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公开(公告)号：US11970974B2
公开(公告)日：2024-04-30
申请号：US17570764
申请日：2022-01-07
Applicant: Raytheon Technologies Corporation
Inventor： Robert E. Malecki , Andrew Hahn , Marc J. Muldoon , Jesse M. Chandler , Joseph B. Staubach
CPC classification number: F02C7/20 , B64C7/02 , B64D27/12 , B64D29/06 , B64D29/08 , F02C7/06 , F02C7/14 , F02C7/32 , F05D2220/323 , F05D2230/72 , F05D2260/213 , F05D2260/4031 , F05D2260/98
Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.
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公开(公告)号：US11892250B2
公开(公告)日：2024-02-06
申请号：US17320817
申请日：2021-05-14
Applicant: Raytheon Technologies Corporation
Inventor： Joseph B. Staubach , Marc J. Muldoon , James F. Wiedenhoefer
CPC classification number: F28F9/0131 , F28D1/0475 , F28F21/02 , F02C7/10 , F28D2001/0273
Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each comprising; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; a turn joining the first leg to the second leg; and a first face and a second face. A support has at least one carbon member engaging the plurality of tube sections.
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公开(公告)号：US20240026816A1
公开(公告)日：2024-01-25
申请号：US17871581
申请日：2022-07-22
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Walter A. Ledwith, JR. , Joseph B. Staubach , David Lei Ma
Abstract: An energy supply system includes a source of gas which is at a pressure that is equal to or greater than an atmospheric pressure. The source of gas is configured to deliver the gas into a combustor where it is mixed with a fuel. The combustor is also connected to receive a source of steam. The combustor is operable to provide combustion. Products of the combustion downstream of the combustor are connected to be delivered across a turbine rotor. The turbine rotor is provided with a shaft. The turbine shaft drives a generator. An evaporator downstream of the turbine receives the products of the combustion. The evaporator is operable to heat a source of water. The source of water downstream of the evaporator is the source of steam delivered into the combustor. The gas includes greater than 80% oxygen and the fuel includes hydrogen.
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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：US20230323836A1
公开(公告)日：2023-10-12
申请号：US17716523
申请日：2022-04-08
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Adams , Frederick M. Schwarz , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Gabriel L. Suciu
Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
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Patent Agency Ranking
公开(公告)号：US20230258125A1
公开(公告)日：2023-08-17
申请号：US17670045
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach
CPC classification number: F02C6/006 , F02C7/08 , F02C7/36 , F05D2260/10 , F05D2260/213 , F05D2260/232
Abstract: 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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公开(公告)号：US20230258106A1
公开(公告)日：2023-08-17
申请号：US17670043
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Walter A. Ledwith, JR. , Joseph B. Staubach , David L. Ma
CPC classification number: F01K25/005 , F01K27/02 , F01K7/12 , F01K7/16 , F01K15/02
Abstract: A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.
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公开(公告)号：US11603798B1
公开(公告)日：2023-03-14
申请号：US17669680
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach , Joseph E. Turney
Abstract: Aircraft engines include a burner section and a turbine section arranged along a shaft, wherein an exhaust from the burner section is directed through the turbine section to drive rotation of the turbine section and a core flow path passes through the burner section and then the turbine section. A condenser assembly is arranged downstream of the turbine section along the core flow path. A cryogenic fuel source is configured to supply fuel to the burner section along a fuel line passing through the condenser assembly and the fuel within the fuel line is configured to pick up heat from the exhaust from the burner section and condense water therefrom.
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公开(公告)号：US20220349656A1
公开(公告)日：2022-11-03
申请号：US17854655
申请日：2022-06-30
Applicant: Raytheon Technologies Corporation
Inventor： Joseph B. Staubach , Amanda Jean Learned Boucher , Jesse M. Chandler
Abstract: A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet.
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公开(公告)号：US20220136441A1
公开(公告)日：2022-05-05
申请号：US17570764
申请日：2022-01-07
Applicant: Raytheon Technologies Corporation
Inventor： Robert E. Malecki , Andrew Hahn , Marc J. Muldoon , Jesse M. Chandler , Joseph B. Staubach
Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.
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