Patent application number | Description | Published |
20090071121 | COUNTER-ROTATING GEARBOX FOR TIP TURBINE ENGINE - A tip turbine engine ( | 03-19-2009 |
20090081039 | GAS TURBINE ENGINE FRONT ARCHITECTURE MODULARITY - A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox. | 03-26-2009 |
20090092487 | Systems and Methods Involving Multiple Torque Paths for Gas Turbine Engines - Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other. | 04-09-2009 |
20090188334 | Accessory Gearboxes and Related Gas Turbine Engine Systems - Accessory gearboxes and related gas turbine engine systems are provided. In this regard, a representative accessory gearbox for a gas turbine engine is operative to be driven by rotational energy extracted from the gas turbine engine and imparted to the gearbox by multiple tower shafts. | 07-30-2009 |
20090293278 | METHOD OF MAKING INTEGRAL SUN GEAR COUPLING - A method of constructing an integral coupling system containing a sun gear is disclosed. An integral sun gear is provided that has a sun gear component and a connection shaft. A first straight flat inner edge is machined on a first diaphragm to use as a datum point, and then the straight flat edge is fixtured. A tapered outer edge is machined on the first diaphragm, and the first diaphragm is welded to the integral sun gear. The flat inner edge is generally perpendicular to a central axis of the connection shaft. | 12-03-2009 |
20090298640 | INTEGRAL SUN GEAR COUPLING - A coupling system for connecting a sun gear to a shaft within a planetary gear train, includes a sun gear coupling connecting the sun gear to the shaft. The sun gear coupling has at least one undulant flexible section joined to an inflexible spindle for accommodating misalignment between the sun gear and the shaft. The flexible section comprises a cylindrical ring having a diameter greater than the diameter of the spindle, and joined to the spindle by two longitudinally spaced apart diaphragms. The juncture between the diaphragms, the ring, and the spindle is curved in cross section on an outer side to improve flexibility and minimize stress concentrations, and the inner sides of the diaphragms are straight edges which result in a non-symmetric contour of the diaphragm walls. | 12-03-2009 |
20100086403 | LUBRICATION OF WINDMILLING JOURNAL BEARINGS - A support shaft provides lubrication to a journal bearing during windmilling operation of a gear set. A primary oil pump provides oil from an oil supply during driven operation of the fan, and a secondary oil pump provides oil from an internal sump during windmilling operation of the fan. During driven operation of the fan, oil is pumped with the primary oil pump through a primary oil flow path to an outer surface of the support shaft. During windmilling fan operation, oil is pumped from an internal sump with a secondary oil pump through the secondary oil flow path. The secondary oil flow path has a smaller flow capacity, and the secondary oil pump is a smaller capacity pump. | 04-08-2010 |
20100105516 | COUPLING SYSTEM FOR A STAR GEAR TRAIN IN A GAS TURBINE ENGINE - A star gear train for use in a gas turbine engine includes a sun gear, a ring gear, a plurality of star gears and a coupling system. The sun gear is rotatable by a shaft. The ring gear is secured to a ring gear shaft. Each of the plurality of star gears is rotatably mounted in a star carrier and meshes with the sun gear and the ring gear. The coupling system comprises a sun gear flexible coupling, a carrier flexible coupling and a deflection limiter. The sun gear flexible coupling connects the sun gear to the shaft. The carrier flexible coupling connects the carrier to a non-rotating mechanical ground. The deflection limiter is connected to the star carrier to limit excessive radial and circumferential displacement of the star gear train. | 04-29-2010 |
20100150702 | FLEXIBLE SHAFT FOR GAS TURBINE ENGINE - A shaft for a gas turbine engine is provided that includes a first shaft section, a second shaft section, a first flexible linkage, and a second flexible linkage. The first shaft section extends between a forward axial end and an aft axial end along a first axial centerline. The second shaft section extends between a forward axial end and an aft axial end along a second axial centerline. The first flexible linkage includes a bridge section connected between a first diaphragm and a second diaphragm. The first diaphragm is connected to the aft axial end of the first shaft section. The second diaphragm is connected to the forward axial end of the second shaft section. The second flexible linkage includes a diaphragm and a hub. The second flexible linkage diaphragm cantilevers radially outwardly from an inner radial end to an outer radial end, and is connected to the aft axial end of the second shaft section. The hub is connected to the outer radial end of the second flexible linkage diaphragm, and includes an engine shaft coupling connected to the hub. | 06-17-2010 |
20100154217 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A gas turbine engine includes an epicyclic gear train that drives a turbo fan. The epicyclic gear train employs a one-piece carrier in which the spaced side walls are interconnected with circumferentially spaced apart mounts to form a unitary structure. Baffles are secured to the carrier near the mounts and provide lubrication passages that spray oil onto the sun gear and/or intermediate gears arranged between the baffles. The baffles can be constructed from a different material than the carrier since the baffles are not structural components in the gear train. | 06-24-2010 |
