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公开(公告)号：US20240363874A1
公开(公告)日：2024-10-31
申请号：US18638992
申请日：2024-04-18
IPC分类号： H01M8/04029 , B64D41/00 , F02C6/20 , H01M8/04014 , H01M8/04111
CPC分类号： H01M8/04029 , B64D41/00 , F02C6/20 , H01M8/04014 , H01M8/04111 , B64D2041/005 , H01M2250/20
摘要： A power generation system for an includes: a hydrogen fuel cell; an air supply system configured to supply air to the aircraft, the air supply system comprising an ORC-air heat exchanger; and an organic Rankine cycle (ORC) system comprising an organic fluid circuit. The organic fluid circuit is configured to receive excess fuel cell heat from the hydrogen fuel cell to heat organic fluid in the organic fluid circuit. The organic fluid circuit passes through the ORC-air heat exchanger such that the supply air heats the organic fluid in the organic fluid circuit. The ORC system is configured to extract power from the organic fluid.
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公开(公告)号：US20240309803A1
公开(公告)日：2024-09-19
申请号：US18185007
申请日：2023-03-16
发明人： David MENHEERE
CPC分类号： F02C3/085 , F02C6/20 , F02C3/045 , F02C3/08 , F02C3/09 , F02C3/10 , F02C3/103 , F02C3/107 , F02C3/13 , F02C7/36
摘要： An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.
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公开(公告)号：US20240301832A1
公开(公告)日：2024-09-12
申请号：US18181159
申请日：2023-03-09
发明人： Bahram Jadidian , Kevin Blinn , Mehrad Mehr
摘要： Components of gas turbine engines, aircraft comprising the components, and methods of producing the components are provided. The component includes a surface, and a set of tiles secured to the surface at interfaces between the set of tiles and the surface and between each of the set of tiles. The set of tiles conform to the surface and in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating.
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公开(公告)号：US11994067B2
公开(公告)日：2024-05-28
申请号：US17940055
申请日：2022-09-08
申请人： ROLLS-ROYCE plc
发明人： Natalie C Wong , Jonathan A Cherry , Paul R Davies , David A Jones , Andrew J Newman , Benjamin J Sellers , Stephen J Bradbrook
CPC分类号： F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
摘要： An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
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5.发明公开公开(公告)号：US20240141801A1
公开(公告)日：2024-05-02
申请号：US18546911
申请日：2022-01-05
申请人： PSA AUTOMOBILES SA
发明人： Wissam BOU NADER
IPC分类号： F01D15/10 , B60K3/04 , B60K6/24 , F01D15/02 , F02C3/36 , F02C6/18 , F02C6/20 , F02C7/08 , F02C7/143
CPC分类号： F01D15/10 , B60K3/04 , B60K6/24 , F01D15/02 , F02C3/36 , F02C6/18 , F02C6/20 , F02C7/08 , F02C7/143 , F05D2220/32 , F05D2220/40 , F05D2220/74 , F05D2220/76
摘要： The invention relates to a turbine engine device of the gas turbine cycle type with cooled compression, regeneration, and reheating during expansion. The turbine engine device comprises a first turbocharger (C1, T2), a second turbocharger (C2, T1), two combustion chambers (CC1, CC2), an intercooler (IC), and a heat exchanger (E1). The device is configured to implement a fluid flow from the first compressor (C1) to the intercooler (IC), to the second compressor (C2), to the heat exchanger (E1), to the first combustion chamber (CC1), to the second turbine (T1) or the first turbine, to the second combustion chamber (CC2), to the first turbine (T2) or the second turbine, According to one aspect, the turbochargers are mounted on separate axes (A1, A2).
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公开(公告)号：US11912423B2
公开(公告)日：2024-02-27
申请号：US17714736
申请日：2022-04-06
申请人： RTX Corporation
CPC分类号： B64D27/24 , B64D27/12 , F02C6/20 , F02C7/18 , F05D2220/323 , F05D2220/72 , F05D2260/20
摘要： Propulsion systems for aircraft include a fan and a low pressure turbine operably coupled to a first shaft, a low pressure compressor and an intermediate pressure turbine operably coupled to a second shaft, and a high pressure compressor and a high pressure turbine operably coupled to a third shaft. A burner is arranged between the high pressure compressor and the high pressure turbine, with a main flow path defined through the propulsion system. A hydrogen fuel system is configured to supply hydrogen fuel to the burner. A condenser is arranged along the main flow path and configured to extract water from exhaust from the burner. An evaporator is arranged along the main flow path and configured to receive a portion of the water to generate steam which is injected into the main flow path upstream from the evaporator.
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公开(公告)号：US11891967B2
公开(公告)日：2024-02-06
申请号：US17277801
申请日：2019-09-20
发明人： Henri Yesilcimen , Caroline Marie Frantz , Nicolas Jérôme Jean Tantot , Nathalie Nowakowski , Gilles Alain Marie Charier , Kévin Morgane Lemarchand , Jonathan Evert Vlastuin
CPC分类号： F02K5/00 , F01D15/10 , F02C6/20 , F02K3/00 , F02K3/06 , B64D2027/026 , F05D2220/323 , F05D2220/70 , F05D2220/76 , F05D2260/40311
摘要： A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.
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公开(公告)号：US20230415883A1
公开(公告)日：2023-12-28
申请号：US18466922
申请日：2023-09-14
CPC分类号： B64C11/305 , F01D5/12 , F02C6/20 , F02C9/00 , F05D2220/323
摘要： A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
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公开(公告)号：US20230358169A1
公开(公告)日：2023-11-09
申请号：US18354192
申请日：2023-07-18
CPC分类号： F02C6/20 , F02C6/206 , F02C9/00 , B64D31/06 , B64D27/24 , F05D2270/303 , F05D2220/323 , F05D2270/101 , F05D2270/62 , F05D2270/301
摘要： A method for operating a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system, the method comprising: sensing data indicative of at least one of an aerodynamic instability, a pressure, or a temperature within the HP compressor and the LP compressor of the gas turbine engine; identifying a aerodynamically unstable compressor by determining that conditions within one of the HP compressor or the LP compressor are within a threshold of a stall condition based at least in part on the sensed data within the HP compressor and the LP compressor of the gas turbine engine, the one of the HP compressor or the LP compressor that is determined to be within the threshold of a stall condition being the aerodynamically unstable compressor; and transferring power, via the one or more electric machines, to the aerodynamically unstable compressor in order to clear the stall condition.
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公开(公告)号：US20230322396A1
公开(公告)日：2023-10-12
申请号：US17714736
申请日：2022-04-06
申请人： RTX Corporation
CPC分类号： B64D27/24 , F02C6/20 , B64D27/12 , F02C7/18 , F05D2220/323 , F05D2220/72 , F05D2260/20
摘要： Propulsion systems for aircraft include a fan and a low pressure turbine operably coupled to a first shaft, a low pressure compressor and an intermediate pressure turbine operably coupled to a second shaft, and a high pressure compressor and a high pressure turbine operably coupled to a third shaft. A burner is arranged between the high pressure compressor and the high pressure turbine, with a main flow path defined through the propulsion system. A hydrogen fuel system is configured to supply hydrogen fuel to the burner. A condenser is arranged along the main flow path and configured to extract water from exhaust from the burner. An evaporator is arranged along the main flow path and configured to receive a portion of the water to generate steam which is injected into the main flow path upstream from the evaporator.
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