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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：US20210316877A1
公开(公告)日：2021-10-14
申请号：US17227602
申请日：2021-04-12
Applicant: Raytheon Technologies Corporation
Inventor： Jonathan Rheaume , Robert Mason Darling
IPC: B64D37/30 , B64D27/24 , B64D27/10 , H01M8/0258 , H01M8/0267
Abstract: A propulsion system according to an exemplary embodiment of this disclosure, among other possible things includes a fuel storage tank that is configured to store a fuel in a compressed state, a power generation device that is configured to consume the fuel and generate an output, a fuel system that is configured to provide the fuel from the fuel storage tank to the power generation device, and an electrochemical compressor that is in communication with the fuel system. The electrochemical compressor is configured to gather residual fuel from the fuel system and communicate the gathered residual fuel to at least one of the power generation device and the fuel storage tank.
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Patent Agency Ranking
公开(公告)号：US11745891B2
公开(公告)日：2023-09-05
申请号：US17227602
申请日：2021-04-12
Applicant: Raytheon Technologies Corporation
Inventor： Jonathan Rheaume , Robert Mason Darling
IPC: B64D37/30 , B64D27/24 , B64D27/10 , H01M8/0258 , H01M8/0267 , B64D37/02 , B64D27/02 , B64D41/00
CPC classification number: B64D37/30 , B64D27/10 , B64D27/24 , H01M8/0258 , H01M8/0267 , B64D37/02 , B64D2027/026 , B64D2041/005 , H01M2250/20
Abstract: A propulsion system according to an exemplary embodiment of this disclosure, among other possible things includes a fuel storage tank that is configured to store a fuel in a compressed state, a power generation device that is configured to consume the fuel and generate an output, a fuel system that is configured to provide the fuel from the fuel storage tank to the power generation device, and an electrochemical compressor that is in communication with the fuel system. The electrochemical compressor is configured to gather residual fuel from the fuel system and communicate the gathered residual fuel to at least one of the power generation device and the fuel storage tank.
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公开(公告)号：US11585291B2
公开(公告)日：2023-02-21
申请号：US17018795
申请日：2020-09-11
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon , Jonathan Rheaume , Stephen H. Taylor
Abstract: An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.
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公开(公告)号：US20220349351A1
公开(公告)日：2022-11-03
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
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：US11371430B2
公开(公告)日：2022-06-28
申请号：US15200240
申请日：2016-07-01
Applicant: Raytheon Technologies Corporation
Inventor： Charles E. Lents , Jonathan Rheaume
Abstract: A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.
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公开(公告)号：US20220082052A1
公开(公告)日：2022-03-17
申请号：US17018795
申请日：2020-09-11
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon , Jonathan Rheaume , Stephen H. Taylor
IPC: F02C7/18
Abstract: An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.
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