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公开(公告)号：US20210340908A1
公开(公告)日：2021-11-04
申请号：US16864844
申请日：2020-05-01
Applicant: Raytheon Technologies Corporation
Inventor： Amanda J. L. Boucher , Joseph B. Staubach
Abstract: Turbine engine systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a cryogenic fuel tank configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line and a second flow supply line, the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and a flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.
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公开(公告)号：US12195191B2
公开(公告)日：2025-01-14
申请号：US17535200
申请日：2021-11-24
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Paul R. Hanrahan , Joseph B. Staubach , Jill Klinowski
Abstract: A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.
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公开(公告)号：US20240271549A1
公开(公告)日：2024-08-15
申请号：US18108336
申请日：2023-02-10
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach
CPC classification number: F01K11/02 , F01K7/223 , F01K15/02 , F05D2220/72
Abstract: 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：US11939925B2
公开(公告)日：2024-03-26
申请号：US17840715
申请日：2022-06-15
Applicant: Raytheon Technologies Corporation
Inventor： Charles E. Lents , Joseph B. Staubach , Larry W. Hardin , Jonathan Rheaume
CPC classification number: F02C7/36 , B64D27/10 , B64D27/24 , B64D31/06 , F01D15/10 , F02C6/14 , F02C9/50 , B64D2027/026 , F05D2220/76 , Y10S903/905 , Y10S903/906
Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.
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公开(公告)号：US20230374911A1
公开(公告)日：2023-11-23
申请号：US18314958
申请日：2023-05-10
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Neil J. Terwilliger , Joseph B. Staubach
Abstract: A turbine engine assembly includes a core engine generating a high energy gas flow that is expanded through a turbine section, a hydrogen fuel system supplying hydrogen fuel to a combustor through a fuel flow path, a condenser extracting water from the high energy gas flow, an evaporator inputting thermal energy into the water extracted by the condenser to generate a steam flow, and at least one superheater receiving the steam flow from the evaporator and input thermal energy for heating the steam flow. The steam flow from the at least one superheater is injected into the core flow path upstream of the turbine section.
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Patent Agency Ranking
公开(公告)号：US20230323814A1
公开(公告)日：2023-10-12
申请号：US18192965
申请日：2023-03-30
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach , Joseph E. Turney
CPC classification number: F02C7/12 , B01D53/265 , F05D2270/303 , B01D2257/80
Abstract: Aircraft engines and methods of operation 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. A core condenser is arranged downstream of the turbine section of the core assembly along the core flow path, the core condenser being configured to condense water from the core flow path. A refrigeration system is operably coupled to the core condenser and configured to direct a cold stream flow path into thermal interaction with the core flow path at the core condenser and configured to control a delta temperature at which heat exchange occurs between the core flow path and the cold stream flow path.
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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：US20230279806A1
公开(公告)日：2023-09-07
申请号：US18138481
申请日：2023-04-24
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph B. Staubach , David L. Ma
CPC classification number: F02C3/30 , F02C7/12 , F05D2220/323 , F05D2260/605 , F05D2260/213 , F05D2260/207 , F05D2260/212 , F05D2240/35
Abstract: 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：US20230257131A1
公开(公告)日：2023-08-17
申请号：US17669955
申请日：2022-02-11
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Charles E. Lents , Zubair A. Baig , Haralambos Cordatos , Joseph B. Staubach , Malcolm P. MacDonald
CPC classification number: B64D33/08 , B64D27/24 , H05K7/20372 , B64D2221/00
Abstract: A powertrain system of an aircraft includes one or more electrical components to provide electrical power to one or more electrical loads of the aircraft. The system further includes a rechargeable cryogenic heat sink containing a volume of cryogenic cooling material. The cryogenic heat sink is configured to cool the one or more electrical components. A method of operating a powertrain system of an aircraft includes generating thermal energy at one or more electrical components of the powertrain system, fluidly connecting a cryogenic heat sink to the one or more electrical components, and cooling the one or more electrical components via a volume of cryogenic cooling material of the cryogenic heat sink.
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公开(公告)号：US20220364802A1
公开(公告)日：2022-11-17
申请号：US17320817
申请日：2021-05-14
Applicant: Raytheon Technologies Corporation
Inventor： Joseph B. Staubach , Marc J. Muldoon , James F. Wiedenhoefer
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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