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公开(公告)号：US11300057B2
公开(公告)日：2022-04-12
申请号：US15981559
申请日：2018-05-16
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
IPC: F02C7/36 , F02K3/04 , F16D41/069 , F16H1/20
Abstract: A gas turbine engine including a fan and an oil pump operatively connected to the fan by a main input drive gear, the drive gear rotating when the fan rotor rotates in either a first or second direction of the fan. Further included is a gear train intermediate the main input drive gear and the oil pump, the gear train including a first and second pinion gear, the first and second pinion gear each driven by the main input drive gear, the first pinion gear driving a first gear through a first clutch, the second pinion gear driving a second gear through a second clutch. Only one of the clutches transmits rotation from the respective pinion gear to the respective gear when the fan is rotating in the first direction, with the only the other clutch transmitting rotation when the fan is rotating in the second direction.
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公开(公告)号：US11125167B2
公开(公告)日：2021-09-21
申请号：US16291392
申请日：2019-03-04
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
Abstract: 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.
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公开(公告)号：US11079007B2
公开(公告)日：2021-08-03
申请号：US16833754
申请日：2020-03-30
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling an epicyclic gear train includes providing a unitary carrier that includes spaced apart walls and circumferentially spaced mounts interconnecting the walls, spaced apart apertures provided between the mounts at an outer circumference of the carrier, gear pockets provided between the walls and mounts extending to the apertures, and a central opening in at least one of the walls, inserting an intermediate gear through the central opening and moving the intermediate gear radially into the gear pocket to extend through the aperture, inserting a baffle into the carrier, and inserting a sun gear through the central opening to intermesh with the intermediate gear.
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公开(公告)号：US11028717B2
公开(公告)日：2021-06-08
申请号：US15632628
申请日：2017-06-26
Applicant: United Technologies Corporation
Inventor： Armando Amador , Nasr A. Shuaib , Martin J. Walsh , William G. Sheridan , Eric A. Grover
Abstract: A bearing assembly according to an example of the present disclosure includes, among other things, a bearing situated in a bearing compartment, a seal assembly that defines the bearing compartment, at least one deflector between the bearing and the seal assembly that is rotatable about an axis, and a coalescer at least partially extending about the at least one deflector to define a fluid passage. A method of sealing is also disclosed.
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公开(公告)号：US20210148454A1
公开(公告)日：2021-05-20
申请号：US16689695
申请日：2019-11-20
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a star gear system. The star gear system includes a plurality of star gears surrounding a sun gear. A carrier supports the plurality of star gears and includes a first carrier bearing flange. A ring gear surrounds the plurality of star gears and includes a ring gear bearing flange. At least one ring gear carrier bearing engages the carrier bearing flange and the ring gear bearing flange. A speed change mechanism for a gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US10787930B2
公开(公告)日：2020-09-29
申请号：US15934616
申请日：2018-03-23
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine includes a fan driven by a fan drive turbine through a gear reduction. An oil pump is driven by a main input gear, and the main input drive gear rotates when the fan rotor rotates. A gear train is intermediate the main input gear and the oil pump. The gear train includes a forward input gear and a reverse input gear, each driven by the main input gear. The forward input gear drives a forward pinion gear through a first clutch and the reverse input gear drives a reverse pinion gear through a reverse clutch. The forward clutch transmits rotation from the forward input gear to the forward pinion gear when the fan is rotating in a first direction, and not transmitting rotation from the forward input gear to the forward pinion gear when the fan is rotating in a second opposed direction. The reverse clutch transmits rotation from the reverse input gear to the reverse pinion gear when the fan is rotating in the second opposed direction, and not transmitting rotation from the reverse input gear to the reverse pinion gear when the fan is rotating in the first direction. One of the forward and reverse pinion gears drive a pump drive gear, to, in turn, drive the pump.
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公开(公告)号：US10767753B2
公开(公告)日：2020-09-08
申请号：US15132650
申请日：2016-04-19
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gear system for a turbofan engine assembly includes a sun gear rotatable about an engine centerline, a non-rotatable ring gear, and a rotating carrier that drives a fan. A plurality of planet gears is intermeshed between the sun gear and the ring gear. A rolling element bearing assembly supports rotation of the planet gear on the carrier. The rolling element bearing assembly includes a rolling element between an inner race and an outer race separated by a cage. A first passage for lubricant through the planet gear. A second passage is in communication with the first passage for communicating lubricant through the inner race to an interface between the inner race and the cage. A geared turbofan engine is also disclosed.
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公开(公告)号：US10760488B2
公开(公告)日：2020-09-01
申请号：US15013125
申请日：2016-02-02
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , William G. Sheridan
IPC: F02C1/00 , F02C7/06 , F02K1/09 , F02C7/36 , F02C3/107 , F02K3/04 , F01D5/02 , F01D9/06 , F01D17/10 , F02C3/06 , F02C3/10 , F04D29/32 , F01D5/06 , F02C3/04 , F02C7/28 , F02C9/18 , F02K1/06 , F02K3/06 , F04D29/38 , F16H1/28
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.
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公开(公告)号：US10724445B2
公开(公告)日：2020-07-28
申请号：US15860770
申请日：2018-01-03
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling a fan drive gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier defining a central axis and that includes spaced apart walls and circumferentially spaced mounts defining spaced apart apertures at an outer circumference of the carrier, gear pockets defined between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes the steps of inserting a plurality of intermediate gears through the central opening, moving the intermediate gears radially outwardly relative to the central axis into the gear pockets, inserting a sun gear through the central opening, moving the plurality of intermediate gears radially inwardly relative to the central axis to engage the sun gear, and coupling a fan shaft to the carrier such that the fan shaft and intermediate gears are rotatable about the central axis. A fan drive gear system is also disclosed.
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公开(公告)号：US20200217273A1
公开(公告)日：2020-07-09
申请号：US16812636
申请日：2020-03-09
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.
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