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公开(公告)号：US20220018311A1
公开(公告)日：2022-01-20
申请号：US16931685
申请日：2020-07-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Andrew J. Murphy
Abstract: A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.
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公开(公告)号：US12000338B2
公开(公告)日：2024-06-04
申请号：US17967360
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Russell B. Witlicki
CPC classification number: F02C6/20 , F01D25/04 , F02C7/06 , F02C7/268 , F05D2220/323 , F05D2220/70 , F05D2220/76 , F05D2240/54 , F05D2260/85 , F05D2260/96
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a stationary structure, a rotating structure and an electric machine. The rotating structure is rotatably mounted to the stationary structure by a first bearing and a second bearing. The electric machine is between the first bearing and the second bearing. The electric machine includes a rotor and a stator circumscribing the rotor. The rotor is connected to the rotating structure. The stator is connected to the stationary structure.
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公开(公告)号：US11994038B2
公开(公告)日：2024-05-28
申请号：US17967460
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Russell B. Witlicki
CPC classification number: F01D25/183 , F01D25/16 , F02C6/20 , F05D2220/323 , F05D2220/70 , F05D2240/54 , F05D2240/55 , F05D2260/98
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a first rotating structure, a turbine engine apparatus, a rotating coupler and a seal assembly. The first rotating structure is configured to rotate about a rotational axis. The turbine engine apparatus includes an electric machine and a second rotating structure. The electric machine includes an electric machine rotor and an electric machine stator. The second rotating structure is configured to rotate about the rotational axis and is coupled to the electric machine rotor. The rotating coupler is coupled to the first rotating structure by a first connection. The rotating coupler is coupled to the second rotating structure by a second connection. The seal assembly includes a rotating seal land and a stationary seal element. The rotating seal land is mounted onto the rotating coupler. The stationary seal element sealingly engages the rotating seal land.
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公开(公告)号：US20240010351A1
公开(公告)日：2024-01-11
申请号：US17860746
申请日：2022-07-08
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
CPC classification number: B64D37/30 , B64D41/00 , B64D15/12 , F02C3/22 , F02C7/32 , F05D2220/76 , F05D2220/323
Abstract: Aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having 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. 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 includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.
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公开(公告)号：US20240003268A1
公开(公告)日：2024-01-04
申请号：US18300558
申请日：2023-04-14
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Keith B. Allyn
CPC classification number: F01D25/28 , F01D9/02 , F01D25/24 , F05D2240/14 , F05D2260/30 , F05D2260/606
Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.
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Patent Agency Ranking
公开(公告)号：US20230332542A1
公开(公告)日：2023-10-19
申请号：US17719458
申请日：2022-04-13
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon
IPC: F02C7/05
CPC classification number: F02C7/05
Abstract: An assembly of a gas turbine engine includes a low pressure compressor, a high pressure compressor, an intermediate case between the low pressure compressor and the high pressure compressor, and a cleaning apparatus having an annular arrangement about the intermediate case. A core flow path is defined through the low pressure compressor, the intermediate case, and the high pressure compressor. The annular arrangement includes a scroll portion configured to extract debris from an airstream at an outer diameter wall of the core flow path and return the airstream to the core flow path.
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公开(公告)号：US20230323781A1
公开(公告)日：2023-10-12
申请号：US18333443
申请日：2023-06-12
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon
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.
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公开(公告)号：US20230258131A1
公开(公告)日：2023-08-17
申请号：US17965662
申请日：2022-10-13
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon
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.
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公开(公告)号：US11725580B2
公开(公告)日：2023-08-15
申请号：US17351876
申请日：2021-06-18
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael D. Greenberg , Nancy Poisson , Martin Richard Amari
CPC classification number: F02C6/206 , B64D27/12 , B64D27/24 , F02C9/28 , F05D2220/323 , F05D2270/021
Abstract: An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.
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公开(公告)号：US11674415B2
公开(公告)日：2023-06-13
申请号：US17512824
申请日：2021-10-28
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Keith B. Allyn
CPC classification number: F01D25/28 , F01D9/02 , F01D25/24 , F05D2240/14 , F05D2260/30 , F05D2260/606
Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.
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