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公开(公告)号：US11970970B2
公开(公告)日：2024-04-30
申请号：US18109441
申请日：2023-02-14
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Malcolm P. MacDonald , Stephen H. Taylor
Abstract: A propulsion system for an aircraft includes a core flow path in communication with a compressor section, combustor section and a turbine section. A first bottoming cycle system includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the core engine. The first bottoming cycle is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.
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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：US12140050B2
公开(公告)日：2024-11-12
申请号：US18109448
申请日：2023-02-14
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Malcolm P. MacDonald , Stephen H. Taylor , Ram Ranjan
Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.
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Patent Agency Ranking
公开(公告)号：US20230313737A1
公开(公告)日：2023-10-05
申请号：US18109441
申请日：2023-02-14
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Malcolm P. MacDonald , Stephen H. Taylor
Abstract: A propulsion system for an aircraft includes a core flow path in communication with a compressor section, combustor section and a turbine section. A first bottoming cycle system includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the core engine. The first bottoming cycle is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.
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公开(公告)号：US20240390983A1
公开(公告)日：2024-11-28
申请号：US18201787
申请日：2023-05-25
Applicant: Raytheon Technologies Corporation
Inventor： Masoud Anahid , Matthew E. Lynch , Malcolm P. MacDonald , Ranadip Acharya , Brian A. Fisher
Abstract: A process for uncertainty quantification for a predictive defect model for multi-laser additive manufacturing of a part including executing computational fluid dynamics modeling of a gas flow in an additive manufacturing machine manufacturing chamber; assigning a spatter particle size, velocity and direction relative to a melt pool on a powder bed disposed on a build plate within the manufacturing chamber; executing computational fluid dynamics post processing for spatter particle tracking; predicting a spatter particle landing pattern; feeding the spatter particle landing pattern prediction into a defect model; producing a layer thickness map, the layer thickness map configured to demonstrate a location of locally thicker layers on the part; and predicting defect location and density to accumulate lack-of-fusion risk as a function of part placement, orientation, and scan strategy.
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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：US20230313711A1
公开(公告)日：2023-10-05
申请号：US18109448
申请日：2023-02-14
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Malcolm P. MacDonald , Stephen H. Taylor , Ram Ranjan
CPC classification number: F01K23/10 , F01K25/103 , F05D2260/211 , F05D2220/76 , F05D2260/213
Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.
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公开(公告)号：US20240390987A1
公开(公告)日：2024-11-28
申请号：US18201790
申请日：2023-05-25
Applicant: Raytheon Technologies Corporation
Inventor： Masoud Anahid , Matthew E. Lynch , Amit Surana , Malcolm P. MacDonald , Brian A. Fisher
IPC: B22F12/90 , B22F10/28 , B22F10/31 , B22F10/322 , B22F10/366 , B22F10/85 , B22F12/41 , B22F12/45 , B22F12/70 , B33Y10/00 , B33Y30/00 , B33Y50/02
Abstract: A process for a laser plume interaction for a predictive defect model for multi-laser additive manufacturing of a part including executing computational fluid dynamics modeling of a gas flow in an additive manufacturing machine manufacturing chamber; approximating a laser plume relative to a melt pool on a powder bed disposed on a build plate within the manufacturing chamber; executing a space-time analysis to identify a laser plume interaction; creating a plume interaction zone map; feeding the plume interaction zone map prediction into a multi-laser defect model; and predicting defect location and density to accumulate lack-of-fusion risk as a function of part placement, orientation, and scan strategy.
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