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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：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：US11987377B2
公开(公告)日：2024-05-21
申请号：US17860746
申请日：2022-07-08
申请人： RTX Corporation
CPC分类号： B64D37/30 , B64D15/12 , B64D41/00 , F02C3/22 , F02C7/32 , F05D2220/323 , F05D2220/76
摘要： 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 a turbo expander. The main engine core includes 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 turbo expander, prior to being injected into the burner for combustion. The turbo expander includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.
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公开(公告)号：US12055098B2
公开(公告)日：2024-08-06
申请号：US17860215
申请日：2022-07-08
申请人： RTX Corporation
摘要： A turbine engine system includes at least one hydrogen fuel tank, a core flow path heat exchanger in a core flow path; and engine systems located in the core flow path. The engine system including at least a compressor section, a combustor section having a burner, and a turbine section. The core flow path heat exchanger is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank through a hydrogen fuel supply line, passing through the core flow path heat exchanger and then supplied into the burner for combustion.
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