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1. 发明授权

US11629666B2 Turbofan engine 有权
公开(公告)号：US11629666B2
公开(公告)日：2023-04-18
申请号：US17184903
申请日：2021-02-25
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Aviad Brandstein , Avi Ponchek
IPC分类号： F02K3/04 , F01D5/02 , F01D9/02 , F01D15/10 , F02C3/04 , F02K3/06
摘要： A method for converting a turbofan engine including providing a turbofan engine and converting the turbofan engine. The turbofan engine includes a core engine (including at least one high pressure spool assembly and a combustion chamber), and an unmodified fan configured for providing at least a bypass flow bypassing the core engine, the fan being mechanically coupled to a low pressure turbine that is in turn driven by the core engine. The conversion includes modifying or replacing the unmodified fan to provide a modified fan, the modified fan configured for generating a reduced bypass flow with respect to said fan bypass flow during operation of the converted turbofan engine corresponding to at least one set of engine conditions, enabling said low pressure turbine to generate an excess shaft power above a baseline shaft power required for driving the modified fan during operation of the converted turbofan engine.

2. 发明授权

US11572834B2 Gas turbine engine cooling system 有权
公开(公告)号：US11572834B2
公开(公告)日：2023-02-07
申请号：US17152139
申请日：2021-01-19
申请人： Rolls-Royce plc
发明人： Manuel Diaz Brito
IPC分类号： F02C7/18 , F02K3/04
摘要： Gas turbine engine including a nacelle and an engine core within the nacelle. The engine core defines a principal rotational axis along its length. The engine core and nacelle define a bypass passage therebetween. The gas turbine engine further includes a cooling system including a cooling duct, which duct defines an inlet for receiving bypass air from the bypass passage at an upstream location and an outlet for discharging the bypass air at a downstream location. The cooling duct extends, relative to the principal axis, axially and circumferentially around a section of the engine core. The cooling duct comprises: first portion that extends at least axially relative to the principal rotational axis; second portion downstream of the first portion that extends circumferentially around the engine core relative to the principal rotational axis; and third portion downstream of second portion that extends at least axially relative to the principal rotational axis.

3. 发明授权

US11525406B2 Turbine engine gearbox 有权
公开(公告)号：US11525406B2
公开(公告)日：2022-12-13
申请号：US17023860
申请日：2020-09-17
申请人： Raytheon Technologies Corporation
发明人： Michael E. McCune
IPC分类号： F02C7/36 , F16H1/28 , F01D15/12 , F02K3/072 , F16H57/00 , F16H1/46 , F02K3/04
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a compressor section, and a turbine section including a fan drive turbine that 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 having a first plurality of gear teeth separated from a second plurality of gear teeth such that a first end of the first plurality of gear teeth and a first end of the second plurality of gear teeth are spaced apart by an axial distance. Each of the first plurality of gear teeth is offset a first circumferential offset distance in relation to the next gear tooth of the second plurality of gear teeth when moving in a circumferential direction relative to respective axes.

4. 发明授权

US11300057B2 Gear train for gas geared gas turbine engine 有权
公开(公告)号：US11300057B2
公开(公告)日：2022-04-12
申请号：US15981559
申请日：2018-05-16
申请人： United Technologies Corporation
发明人： William G. Sheridan
IPC分类号： F02C7/36 , F02K3/04 , F16D41/069 , F16H1/20
摘要： 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.

5. 发明授权

US11280267B2 Geared turbofan engine gearbox arrangement 有权
公开(公告)号：US11280267B2
公开(公告)日：2022-03-22
申请号：US17007166
申请日：2020-08-31
申请人： Raytheon Technologies Corporation
发明人： Frederick M. Schwarz , William G. Sheridan
IPC分类号： F02C7/36 , F02C7/06 , F02K1/09 , 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
摘要： A gas turbine engine according to the present disclosure includes, among other things, a fan section having a plurality of fan blades, the plurality of fan blades having a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath, and a core engine including a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section.

