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1.发明授权公开(公告)号：US12215620B2
公开(公告)日：2025-02-04
申请号：US18119154
申请日：2023-03-08
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Jacob C. Snyder , Neil J. Terwilliger
IPC: F02C6/18
Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The recovery system includes an evaporator module and a condenser module. The condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.
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公开(公告)号：US20240301819A1
公开(公告)日：2024-09-12
申请号：US18119182
申请日：2023-03-08
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger
CPC classification number: F02C3/30 , F01D25/32 , F05D2220/323 , F05D2220/62 , F05D2220/72 , F05D2260/213
Abstract: A powerplant includes a turbine engine core configured to power a mechanical load. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. A recovery system includes a condenser and an evaporator. A core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser from an inlet into the core flowpath to an exhaust from the core flowpath. The recovery system is configured to condense water vapor flowing through the core flowpath into water using the condenser. The recovery system is configured to evaporate the water into steam using the evaporator and to provide the steam to the turbine engine core during a first mode of operation. The recovery system is configured to flow the water through the evaporator during a second mode of operation.
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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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4.发明公开公开(公告)号：US20240271548A1
公开(公告)日：2024-08-15
申请号：US18108372
申请日：2023-02-10
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Joseph E. Turney
CPC classification number: F01D25/32 , F01D13/02 , F05D2220/323 , F05D2220/72 , F05D2220/74
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 to generate a first steam flow, a first steam turbine where the first steam flow is expanded and cooled to generate a first cooled flow, a bypass passage that defines a path for the first steam flow around the first steam turbine, and a superheater where at least one of the first steam flow and the first cooled flow is reheated to generate a second steam flow.
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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：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：US12173624B2
公开(公告)日：2024-12-24
申请号：US18199742
申请日：2023-05-19
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Neil J. Terwilliger
Abstract: A turbine engine is provided that includes a bypass flowpath, a plurality of upstream vanes and a plurality of downstream vanes. The bypass flowpath is fluidly coupled with and downstream of a fan section. The bypass flowpath bypasses a turbine engine core. The upstream vanes are arranged circumferentially about an axis in an upstream vane array. Each of the upstream vanes extends radially across the bypass flowpath. The downstream vanes are arranged circumferentially about the axis in a downstream vane array. The downstream vanes are circumferentially interspersed with the upstream vanes. Each of the downstream vanes extends radially across the bypass flowpath. A first of the downstream vanes is axially offset from a first of the upstream vanes along the axis.
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公开(公告)号：US20240343408A1
公开(公告)日：2024-10-17
申请号：US18300594
申请日：2023-04-14
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger
Abstract: A cryogenic fuel system for an aircraft, the cryogenic fuel system includes a fuel tank assembly that is configured to store a cryogenic fuel in a liquid phase during aircraft operation, and a cooling system that is associated with the fuel tank assembly. The cooling system is configured to maintain the fuel tank assembly within a predefined temperature range during non-flight operation.
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