An environmental air conditioning system is described for conditioning compressed air for supply as conditioned air. The system includes an airflow path to which the compressed air for ultimate distribution as conditioned air (i.e., airflow path compressed air) is supplied. Then airflow path has various components of an air cycle system, and also includes a power turbine outside of the air cycle that receives compressed air and discharges it as exhaust. The power turbine transfers power to a compressor in the air cycle system. | 2016-05-26 |
20160146115 | GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME - A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC. | 2016-05-26 |
20160146116 | METHOD FOR OPTIMIZING THE CONTROL OF A FREE TURBINE POWER PACKAGE FOR AN AIRCRAFT, AND CONTROL FOR IMPLEMENTING SAME - A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply. | 2016-05-26 |