Patent application number | Description | Published |
20090090096 | Epicyclic gear train for variable cycle engine - A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the speed of the drive shaft. The stationary torque tube is connected with a fan case in the gas turbine engine. The gear system is connected to the second-stage fan shaft and the torque tube. The first-stage fan shaft extends from the gear system such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft. | 04-09-2009 |
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 |
20100212281 | AUXILIARY PUMP SYSTEM FOR FAN DRIVE GEAR SYSTEM - A pump system for lubricating a bearing in a gear system includes an auxiliary pump connected to the gear system. The auxiliary pump is fluidically connected to the bearing through an auxiliary supply passage and to a reservoir through an auxiliary scavenge passage. An auxiliary valve is fluidically connected to the auxiliary supply passage for transferring liquid from the auxiliary pump to the bearing when a pressure in the auxiliary supply passage downstream of the auxiliary valve is less than a particular threshold and for transferring liquid from the auxiliary pump to the reservoir when the pressure in the auxiliary supply passage downstream of the auxiliary valve is greater than the particular threshold. A method for circulating liquid is also included. | 08-26-2010 |
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 |
20110297485 | MULTI-STAGE AMPLIFICATION VORTEX MIXTURE FOR GAS TURBINE ENGINE COMBUSTOR - A lubrication system, includes an auxiliary lubricant tank | 12-08-2011 |
20120088624 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - A lubricating system for lubricating components across a rotation gap has an input that provides lubricant to a stationary first bearing. The first bearing has an inner first race in which lubricant flows. A second bearing rotates within the first bearing and has a first opening in registration with the inner first race such that lubricant may flow from the inner first race through the first opening into a first conduit. | 04-12-2012 |
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 |
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 |
20120272762 | FAN DRIVE GEAR SYSTEM INTEGRATED CARRIER AND TORQUE FRAME - A fan gear drive system includes a torque frame having a base with integrated gear shafts circumferentially spaced relative to one another. Each shaft provides a shaft axis. A bearing assembly is mounted on each of the gear shafts and provides a bearing assembly. The bearing assembly includes a spherical bearing configured to permit angular movement of the bearing axis relative to the shaft axis. | 11-01-2012 |
20120277055 | FAN DRIVE PLANETARY GEAR SYSTEM INTEGRATED CARRIER AND TORQUE FRAME - A fan gear drive system includes a torque frame having a base with integrated gear shafts circumferentially spaced relative to one another. A fan shaft is integrated with the base, such that the torque frame provides rotational output from the fan gear drive system. Each shaft provides a shaft axis. A bearing assembly is mounted on each of the gear shafts and provides a bearing assembly. The bearing assembly includes a spherical bearing configured to permit angular movement of the bearing axis relative to the shaft axis. | 11-01-2012 |
20130004297 | DUAL FAN GAS TURBINE ENGINE AND GEAR TRAIN - A gas turbine engine includes a first fan, a second fan spaced axially from the first fan, a turbine-driven fan shaft and an epicyclic gear train coupled to be driven by the turbine-driven fan shaft and coupled to drive the first fan and the second 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. The star gears are supported on respective journal bearings. | 01-03-2013 |
20130016936 | DUAL MODEL SCAVENGE SCOOP - A system for removing oil from a bearing compartment has a port connected to an end wall of the compartment through which the oil exits the compartment, a scavenge scoop connected to the port for collecting the oil, and a separation device connected to the scavenge scoop for creating an oil collection region. | 01-17-2013 |
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 |
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 |
20130098058 | SPLIT ACCESSORY DRIVE SYSTEM - A gas turbine engine includes a spool, a first accessory gearbox, a second accessory gearbox, and a scavenge pump. The first accessory gearbox is connected to and driven by the spool. The second accessory gearbox is connected to and driven by the first accessory gearbox. The scavenge pump is connected between the first accessory gearbox and the second accessory gearbox. The first accessory gearbox drives the second accessory gearbox through the scavenge pump. | 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 |
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 |
