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公开(公告)号：US11668243B2
公开(公告)日：2023-06-06
申请号：US17329501
申请日：2021-05-25
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Carroll V. Sidwell
IPC: F02C7/224 , F02C3/22 , F02C7/232 , F02C7/26 , F02C9/40 , B64D37/14 , B64D37/30 , F02C7/262 , F02C7/32 , B64D37/04 , B64D37/10 , B64D37/16 , B64D37/34 , B64D37/06 , B64F1/28
CPC classification number: F02C7/224 , F02C3/22 , F02C7/232 , F02C7/26 , F02C7/262 , F02C7/32 , F02C9/40 , B64D37/04 , B64D37/06 , B64D37/10 , B64D37/14 , B64D37/16 , B64D37/30 , B64D37/34 , B64F1/28 , F05D2220/323 , F05D2240/36
Abstract: Aircraft hydrogen fuel systems and methods and systems of starting such systems are described. The aircraft hydrogen fuel systems include a hydrogen burning main engine, a main tank configured to contain liquid hydrogen to be supplied to the main engine during a normal operation, and a starter tank configured to contain gaseous hydrogen to be used during a startup operation of the main engine. Methods and processes for starting and/or restarting such systems are described.
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公开(公告)号：US20230122524A1
公开(公告)日：2023-04-20
申请号：US17967402
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Russell B. Witlicki
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine shaft, a gearbox and a coupler. The turbine engine shaft is configured to rotate about a rotational axis. The gearbox includes a gear configured to rotate about the rotational axis. The coupler is coupled to the turbine engine shaft by a coupler-shaft connection. The coupler-shaft connection is configured as or otherwise includes a crowned spline connection. The coupler is coupled to the gear by a coupler-gear connection. The coupler-gear connection is configured as or otherwise includes a crowned spline connection.
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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：US20220396365A1
公开(公告)日：2022-12-15
申请号：US17345626
申请日：2021-06-11
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Christopher D. Ramsey , Coy Bruce Wood , Lance L. Smith
Abstract: Examples described herein provide a computer-implemented method that includes monitoring a hybrid electric turbine engine of an aircraft, the hybrid electric turbine engine including a first electric machine associated with a high speed spool and a second electric machine associated with a low speed spool. The method further includes receiving an indication of a failed electric machine, the failed electric machine being an electric machine on another hybrid electric turbine engine of the aircraft. The method further includes, responsive to detecting the failed electric machine, distributing power from one or more of the first electric machine or the second electric machine to a spool associated with the failed electric machine.
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公开(公告)号：US11415065B2
公开(公告)日：2022-08-16
申请号：US16912110
申请日：2020-06-25
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Marc J. Muldoon
IPC: F02C7/36 , F02C6/00 , F02C7/32 , F02K5/00 , F02C3/04 , F02C7/20 , F01D15/10 , B64D27/02 , F02C6/14
Abstract: Hybrid electric propulsion systems are described. The hybrid electric propulsion systems include a gas turbine engine including a low speed spool and a high speed spool, the low speed spool including a low pressure compressor and a low pressure turbine, and the high speed spool including a high pressure compressor and a high pressure turbine, a mechanical power transmission configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric motor configured to augment rotational power of at least one of the low speed spool and the high speed spool, and a controller operable to control a power augmentation of at least one of the low speed spool and the high speed spool during an operational stress state of operation of the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US20220128004A1
公开(公告)日：2022-04-28
申请号：US17081627
申请日：2020-10-27
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon , Jonathan M. Rheaume
Abstract: The cooling system may comprise: an electric machine; a first conduit including a cable housing and an inlet; a plurality of conductive cables extending from the electric machine, the plurality of conductive cables disposed at least partially in the cable housing; and an electric fan disposed in the first conduit, the cooling system configured to passively flow air through the first conduit to cool the plurality of conductive cables during operation of the gas turbine engine, and the electric fan configured to actively cool the plurality of conductive cables after an engine shutdown of the gas turbine engine.
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公开(公告)号：US11313278B2
公开(公告)日：2022-04-26
申请号：US16909490
申请日：2020-06-23
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.
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公开(公告)号：US20210079843A1
公开(公告)日：2021-03-18
申请号：US16909490
申请日：2020-06-23
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.
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公开(公告)号：US20240352892A1
公开(公告)日：2024-10-24
申请号：US18137898
申请日：2023-04-21
Applicant: Raytheon Technologies Corporation
Inventor： Murat Yazici , Marc J. Muldoon
CPC classification number: F02C7/18 , F02C9/18 , F05D2260/20
Abstract: A gas turbine engine is provided that includes fan, compressor, combustor, and turbine sections, an outer casing, an outside core annular region, and a fan air circulation system. The engine has a core gas path that is disposed radially inside of the outer casing. A fan bypass air duct is defined by inner and outer radial flow path boundaries. The outside core annular region is disposed radially between the outer casing and the inner radial boundary flow path boundary. The fan air circulation system has a plurality of inlet ports, valves, and exit ports. The fan air circulation system is configured such that a respective inlet port is in fluid communication with a respective valve, and the respective valve is in fluid communication with a respective exit port. Each valve is selectively controllable to control fan bypass air flow therethrough and into the outside core annular region.
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公开(公告)号：US20240110491A1
公开(公告)日：2024-04-04
申请号：US17956881
申请日：2022-09-30
Applicant: Raytheon Technologies Corporation
Inventor： Thomas E. Clark , Marc J. Muldoon
CPC classification number: F02C7/28 , F02C7/18 , F02C7/24 , F05D2260/231 , F05D2260/232 , F05D2260/30 , F05D2260/60 , F05D2300/175
Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is disposed radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features defining a purge airflow. A heat shield is positioned immediately downstream of the first seal and is configured in relation to the first seal such that the purge airflow enters a mixing plenum defined between the heat shield and the first seal.
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