公开(公告)号：US20240352906A1

公开(公告)日：2024-10-24

申请号：US18137887

申请日：2023-04-21

Applicant: Raytheon Technologies Corporation

Inventor： Murat Yazici ,  Marc J. Muldoon

IPC: F02K3/04 ,  F02C7/25 ,  F04D27/00

CPC classification number: F02K3/04 ,  F02C6/06 ,  F02C7/18 ,  F02C7/25 ,  F04D27/009 ,  B64D2045/009

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 outer casing is disposed radially outside of the compressor, combustor, and turbine sections. The engine has a core gas path and a fan bypass air duct. The core gas path extends through the compressor, combustor, and turbine sections, and is disposed radially inside of the outer casing. The 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 is configured to receive fan bypass air from the fan bypass air duct and selectively pass the received fan bypass air into the outside core annular region.

公开(公告)号：US12065974B2

公开(公告)日：2024-08-20

申请号：US17967402

申请日：2022-10-17

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Russell B. Witlicki

IPC: F02C7/36 ,  F01D15/10 ,  F02C7/28 ,  F16D3/18

CPC classification number: F02C7/36 ,  F01D15/10 ,  F02C7/28 ,  F05D2260/36 ,  F05D2260/40311

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.

公开(公告)号：US20240254927A1

公开(公告)日：2024-08-01

申请号：US18102295

申请日：2023-01-27

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Marc J. Muldoon

IPC: F02C9/40 ,  F02C7/22

CPC classification number: F02C9/40 ,  F02C7/22 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/20

Abstract: A cryogenic fueled aircraft propulsion system includes a core engine that generates a high energy exhaust gas flow, a fuel system that is configured to supply a fuel to the core engine, a cryogenic fuel tank that is configured to maintain fuel in a liquid phase during aircraft operating conditions, a gas collection system where boil off gas from the cryogenic fuel tank is collected, and a fuel reliquification system where collected boil off gas from the cryogenic fuel tank is transformed into a liquid phase.

公开(公告)号：US20240253821A1

公开(公告)日：2024-08-01

申请号：US18102154

申请日：2023-01-27

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Marc J. Muldoon

IPC: B64F1/28 ,  B64D37/30 ,  B64F5/40

CPC classification number: B64F1/28 ,  B64D37/30 ,  B64F5/40

Abstract: A cryogenic fueled aircraft propulsion maintenance system includes a fuel system of an aircraft, the fuel system includes a cryogenic fuel tank that is configured to maintain the fuel in a liquid phase during aircraft operating conditions, a gas collection system where boil off gas from the fuel system is collected, and a fuel reliquification system that is configured to receive boil off gas from the gas collection system and transform the boil off gas into a liquid phase as liquid fuel.

公开(公告)号：US12044149B2

公开(公告)日：2024-07-23

申请号：US18333443

申请日：2023-06-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Marc J. Muldoon

IPC: F01D9/06 ,  F01D25/12 ,  F02C7/18 ,  F01D15/10 ,  F04D25/06

CPC classification number: F01D9/065 ,  F01D25/12 ,  F02C7/18 ,  F01D15/10 ,  F04D25/06

Abstract: A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.

公开(公告)号：US11970974B2

公开(公告)日：2024-04-30

申请号：US17570764

申请日：2022-01-07

Applicant: Raytheon Technologies Corporation

Inventor： Robert E. Malecki ,  Andrew Hahn ,  Marc J. Muldoon ,  Jesse M. Chandler ,  Joseph B. Staubach

IPC: F02C7/20 ,  B64C7/02 ,  B64D27/12 ,  B64D29/06 ,  B64D29/08 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32

CPC classification number: F02C7/20 ,  B64C7/02 ,  B64D27/12 ,  B64D29/06 ,  B64D29/08 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2260/213 ,  F05D2260/4031 ,  F05D2260/98

Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

公开(公告)号：US11952946B2

公开(公告)日：2024-04-09

申请号：US17965662

申请日：2022-10-13

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon

IPC: F02C7/224 ,  F02C7/12

CPC classification number: F02C7/224 ,  F02C7/12

Abstract: A turbine engine has: a compressor; a combustor; a turbine; a gaspath passing downstream from the compressor through the combustor and then through the turbine; a fuel source; a fuel flowpath from the fuel source to the combustor; and a heat exchanger for transferring heat from the gaspath to the fuel flowpath The heat exchanger has: an inner wall in heat transfer relation with the gaspath; an outer wall; tubes between the inner wall and the outer wall bounding respective segments of the fuel flowpath; and a heat transfer fluid between the inner wall and the outer wall and in heat transfer relation with the tubes and the inner wall.

公开(公告)号：US11892250B2

公开(公告)日：2024-02-06

申请号：US17320817

申请日：2021-05-14

Applicant: Raytheon Technologies Corporation

Inventor： Joseph B. Staubach ,  Marc J. Muldoon ,  James F. Wiedenhoefer

IPC: F28F9/013 ,  F28D1/047 ,  F28F21/02 ,  F02C7/10 ,  F28D1/02

CPC classification number: F28F9/0131 ,  F28D1/0475 ,  F28F21/02 ,  F02C7/10 ,  F28D2001/0273

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.

公开(公告)号：US20240010352A1

公开(公告)日：2024-01-11

申请号：US17860751

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： Brian M. Holley ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Charles E. Lents

IPC: B64D37/30 ,  B64D41/00 ,  B64D37/34 ,  F02C3/22 ,  F02C7/32

CPC classification number: B64D37/30 ,  B64D41/00 ,  B64D37/34 ,  F02C3/22 ,  F02C7/32 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2220/76

Abstract: Aircraft propulsion systems have aircraft systems including at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems includes at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section arranged along an engine shaft. 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 turbo expander, prior to being injected into the burner for combustion. The turbo expander is configured to impart power to the engine shaft.

公开(公告)号：US11867075B2

公开(公告)日：2024-01-09

申请号：US17967369

申请日：2022-10-17

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Russell B. Witlicki

IPC: F01D25/16 ,  F01D25/06

CPC classification number: F01D25/06 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2240/54

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure, a bearing and a gearbox. The rotating structure is configured to rotate about a rotational axis. The rotating structure includes a shaft and a bladed rotor connected to the shaft. The stationary structure circumscribes the rotating structure. The bearing rotatably mounts the shaft to the stationary structure. The gearbox is disposed radially inboard of the bearing.