20100160105 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A gas turbine engine includes an epicyclic gear train that drives a turbo fan. The epicyclic gear train employs a one-piece carrier in which the spaced side walls are interconnected with circumferentially spaced apart mounts to form a unitary structure. Baffles are secured to the carrier near the mounts and provide lubrication passages that spray oil onto the sun gear and/or intermediate gears arranged between the baffles. The baffles can be constructed from a different material than the carrier since the baffles are not structural components in the gear train. | 06-24-2010 |
20100317477 | EPICYCLIC GEAR SYSTEM WITH IMPROVED LUBRICATION SYSTEM - A journal bearing that includes a central body having first and second passageways and a filter. The central body extends axially and is adapted to be supported at each outer end. The first passageway extends generally axially through a portion of the central body. The filter is disposed in the first passageway and is configured to trap debris from a lubricant fluid flowing therethrough. The second passageway extends between both the first passageway and an exterior surface of the central body to allow for delivery of lubricant fluid thereto. | 12-16-2010 |
20100317478 | JOURNAL BEARING WITH SINGLE UNIT JUMPER TUBE AND FILTER - A journal bearing includes a central body having first passageway and a filter module. The central body extends axially and is adapted to be supported at each outer end. The first passageway extends generally axially through a portion of the central body. The filter module is disposed in the first passageway and is configured to trap debris from a lubricant fluid flowing therethrough. In one embodiment, the filter module is adapted to be inserted and removed from the first passageway as a single unit, thereby allowing the filter module to be connected and disconnected from fluid communication with a lubricant manifold positioned adjacent the journal bearing. | 12-16-2010 |
20100331139 | EPICYCLIC GEAR SYSTEM WITH SUPERFINISHED JOURNAL BEARING - An epicyclic gear assembly includes a ring gear, a sun gear, at least one star gear enmeshed between the ring gear and sun gear, a carrier and a journal bearing. The carrier is disposed adjacent the rotatable sun gear and star gear. The journal bearing is disposed in the at least one star gear and connected to the carrier. The journal bearing has an outer radial surface with an amorphous surface finish of less than about 5 micro inches (127 micro mm) measured on an R | 12-30-2010 |
20100331140 | EPICYCLIC GEAR SYSTEM WITH LOAD SHARE REDUCTION - A journal bearing includes a main body and a connection portion. The main body extends radially outward from a central cavity to an interface surface. The connection portion supports an end of the main body and extends radially around the central cavity. The connection portion has a dimension selected as a proportion of a reference dimension of the main body to achieve a desired spring rate for the journal bearing. | 12-30-2010 |
20110130246 | MOUNTING SYSTEM FOR A PLANATARY GEAR TRAIN IN A GAS TURBINE ENGINE - A mounting system for a planetary gear train in a gas turbine engine comprises a support strut, a deflection flange and a deflection limiter. The support strut extends between a stationary engine case and a rotating engine shaft that provides input to the planetary gear train in the gas turbine engine. The deflection flange extends from a rotating output component of the planetary gear train. The deflection limiter is connected to the support strut and engages the deflection flange when the gear train becomes radially displaced. | 06-02-2011 |
20110200424 | COUNTER-ROTATING GEARBOX FOR TIP TURBINE ENGINE - A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased. | 08-18-2011 |
20110297485 | MULTI-STAGE AMPLIFICATION VORTEX MIXTURE FOR GAS TURBINE ENGINE COMBUSTOR - A lubrication system, includes an auxiliary lubricant tank | 12-08-2011 |
20120090329 | SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES - Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other. | 04-19-2012 |
20120102971 | TAPERED BEARINGS - A gear support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing are arranged axially forward of the epicyclic gear arrangement and support the epicyclic gear arrangement. | 05-03-2012 |
20120103728 | LUBRICATION SYSTEM WITH TOLERANCE FOR REDUCED GRAVITY - A lubrication system includes an auxiliary lubricant tank | 05-03-2012 |
20120121378 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine and a compressor hub driven by the first shaft. The compressor hub is within a compressor section of the gas turbine engine. An epicyclic gear train is driven by the first shaft. A common attachment point secures the first shaft and the compressor hub to the second shaft. | 05-17-2012 |
20120189430 | RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME - A turbine engine includes an input shaft and a fan shaft rotatable about an axis. The fan shaft supports fan blades. An epicyclic gear train is connected between the input shaft and the fan shaft. The epicyclic gear train includes a plurality of star gears, a carrier supporting the plurality of star gears, a sun gear that meshes with the plurality of star gears and a ring gear surrounding and meshing with the plurality of star gears such that the sun gear is rotatable in a first direction and the ring gear is rotatable in a second, opposite direction. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions include respective recesses facing one another to provide an internal annular cavity. | 07-26-2012 |
