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公开(公告)号：US12049850B1
公开(公告)日：2024-07-30
申请号：US18370511
申请日：2023-09-20
Applicant: RTX CORPORATION
Inventor： Francis Parnin , David Allen Stachowiak , Marc J. Muldoon
CPC classification number: F02C7/36 , F01D25/18 , F02C7/06 , F05D2220/36 , F05D2260/40311 , F05D2260/98
Abstract: A fan drive gear system for a turbine engine includes a sun gear that is configured to be driven by an engine shaft that is rotatable about an axis, a plurality of intermediate gears that are intermeshed with the sun gear, a ring gear assembly that is engaged with the plurality of intermediate gears, the ring gear configured for attachment to a static structure, a carrier that supports rotation of the plurality of intermediate gears, the carrier configured for rotation about the axis, a fixed gutter system that is configured to receive expelled lubricant and to direct the expelled lubricant to an auxiliary reservoir, at least one ejector that is disposed within the fixed gutter and configured to utilize a motive flow to generate a lubricant flow through at least one outlet, and a fan shaft that is rotatable about the axis and configured to be driven by the carrier.
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公开(公告)号：US12018578B1
公开(公告)日：2024-06-25
申请号：US18299423
申请日：2023-04-12
Applicant: RTX Corporation
Inventor： Bradley C. Schafer , Brian V. Winebrenner , Jason B. Solomonides , Marc J. Muldoon , John P. Virtue, Jr.
CPC classification number: F01D25/36 , F01D21/04 , F05D2270/114
Abstract: A bowed rotor prevention system includes a gas turbine engine, and electric motor, and a core turning controller. The gas turbine engine includes a rotor that is rotatably coupled to a drive shaft. The electric motor is rotatably coupled to a motor shaft, which is mechanically coupled to the drive shaft so as to rotate therewith. The core turning controller in signal communication with the electric motor. The core turning controller determines whether a rotor bow is present in the rotor based on an operating time of the gas turbine engine, determines a motoring time based on the operating time, and invokes an anti-rotor bowing mode configured to control the electric motor to rotate the rotor according to the motor time.
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公开(公告)号：US11987377B2
公开(公告)日：2024-05-21
申请号：US17860746
申请日：2022-07-08
Applicant: RTX Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
CPC classification number: B64D37/30 , B64D15/12 , B64D41/00 , F02C3/22 , F02C7/32 , F05D2220/323 , F05D2220/76
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：US20250092832A1
公开(公告)日：2025-03-20
申请号：US18370497
申请日：2023-09-20
Applicant: RTX CORPORATION
Inventor： Marc J. Muldoon , Michael E. McCune
Abstract: A fan drive gear system for a turbine engine includes an auxiliary reservoir that is disposed radially outward of a rotating carrier and an oil director that is attached to the carrier. The oil director imparts a rotational flow direction into expelled oil to drive the expelled oil tangentially against an oil receiving surface and into the auxiliary reservoir.
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Patent Agency Ranking
公开(公告)号：US12055098B2
公开(公告)日：2024-08-06
申请号：US17860215
申请日：2022-07-08
Applicant: RTX Corporation
Inventor： James Wiedenhoefer , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents , Brian M. Holley
Abstract: A turbine engine system includes at least one hydrogen fuel tank, a core flow path heat exchanger in a core flow path; and engine systems located in the core flow path. The engine system including at least a compressor section, a combustor section having a burner, and a turbine section. The core flow path heat exchanger is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank through a hydrogen fuel supply line, passing through the core flow path heat exchanger and then supplied into the burner for combustion.
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公开(公告)号：US11933190B2
公开(公告)日：2024-03-19
申请号：US18300558
申请日：2023-04-14
Applicant: RTX 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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公开(公告)号：US20230417178A1
公开(公告)日：2023-12-28
申请号：US18458732
申请日：2023-08-30
Applicant: RTX Corporation
Inventor： Marc J. Muldoon
CPC classification number: F02C6/08 , B64D13/06 , B64D27/16 , B64D27/24 , F02C7/32 , B64D2013/0618 , B64D2027/026
Abstract: A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, first and second ducting systems fluidly communicative with each other and with the first and second hybrid-electric engines, respectively, and a control system. The control system is operably coupled to each of the first and second hybrid-electric engines and to each of the first and second ducting systems. The control system is configured to run the first hybrid-electric engine normally, to run the second hybrid-electric engine in a lower power mode and to control each of the first and second ducting systems to direct bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
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公开(公告)号：US11821372B2
公开(公告)日：2023-11-21
申请号：US17837829
申请日：2022-06-10
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , Arnab Roy , John R. Farris
CPC classification number: F02C7/32 , B64D27/16 , B64D27/24 , F01D11/22 , F02C6/14 , B64D2027/026 , F05D2220/323 , F05D2220/76
Abstract: A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; at least one blade outer air seal positioned between an outer case of the high pressure turbine and a plurality of blades of the high pressure turbine; a clearance control system operably coupled to the at least one blade outer air seal, the clearance control system configured to vary a position of the at least one blade outer air seal with respect to the plurality of blades of the high pressure turbine; and a controller operably coupled to the electric motor and the clearance control system, wherein the controller is configured to operate the clearance control system based upon an operational state of the electric motor.
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公开(公告)号：US11781477B2
公开(公告)日：2023-10-10
申请号：US17976326
申请日：2022-10-28
Applicant: RTX Corporation
Inventor： Marc J. Muldoon
CPC classification number: F02C6/08 , B64D13/06 , B64D27/16 , B64D27/24 , F02C7/32 , B64D2013/0618 , B64D2027/026 , F05D2220/323 , F05D2220/76
Abstract: A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, first and second ducting systems fluidly communicative with each other and with the first and second hybrid-electric engines, respectively, and a control system. The control system is operably coupled to each of the first and second hybrid-electric engines and to each of the first and second ducting systems. The control system is configured to run the first hybrid-electric engine normally, to run the second hybrid-electric engine in a lower power mode and to control each of the first and second ducting systems to direct bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
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