6. 发明授权

US11274828B2 Article with bond coat layer and layer of networked ceramic nanofibers 有权
公开(公告)号：US11274828B2
公开(公告)日：2022-03-15
申请号：US16270645
申请日：2019-02-08
申请人： United Technologies Corporation
发明人： Zhongfen Ding
IPC分类号： F23R3/00 , C04B35/10 , C04B35/48 , C04B35/622 , F02K3/04
摘要： An article includes a substrate, a bond coat layer disposed on the substrate, and a layer of networked ceramic nanofibers disposed on the bond coat layer.

7. 发明授权

US11230975B2 Modulated fire extinguishing vent for a gas turbine engine 有权
公开(公告)号：US11230975B2
公开(公告)日：2022-01-25
申请号：US16358760
申请日：2019-03-20
申请人： United Technologies Corporation
发明人： Nigel David Sawyers-Abbott , Federico Papa
IPC分类号： F02C7/25 , A62C3/08 , F02C9/18 , F02C9/34 , F02K3/04 , B64D45/00
摘要： A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

8. 发明授权

US11225881B2 Hybrid propulsion systems 有权
公开(公告)号：US11225881B2
公开(公告)日：2022-01-18
申请号：US16184725
申请日：2018-11-08
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Stephen Andrew Long
IPC分类号： B64D27/24 , F01D15/10 , F02K3/04 , B64D27/14 , B64D27/02
摘要： An example hybrid aircraft propulsion system includes one or more parallel propulsion units, each of the parallel propulsion units comprising: a first propulsor; a gas turbine engine configured to drive the first propulsor; and an electrical machine selectively configurable to: generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the first propulsor or the gas turbine engine; and drive the first propulsor using electrical energy received via the one or more electrical busses; and one or more series propulsion units, each of the series propulsion units comprising: a second propulsor; and an electrical machine selectively configurable to: generate, for output via the one or more electrical busses, electrical energy using mechanical energy derived from the second propulsor or the gas turbine engine; and drive the second propulsor using electrical energy received from one or more electrical busses.

9. 发明授权

US11149689B2 Gas turbine engine shaft bearing configuration 有权
公开(公告)号：US11149689B2
公开(公告)日：2021-10-19
申请号：US16152502
申请日：2018-10-05
申请人： Raytheon Technologies Corporation
发明人： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
IPC分类号： F02C7/36 , F02K3/00 , F01D25/16 , F02K3/04 , F02C7/06 , F02C3/04
摘要： A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.

10. 发明授权

US11089389B2 Remote communication and powered sensing/control/identification devices using high temperature compatible semiconductor materials 有权
公开(公告)号：US11089389B2
公开(公告)日：2021-08-10
申请号：US16572046
申请日：2019-09-16
申请人： United Technologies Corporation
发明人： Joseph V. Mantese , Kurt J. Sobanski
IPC分类号： G06F19/00 , G06G7/70 , H04Q9/00 , H01Q5/55 , F01D21/00 , H04L12/24 , H04Q1/02 , H04Q1/28 , F02K3/06 , G07C5/00 , H04B15/02 , G01M15/14 , H04B1/02 , F02C3/04 , F02C9/00 , H01P3/12 , H01P5/02 , H05K9/00 , H04L12/40 , G06K7/10 , G07C5/08 , F02K3/04 , H04B1/3822 , G08C17/00 , G08C19/12 , H04L29/08 , H04W84/18 , H04W84/12
摘要： A system includes a network of a plurality of sensing/control/identification devices distributed throughout a machine, each of the sensing/control/identification devices associated with at least one sub-system component of the machine and operable to communicate through a plurality of electromagnetic signals. Shielding surrounds at least one of the sensing/control/identification devices to contain the electromagnetic signals proximate to the at least one sub-system component. A communication path is integrally formed in a component of the machine to route a portion of the electromagnetic signals through the component and a remote processing unit operable to communicate with the network of the sensing/control/identification devices through the electromagnetic signals, wherein at least a portion of the sensing/control/identification devices comprise a wide band gap semiconductor device and wherein at least a portion of the sensing/control/identification devices comprise an on-chip antenna.

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