20120192570 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed. | 08-02-2012 |
20120213628 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture with a flex mount for a fan drive gear system. | 08-23-2012 |
20120216548 | SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES - Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative method for reducing overspeed potential of a turbine of a gas turbine engine includes: providing a first load to the turbine via a first torque path; providing a second load to the turbine via a second torque path; and operating the turbine such that: mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path; and mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path. | 08-30-2012 |
20120234019 | TAPERED BEARINGS - A gear support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing are arranged axially forward of the epicyclic gear arrangement and support the epicyclic gear arrangement. | 09-20-2012 |
20120237334 | GAS TURBINE ENGINE GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3 | 09-20-2012 |
20120237335 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture with a flex mount for a fan drive gear system. | 09-20-2012 |
20120237336 | GAS TURBINE ENGINE GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3 | 09-20-2012 |
20120238391 | RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME - A turbine engine includes an input shaft and a fan shaft rotatable about an axis. The fan shaft supports fan blades. An epicyclic gear train is connected between the input shaft and the fan shaft. The epicyclic gear train includes a plurality of star gears, a carrier supporting the plurality of star gears, a sun gear that meshes with the plurality of star gears and a ring gear surrounding and meshing with the plurality of star gears such that the sun gear is rotatable in a first direction and the ring gear is rotatable in a second, opposite direction. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions include respective recesses facing one another to provide an internal annular cavity. | 09-20-2012 |
20120238401 | EPICYCLIC GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3. | 09-20-2012 |
20120243971 | EPICYCLIC GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3. | 09-27-2012 |
20120260623 | COUPLING SHAFT FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A coupling shaft assembly for a gas turbine engine includes a forward coupling shaft section with a forward interface spline and a forward mid shaft interface spline and an aft coupling shaft section includes an aft mid shaft interface spline and an aft interface spline, the aft mid shaft interface spline engageable with the forward mid shaft interface spline. | 10-18-2012 |
20120275904 | GAS TURBINE ENGINE LUBRICATION - A turbine engine includes a fan shaft and at least one tapered bearing mounted on the fan shaft. The fan shaft includes at least one radially extending passage adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3 | 11-01-2012 |
20120302391 | UNINTERRUPTIBLE OIL SUPPLY IN PLANETARY SYSTEM - A planetary carrier includes a journal bearing for supporting a planetary gear. The journal bearing receives lubricant to produce a lubricant film to support gear loads. A torque frame is attached to the carrier housing to transmit torque and to prevent twisting of the carrier housing. The torque frame includes several lubricant communication passages to provide lubricant to each of the separate journal bearings. Each of the lubricant communication passages includes an accumulator for storing lubricant during normal operation. The accumulator stores a desired amount of lubricant to provide lubricant to the adjacent journal bearing for the interim period between primary system stoppage and reestablishment of lubricant flow by a secondary system. | 11-29-2012 |
20120309582 | JOURNAL PIN FOR GEAR SYSTEM - An example turbomachine epicyclic gear system includes a sun gear rotatable around an axis, a ring gear radially outward of the sun gear, and a plurality of intermediate gears meshed with the sun gear and the ring gear. A plurality of journal pins are each configured to support one of the plurality of intermediate gears. Each of the plurality of journal pins has an asymmetric rim. | 12-06-2012 |
20130023378 | Method of Assembly for Gas Turbine Fan Drive Gear System - A method of assembling an epicyclic gear train includes the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears is inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend through the apertures. A sun gear is inserted through the central opening. The plurality of intermediate gears is moved radially inwardly to engage the sun gear. A gear reduction is also disclosed. | 01-24-2013 |
20130035190 | JOURNAL PIN OIL SUPPLY FOR GEAR SYSTEM - An example journal pin includes a generally cylindrical body disposed on an axis having a supply passage. A first chamber and a second chamber are disposed in the generally cylindrical body and are in fluid communication with the supply passage. A recess on an outer diameter of the cylindrical body is in fluid communication with the first chamber and the second chamber. The first chamber and second chamber are each radially outward of the supply passage and including an outlet to the recess. The first chamber and second chamber each have a first section radially inward of a second section. A cross sectional area of the second section is greater than a cross sectional area of the corresponding first section. | 02-07-2013 |
