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公开(公告)号：US12158110B2
公开(公告)日：2024-12-03
申请号：US18107671
申请日：2023-02-09
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan
Abstract: A gas turbine engine includes a propulsor having blades extending from a propulsor hub. A compressor section includes a first compressor and a second compressor. A speed reduction device includes an epicyclic gear system. The epicyclic gear system includes a sun gear, a plurality of intermediate gears, a carrier supporting the intermediate gears and the propulsor hub, and a ring gear. A turbine section includes a first turbine and a second turbine. The second turbine drives the propulsor through the epicyclic gear system. The epicyclic gear system is straddled by forward and aft bearings that engage the carrier.
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公开(公告)号：US20230366330A1
公开(公告)日：2023-11-16
申请号：US18358524
申请日：2023-07-25
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F01D25/18 , B01D19/0073 , F01D25/20 , F02C7/06 , B01D19/0068 , F05D2260/609 , Y02T50/60
Abstract: A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed.
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公开(公告)号：US20230122298A1
公开(公告)日：2023-04-20
申请号：US18068660
申请日：2022-12-20
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a propulsor section and a speed change mechanism for driving the propulsor section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers extending from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first propulsor section support bearing is mounted on a first axial side of the speed change mechanism and a second propulsor section support bearing is mounted on the bearing support on a second axial side of the speed change mechanism. The second propulsor section support bearing is a propulsor thrust bearing. Each of the plurality of fingers include a pin opening with a pin extending through the pin opening and into the epicyclic gear train.
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公开(公告)号：US11608779B2
公开(公告)日：2023-03-21
申请号：US16786421
申请日：2020-02-10
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A turbofan engine includes a fan that delivers air into a bypass duct and into a core engine. A fan drive gear system includes a gear carrier and at least one ring gear. The at least one ring gear is coupled to an engine case of the turbofan engine with a compliant flexure. A fan shaft couples the gear carrier in the fan drive gear system to the fan. A first bearing is forward of the fan drive gear system and supports the fan drive gear system. A second bearing is aft of the fan drive gear system and supports the fan drive gear system.
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45.发明授权公开(公告)号：US11519338B1
公开(公告)日：2022-12-06
申请号：US17578818
申请日：2022-01-19
Applicant: Raytheon Technologies Corporation
Inventor： William C. Sheridan , William G. Sheridan
IPC: F02C7/32 , F02C7/36 , F02K3/04 , F16H1/20 , F16D41/069
Abstract: An oil system for a gas turbine engine includes an oil pump driven by a gear train having a main input drive gear rotating when a propulsor rotor rotates. The gear train includes two sets of gears joined by two connection shafts each having a clutch. The first set of the gears include a forward input gear and a reverse input gear each driven by the main input drive gear. The forward and the reverse input gears drive a pinion gear in the second set of gears through a clutch. Each clutch transmits rotation driven in a same driving direction and slips in an alternate driving direction. The first set of the gears has an even number of the gears, and the second set of the gears has an odd number of the gears.
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Patent Agency Ranking
公开(公告)号：US11448310B2
公开(公告)日：2022-09-20
申请号：US17365220
申请日：2021-07-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling an epicyclic gear train includes positioning a carrier, the carrier being a unitary structure with side walls and mounts unitary with one another, inserting intermediate gears through a central opening of the carrier, moving each of the intermediate gears into intermediate gear pockets, inserting baffles into the carrier, inserting a sun gear through the central opening, and moving the intermediate gears to intermesh with the sun gear, and moving a ring gear into engagement with the intermediate gears.
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公开(公告)号：US11434829B2
公开(公告)日：2022-09-06
申请号：US17236850
申请日：2021-04-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
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公开(公告)号：US20220235712A1
公开(公告)日：2022-07-28
申请号：US17717888
申请日：2022-04-11
Applicant: Raytheon 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：US11339723B2
公开(公告)日：2022-05-24
申请号：US14431839
申请日：2013-03-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , William G. Sheridan , Glenn Levasseur
Abstract: A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency.
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公开(公告)号：US20220128060A1
公开(公告)日：2022-04-28
申请号：US17570728
申请日：2022-01-07
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
IPC: F04D25/16 , F02C7/06 , F01D21/04 , F01D21/02 , F02C7/36 , F01D5/02 , F01D15/12 , F04D25/04 , F04D29/041 , F04D29/046 , F16H1/28 , F16H57/10
Abstract: A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.
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