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公开(公告)号：US12103699B2
公开(公告)日：2024-10-01
申请号：US17860751
申请日：2022-07-08
申请人： RTX Corporation
CPC分类号： B64D37/30 , B64D37/34 , B64D41/00 , F02C3/22 , F02C7/224 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/40311
摘要： Aircraft propulsion systems have aircraft systems including at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems includes at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section arranged along an engine shaft. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander is configured to impart power to the engine shaft.
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公开(公告)号：US12085025B2
公开(公告)日：2024-09-10
申请号：US18387527
申请日：2023-11-07
申请人： RTX CORPORATION
CPC分类号： F02C7/36 , F02C3/04 , F02C3/06 , F02C3/107 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2220/323 , F05D2260/4031 , F05D2260/40311
摘要： A gas turbine engine includes, among other things, a propulsor section including a propulsor, a core engine, a gear arrangement that drives the propulsor. A compressor section includes a first compressor section and a second compressor section. A turbine section includes a first turbine and a second turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than 40. The pressure ratio across the second compressor section is between 7 and 15, and the pressure ratio across the first compressor section is between 4 and 8.
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公开(公告)号：US20240287931A1
公开(公告)日：2024-08-29
申请号：US18655808
申请日：2024-05-06
申请人： RTX Corporation
IPC分类号： F02C6/00 , B64D27/02 , B64D27/10 , B64D27/24 , B64D33/08 , F02C7/12 , F02C9/26 , H01M8/04007
CPC分类号： F02C6/00 , B64D27/10 , B64D27/24 , B64D33/08 , F02C7/12 , F02C9/26 , H01M8/04059 , B64D27/026 , H01M2250/20
摘要： Turbine engine systems include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section and exits through a nozzle. A core condenser is arranged downstream of the turbine section and upstream of the nozzle and configured to condense water from the core flow path. A fuel cell is operably connected to the core assembly. A fuel source is configured to supply a fuel to each of the burner section for combustion and the fuel cell for reaction to generate electricity. At least one electric motor is operably coupled to the core assembly and configured to impart power to a portion of the core assembly and the fuel cell is configured to supply electrical power to the at least one electric motor.
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公开(公告)号：US20240271550A1
公开(公告)日：2024-08-15
申请号：US18625755
申请日：2024-04-03
申请人： RTX CORPORATION
CPC分类号： F01K11/02 , F01K7/223 , F01K15/02 , F05D2220/72
摘要： A turbine engine assembly includes a core engine that generates an exhaust gas flow, a condenser where water is extracted from the exhaust gas flow, an evaporator where heat is input into the water that is extracted by the condenser into a first steam flow, a steam turbine where the first steam flow is expanded and cooled, and a superheater where additional heat is input into the first steam flow that is exhausted from the steam turbine to generate a second steam flow. The second steam flow is injected into a core flow path of the core engine.
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公开(公告)号：US20240254914A1
公开(公告)日：2024-08-01
申请号：US18486362
申请日：2023-10-13
申请人： RTX CORPORATION
CPC分类号： F02C3/30 , F02C3/22 , F02C7/14 , F05D2220/323 , F05D2260/213 , F05D2270/08
摘要： A turbine engine assembly includes a condenser assembly arranged along the core flow path to extract water from the exhaust gas flow, and an evaporator assembly where thermal energy from the exhaust gas flow is communicated to the water extracted by the condenser assembly to generate a steam flow for injection into the core flow path. The evaporator assembly splits steam generation and cooling functions to increase efficiencies of each function.
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公开(公告)号：US12044176B2
公开(公告)日：2024-07-23
申请号：US17860756
申请日：2022-07-08
申请人： RTX Corporation
摘要： Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.
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公开(公告)号：US20240167427A1
公开(公告)日：2024-05-23
申请号：US18425131
申请日：2024-01-29
申请人： RTX CORPORATION
摘要： A propulsion system for an aircraft includes a core engine that includes a core flow path where a core flow is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen-based fuel, and ignited to generate a gas flow that is expanded through a turbine section. A fuel system is configured to supply a hydrogen based fuel to the combustor through a fuel flow path. A condenser is arranged along the core flow path and configured to extract water from the gas flow. An intercooling system receives a portion of water from the condenser for cooling a portion of the core flow at a first location within the compressor section. Heated water from the intercooling system is exhausted to a second location within the core flow path downstream of the first location.
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公开(公告)号：US12065963B2
公开(公告)日：2024-08-20
申请号：US18138481
申请日：2023-04-24
申请人： RTX Corporation
CPC分类号： F02C3/30 , F02C7/12 , F05D2220/323 , F05D2240/35 , F05D2260/207 , F05D2260/212 , F05D2260/213 , F05D2260/605
摘要： A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.
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公开(公告)号：US12006866B2
公开(公告)日：2024-06-11
申请号：US17860730
申请日：2022-07-08
申请人： RTX Corporation
IPC分类号： F02C6/00 , B64D27/10 , B64D27/24 , B64D33/08 , F02C7/12 , F02C9/26 , H01M8/04007 , B64D27/02
CPC分类号： F02C6/00 , B64D27/10 , B64D27/24 , B64D33/08 , F02C7/12 , F02C9/26 , H01M8/04059 , B64D27/026 , H01M2250/20
摘要： Turbine engine systems include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section and exits through a nozzle. A core condenser is arranged downstream of the turbine section and upstream of the nozzle and configured to condense water from the core flow path. A fuel cell is operably connected to the core assembly. A fuel source is configured to supply a fuel to each of the burner section for combustion and the fuel cell for reaction to generate electricity. At least one electric motor is operably coupled to the core assembly and configured to impart power to a portion of the core assembly and the fuel cell is configured to supply electrical power to the at least one electric motor.
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公开(公告)号：US11939913B2
公开(公告)日：2024-03-26
申请号：US17670045
申请日：2022-02-11
申请人： RTX Corporation
CPC分类号： F02C6/006 , F02C7/08 , F02C7/36 , F05D2260/10 , F05D2260/213 , F05D2260/232
摘要： An engine system includes a turbine engine including a compressor section, a combustor section having a burner, a turbine section, and a nozzle in an open-loop configuration. The engine system also includes a bottom-cycle apparatus and an exhaust heat exchanger downstream of the turbine section of the turbine engine configured to reject heat from the turbine engine to the bottoming-cycle apparatus and create a cooled turbine exhaust in the turbine engine. The engine system further includes an exhaust compressor arranged downstream of the exhaust heat exchanger and upstream of the nozzle of the turbine engine configured to compress the cooled turbine exhaust stream and increase a pressure of the cooled turbine exhaust stream prior to exiting the nozzle of the turbine engine.
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