20130051984 | TORQUE FRAME AND ASYMMETRIC JOURNAL BEARING FOR FAN DRIVE GEAR SYSTEM - A fan drive gear system for a gas turbine engine includes a torque frame and a journal bearing. The torque frame has an arm that extends therefrom, the journal bearing is mounted on the arm. When the fan drive gear system is in an unloaded condition an outer circumferential surface of the journal bearing is disposed at an angle so that it is non-parallel with respect to an axis of the arm. When the fan drive gear system is in a loaded condition the outer circumferential surface is disposed substantially parallel to the axis of the arm. In another aspect, the journal bearing includes a main body, a first wing, and a second wing. The first and second wings extend from the main body and are asymmetric with respect to one another. | 02-28-2013 |
20130098047 | COMPARTMENT COOLING FOR A GAS TURBINE ENGINE - A gas turbine engine includes a first pump driven by a spool, an air-oil cooler downstream of the first pump. A second pump driven by the spool and an air-air precooler downstream of the second pump, the air-air precooler downstream of the air-oil cooler. A compartment is downstream of the precooler to receive a cooling air from the precooler. | 04-25-2013 |
20130098057 | CONTROLLABLE SPEED WINDMILL OPERATION OF A GAS TURBINE ENGINE THROUGH LOW SPOOL POWER EXTRACTION - A gas turbine engine that includes at least one component geared to a spool to control a speed of the low spool during a “windmilling” condition. | 04-25-2013 |
20130098059 | WINDMILL OPERATION OF A GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes a windmill pump driven by a spool. | 04-25-2013 |
20130178327 | COUPLING SYSTEM FOR A STAR GEAR TRAIN IN A GAS TURBINE ENGINE - A star gear train for use in a gas turbine engine includes a sun gear, a ring gear, a plurality of star gears and a coupling system. The sun gear is rotatable by a shaft. The ring gear is secured to a ring gear shaft. Each of the plurality of star gears is rotatably mounted in a star carrier and meshes with the sun gear and the ring gear. The coupling system comprises a sun gear flexible coupling, a carrier flexible coupling and a deflection limiter. The sun gear flexible coupling connects the sun gear to the shaft. The carrier flexible coupling connects the carrier to a non-rotating mechanical ground. The deflection limiter is connected to the star carrier to limit excessive radial and circumferential displacement of the star gear train. | 07-11-2013 |
20130186058 | GEARED TURBOMACHINE FAN AND COMPRESSOR ROTATION - A high-bypass ratio geared turbomachine comprises a compressor section of a high-bypass ratio geared turbomachine. The compressor section provides at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan. | 07-25-2013 |
20130192264 | TURBINE ENGINE GEARBOX - An example method of controlling performance of gearbox of a gas turbine engine includes establishing a gear characteristic of a plurality of double helical gears each disposed about a respective axis in a gearbox. Performance of the plurality of double helical gears is controlled by selecting a circumferential offset distance between a first plurality of gear teeth spaced apart from a second plurality of gear teeth on each of the plurality of double helical gears in response to the established gear characteristic. | 08-01-2013 |
20130195603 | TURBOMACHINE FAN CLUTCH - An exemplary turbomachine clutch assembly includes a clutch that moves from a first position to a second position in response to rotation of a turbomachine fan at a speed greater than a threshold speed. The clutch permits rotation of the turbomachine fan in a first direction whether the clutch is in the first position or the second position. The clutch limits rotation of the turbomachine fan in an opposite, second direction when the clutch is in the first position. | 08-01-2013 |
20130219913 | GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION - A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described. | 08-29-2013 |
20130223983 | COUNTER ROTATING LOW PRESSURE TURBINE WITH SPLITTER GEAR SYSTEM - A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. | 08-29-2013 |
20130223991 | GAS TURBINE ENGINE DRIVING MULTIPLE FANS - A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor. | 08-29-2013 |
20130223994 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A turbine engine includes a housing supporting compressor, turbine sections, and an epicyclic gear train including a carrier. Sun gear and intermediate gears are arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubrication on the at least one of the sun gear and intermediate gears. | 08-29-2013 |
20130287575 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 10-31-2013 |
20130331223 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A geared architecture for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan shaft, a frame which supports the fan shaft, the frame defines a frame stiffness and a plurality of gears which drives the fan shaft. A flexible support defines a flexible support stiffness that is less than the frame stiffness. The plurality of gears are supported by at least one of a carrier and the flexible support and an input coupling to the plurality of gears, the input coupling defines an input coupling stiffness with respect to the frame stiffness. | 12-12-2013 |