20130195647 | GAS TURBINE ENGINE BEARING ARRANGEMENT INCLUDING AFT BEARING HUB GEOMETRY - An example gas turbine engine includes a housing and first and second spools coaxial with one another and arranged within the housing. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool. First and second bearings support the aft end of the first spool relative to the housing. An example method of assembling the gas turbine engine includes arranging a first spool within a second spool. First and second bearings are mounted between an aft end of the first spool and a fixed housing. | 08-01-2013 |
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 |
20130319798 | AUXILIARY OIL SYSTEM FOR NEGATIVE GRAVITY EVENT - A lubrication system includes a bearing compartment. A main reservoir is fluidly connected to the bearing compartment by a main supply passage. A main pump is arranged in the main supply passage configured to provide fluid from the main reservoir to the bearing compartment during a positive gravity condition. A secondary supply passage fluidly connects the main reservoir to at least one segment of the main supply passage, thereby providing fluid from the main reservoir to the bearing compartment during a negative gravity condition. A method of supplying a bearing compartment with fluid includes pumping a fluid from a main reservoir to a bearing compartment through a main supply passage during a positive gravity condition, and providing fluid from the main reservoir to the bearing compartment through a secondary supply passage, fluidly connected to at least one segment of the main supply passage, in response to a negative gravity condition. | 12-05-2013 |
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 |
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 |
20140062026 | FACE SEAL RETAINING ASSEMBLY FOR GAS TURBINE ENGINE - A face seal assembly for a gas turbine engine includes an engine static structure. A guide assembly supports a face seal for movement relative to the engine static structure in an axial direction. The guide assembly includes a guide pin having a first end that supports a washer that is retained by a circlip secured to the first end. The circlip is configured to limit movement of the face seal in the axial direction. | 03-06-2014 |
20140083107 | Method for Setting a Gear Ratio of a Fan Drive Gear System of a Gas Turbine Engine - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps. | 03-27-2014 |
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 |
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 |
20140140824 | OIL SYSTEM BEARING COMPARTMENT ARCHITECTURE FOR GAS TURBINE ENGINE - A gas turbine engine with a geared architecture includes a multiple of bearing compartments and at least one carbon seal that seals at least one side of each of the multiple of bearing compartments. | 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 |
20140155213 | GEARED ARCHITECTURE GAS TURBINE ENGINE WITH IMPROVED LUBRICATION AND MISALIGNMENT TOLERANT ROLLER BEARING SYSTEM - A gas turbine engine includes a structural oil baffle housing which at least partially supports a set of intermediate gears. | 06-05-2014 |
20140178180 | 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 thermal energy equal to less than about 2% of power input into the gear system. | 06-26-2014 |
20140193238 | METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE - A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0. | 07-10-2014 |
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 |
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 |
20140234078 | METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE - A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0. | 08-21-2014 |
20140271135 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 09-18-2014 |
20140274531 | FAN DRIVE PLANETARY GEAR SYSTEM INTEGRATED CARRIER AND TORQUE FRAME - A fan gear drive system includes a fan shaft, a turbine shaft, a fixed structure, and a gear train which includes a torque frame that comprises a base with integrated gear shafts that are circumferentially spaced relative to one another. Each shaft provides a shaft axis. Intermediate gears are supported on each bearing assembly for rotation about the bearing axis. A central gear is located radially inward from and intermeshes with the intermediate gears. A ring gear is arranged about and intermeshes with the intermediate gears. One of the torque frame, central gear and ring gear is connected to the fan shaft. Another of the torque frame, central gear and ring gear is connected to the turbine shaft. The remaining of the torque frame, central gear and ring gear is connected to the fixed structure. A bearing assembly is mounted on each of the gear shafts and provides a bearing axis. Each bearing assembly supports the respective intermediate gear. | 09-18-2014 |
20140314541 | TURBOMACHINE THRUST BALANCING SYSTEM - An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine. | 10-23-2014 |
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 |
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 |