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公开(公告)号：US20240010352A1
公开(公告)日：2024-01-11
申请号：US17860751
申请日：2022-07-08
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
CPC classification number: B64D37/30 , B64D41/00 , B64D37/34 , F02C3/22 , F02C7/32 , F05D2220/323 , F05D2260/40311 , F05D2220/76
Abstract: 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：US20220299205A1
公开(公告)日：2022-09-22
申请号：US17665063
申请日：2022-02-04
Applicant: Raytheon Technologies Corporation
Inventor： Malcolm MacDonald , Sean C. Emerson , Brian M. Holley , Lance L. Smith , Peter Cocks
Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).
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公开(公告)号：US20230304439A1
公开(公告)日：2023-09-28
申请号：US17860756
申请日：2022-07-08
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
Abstract: 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：US11629858B2
公开(公告)日：2023-04-18
申请号：US17665063
申请日：2022-02-04
Applicant: Raytheon Technologies Corporation
Inventor： Malcolm MacDonald , Sean C. Emerson , Brian M. Holley , Lance L. Smith , Peter Cocks
Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).
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公开(公告)号：US20240010351A1
公开(公告)日：2024-01-11
申请号：US17860746
申请日：2022-07-08
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
CPC classification number: B64D37/30 , B64D41/00 , B64D15/12 , F02C3/22 , F02C7/32 , F05D2220/76 , F05D2220/323
Abstract: 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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Patent Agency Ranking
公开(公告)号：US11225905B1
公开(公告)日：2022-01-18
申请号：US17018471
申请日：2020-09-11
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Christopher Britton Greene
Abstract: Supercritical fluid systems and aircraft power systems are described. The systems include a compressor, a turbine operably coupled to the compressor, a generator operably coupled to the turbine and configured to generate power, a primary working fluid flow path having a primary working fluid configured to pass through the compressor, a separator, the turbine, and back to the compressor, and a secondary working fluid flow path passing through the generator, the compressor, the separator, and back to the generator. The primary working fluid is supercritical carbon dioxide (sCO2) and the secondary working fluid is a fluid having at least one of a density less than the primary working fluid and a molecular size smaller than the primary working fluid.
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公开(公告)号：US20230349321A1
公开(公告)日：2023-11-02
申请号：US17730849
申请日：2022-04-27
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Stephen H. Taylor , Malcolm P. MacDonald , Dmytro M. Voytovych , Brian M. Holley
CPC classification number: F02C3/10 , F02C6/18 , F01D15/10 , F05D2260/213 , F05D2210/12 , F05D2220/323 , F05D2260/10
Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path that is in communication with a compressor section, combustor section and a turbine section, the core engine is configured to generate a high energy gas flow, a first cycle turbine that is configured to drive a first cycle compressor at a cycle speed in response to expansion of a heated working fluid flow between a first inlet and a first outlet of the first cycle turbine, and a first power turbine that is configured to drive a first output shaft at a power speed that is different than the cycle speed in response to expansion of a working fluid flow received from the first outlet of the first cycle turbine.
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公开(公告)号：US11802508B2
公开(公告)日：2023-10-31
申请号：US17708095
申请日：2022-03-30
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Lance L. Smith , David Lei Ma , Joseph B. Staubach , Brian M. Holley , Sean C. Emerson
Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.
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公开(公告)号：US20230313735A1
公开(公告)日：2023-10-05
申请号：US17708095
申请日：2022-03-30
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Lance L. Smith , David Lei Ma , Joseph B. Staubach , Brian M. Holley , Sean C. Emerson
Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.
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公开(公告)号：US11624317B2
公开(公告)日：2023-04-11
申请号：US17559281
申请日：2021-12-22
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Christopher Britton Greene
Abstract: Supercritical fluid systems and aircraft power systems are described. The systems include a compressor, a turbine, and a generator. A primary working fluid flow path has a primary working fluid that passes through the compressor, a separator, the turbine, and back to the compressor. A secondary working fluid flow path having a secondary working fluid that passes through the generator, the compressor, the separator, and back to the generator. The primary working fluid and the secondary working fluid are compressed and mixed within the compressor to form a mixture of the two fluids and the separator separates the mixture of the two fluids to direct the primary working fluid back to the turbine and the secondary working fluid to the generator.
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