20130331224 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A geared architecture for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan shaft and a frame which supports the fan shaft, the frame defines a frame stiffness. A plurality of gears drives the fan shaft. A flexible support at least partially supports the plurality of gears, the flexible support defines a flexible support stiffness that is less than the frame stiffness. An input coupling to the plurality of gears, the input coupling defines an input coupling stiffness with respect to the frame stiffness. | 12-12-2013 |
20130336791 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 12-19-2013 |
20140000721 | TURBOMACHINE FLUID DELIVERY SYSTEM | 01-02-2014 |
20140011623 | COUPLING SYSTEM FOR A GEAR TRAIN IN A GAS TURBINE ENGINE - An engine comprises a gear system and a coupler. The gear system comprises a sun gear, a ring gear, and a plurality of intermediate gears that engage the sun and ring gears. The coupler is for connecting the gear system to an engine static structure. The coupler is configured to limit deflection of the gear system. Two of the sun gear, the ring gear, and the plurality of intermediate gears are configured to rotate and/or orbit about a central axis. The third of the sun gear, the ring gear, and the plurality of intermediate gears is connected to the coupler and is configured not to orbit and/or rotate relative to the central axis. | 01-09-2014 |
20140020404 | FUNDAMENTAL GEAR SYSTEM ARCHITECTURE - A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system. | 01-23-2014 |
20140031162 | UNINTERRUPTIBLE OIL SUPPLY IN PLANETARY SYSTEM - A planetary carrier includes a journal bearing for supporting a planetary gear. The journal bearing receives lubricant to produce a lubricant film to support gear loads. A torque frame is attached to the carrier housing to transmit torque and to prevent twisting of the carrier housing. The torque frame includes several lubricant communication passages to provide lubricant to each of the separate journal bearings. Each of the lubricant communication passages includes an accumulator for storing lubricant during normal operation. The accumulator stores a desired amount of lubricant to provide lubricant to the adjacent journal bearing for the interim period between primary system stoppage and reestablishment of lubricant flow by a secondary system. | 01-30-2014 |
20140045645 | Method of Assembly for Gas Turbine Fan Drive Gear System - A method of mounting a gear train to a torque frame includes providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining mounts for interconnecting the walls. Spaced apart apertures are provided between the mounts at an outer circumference of the carrier. Gear pockets are provided between the walls and mounts extending to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears and a sun gear are inserted in the carrier. A first ring gear half is placed about the outer periphery of the intermediate gears, and attach a torque frame to the carrier. | 02-13-2014 |
20140087907 | GEAR CARRIER FLEX MOUNT LUBRICATION - An example epicyclic gear train assembly includes a flexure pin received by a carrier. The flexure pin and the carrier respectively include first and second pin apertures configured to receive a retainer pin. The flexure pin further includes a lubricant conduit separate from the first pin aperture. | 03-27-2014 |
20140096508 | SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES - A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft configured to be driven by the turbine section and coupled to the compressor section through a first torque load path, and a speed reduction mechanism configured to be driven by the shaft through a second torque load path separate from the first load path for rotating the fan. | 04-10-2014 |
20140099187 | OIL BAFFLE FOR GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM - An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine, a compressor hub driven by the second shaft, the compressor hub within a compressor section of the gas turbine engine, an epicyclic gear train that is driven by the first shaft, and a common attachment point that secures the first shaft and the compressor hub to the second shaft. | 04-10-2014 |
20140133958 | Flexible Support Structure For A Geared Architecture Gas Turbine Engine - A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed. | 05-15-2014 |
20140140819 | Flexible Support Structure For A Geared Architecture Gas Turbine Engine - A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to the support lateral stiffness. A method of designing a gas turbine engine is also disclosed. | 05-22-2014 |
20140154054 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A turbine engine comprises compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and intermediate gears. A method of designing a turbine engine is also disclosed. | 06-05-2014 |
20140155219 | TURBINE ENGINE GEARBOX - A gas turbine engine comprises a fan, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement. Each of the at least two double helical gears are disposed to rotate about respective axes, and each have a first plurality of gear teeth axially spaced from a second plurality of gear teeth by a spacer. Each of the first plurality of gear teeth has a first end facing the spacer and each of the second plurality of gear teeth has a first end facing the spacer. Each first end of the first plurality of gear teeth is circumferentially offset from each first end of the second plurality of gear teeth. | 06-05-2014 |
20140194240 | JOURNAL PIN OIL SUPPLY FOR GEAR SYSTEM - An example journal pin includes a generally cylindrical body disposed on an axis having a supply passage. A first chamber and a second chamber are disposed in the generally cylindrical body and are in fluid communication with the supply passage. A recess on an outer diameter of the cylindrical body is in fluid communication with the first chamber and the second chamber. The first chamber and second chamber are each radially outward of the supply passage and including an outlet to the recess. The first chamber and second chamber each have a first section radially inward of a second section. A cross sectional area of the second section is greater than a cross sectional area of the corresponding first section. | 07-10-2014 |
20140206496 | METHOD OF ASSEMBLY FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A method of assembling an epicyclic gear train comprises the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures. A central opening is in at least one of the walls. A plurality of intermediate gears are inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend into the apertures. A sun gear is inserted through the central opening. The plurality of intermediate gears is moved radially inwardly to engage the sun gear. | 07-24-2014 |
20140216053 | GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION - A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described. | 08-07-2014 |
20140230452 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations. | 08-21-2014 |
20140234079 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 08-21-2014 |
20140256504 | MOUNTING SYSTEM FOR A PLANATARY GEAR TRAIN IN A GAS TURBINE ENGINE - A mounting system for a planetary gear train in a gas turbine engine comprises a support strut, a deflection flange and a deflection limiter. The support strut extends between a stationary engine case and a rotating engine shaft that provides input to the planetary gear train in the gas turbine engine. The deflection flange extends from a rotating output component of the planetary gear train. The deflection limiter is connected to the support strut and engages the deflection flange when the gear train becomes radially displaced. | 09-11-2014 |
20140271135 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 09-18-2014 |
20140286755 | RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME - A turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section. The epicyclic gear train includes a plurality of intermediate gears. A carrier supports the plurality of intermediate gears. A sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis. An epicyclic gear train for a turbine engine and method of designing an epicyclic gear train are also disclosed. | 09-25-2014 |
20140294558 | TURBOMACHINE FLUID DELIVERY MANIFOLD AND SYSTEM - An example turbomachine fluid delivery manifold provides a journal fluid path and a gear mesh fluid path that is separate from the journal fluid path. An example turbomachine lubrication system includes a geared architecture having a journal bearing and a gear. In this example, a manifold provides a portion of a first fluid path and a portion of a second fluid path separate from the first fluid path. The first fluid path is operative to communicate a first fluid from a fluid supply to the journal bearing. The second fluid path is operative to communicate a second fluid from the fluid supply to a gear mesh. | 10-02-2014 |
20140348635 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A turbine engine includes a housing supporting compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle is supported relative to the carrier and includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and the intermediate gears. A spray bar is external to the carrier and is in communication with the lubrication passage. The spray bar terminates near the sun gear for directing lubricant on the sun gear. | 11-27-2014 |
20140366548 | TURBINE ENGINE GEARBOX - A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement. Each of the at least two double helical gears are disposed to rotate about respective axes, and each have a first plurality of gear teeth axially spaced from a second plurality of gear teeth by a spacer. Each of the first plurality of gear teeth has a first end facing the spacer and each of the second plurality of gear teeth has a first end facing the spacer. Each first end of the first plurality of gear teeth is circumferentially offset from each first end of the second plurality of gear teeth. A method is also disclosed. | 12-18-2014 |
20140369818 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - A gas turbine engine includes a fan, a speed reduction device driving the fan and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows and a second race. A second bearing for rotation is within the first bearing including a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar. | 12-18-2014 |
20150051040 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - An epicyclic gear train component includes spaced apart walls with circumferentially spaced mounts that interconnect the walls. The mounts provide circumferentially spaced apart apertures between the mounts at an outer circumference of the walls. Baffles are arranged between the walls near the mounts. Gear pockets are provided between the baffles and the baffles include a lubrication passage that terminates at least one of the gear pockets. One of the walls includes a hole which has a tube that extends through the hole and is received in an opening in the baffle. The tube is in communication with the lubrication passage. | 02-19-2015 |
20150065285 | 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. | 03-05-2015 |