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公开(公告)号：US12098681B2
公开(公告)日：2024-09-24
申请号：US18202550
申请日：2023-05-26
Applicant: RTX Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2220/36 , F05D2260/40311
Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.
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公开(公告)号：US20250075659A1
公开(公告)日：2025-03-06
申请号：US18458640
申请日：2023-08-30
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , Francis Parnin
Abstract: A disclosed turbine engine having a fan drive gear system includes a first lubrication circuit having a first pump communicating oil to at least the fan drive gear system and at least one low shaft bearing assembly. The first pump is driven by the low spool through a first tower shaft. A second lubrication circuit includes a second pump driven by one of a high spool and the low spool separate from the first pump and communicates oil to engine components separate from the first lubrication system.
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公开(公告)号：US12103699B2
公开(公告)日：2024-10-01
申请号：US17860751
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 , B64D37/34 , B64D41/00 , F02C3/22 , F02C7/224 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/40311
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.
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公开(公告)号：US12044176B2
公开(公告)日：2024-07-23
申请号：US17860756
申请日：2022-07-08
Applicant: RTX Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
Abstract: Aircraft propulsion systems and aircraft are described. The 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 an expander, wherein the main engine core comprises 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 expander, prior to being injected into the burner for combustion.
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公开(公告)号：US20250116224A1
公开(公告)日：2025-04-10
申请号：US18376699
申请日：2023-10-04
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Michael G. McCaffrey
Abstract: A particle separator configured to be disposed within a turbine engine diffuser flow path is provided. The particle separator includes a housing, a hollow cavity member, and a helical member. The housing has a forward end inlet, an exterior wall, an aft wall, an interior cavity, and an aft exhaust passage extending outwardly from the exterior wall adjacent the aft wall. The hollow cavity member has a first portion, an interior region, and an open aft end. The first portion is disposed within the housing interior cavity and includes perforations. The helical member is disposed within the housing interior cavity. The helical member forms a helical passage between the housing exterior wall and the first portion of the hollow cavity member. The helical passage has a passage inlet disposed adjacent to the housing forward end inlet and a terminal end in communication with the aft exhaust passage.
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Patent Agency Ranking
公开(公告)号：US11867069B2
公开(公告)日：2024-01-09
申请号：US17360480
申请日：2021-06-28
Applicant: RTX Corporation
Inventor： John R. Farris , Marc J. Muldoon
CPC classification number: F01D17/16 , F01D17/24 , F05D2220/323 , F05D2220/76 , F05D2270/62
Abstract: A hybrid electric engine including a gas turbine engine including a low speed spool, a high speed spool a fan section, a compressor section, a combustor section, and a turbine section. The hybrid electric engine further includes an electric generator configured to convert rotational power of the high or low speed spool to electricity and a variable area turbine control system electrically connected to the electric generator. The variable area turbine control system being configured to adjust a cross-sectional area of a core flow path of the hybrid electric engine. The variable area turbine control system including a plurality of variable turbine vanes located in the turbine section and a variable area turbine actuator configured to rotate each of the plurality of variable turbine vanes to adjust the cross-sectional area of the core flow path of the hybrid electric engine. The variable area turbine actuator is an electromechanical actuator.
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公开(公告)号：US20250116227A1
公开(公告)日：2025-04-10
申请号：US18376706
申请日：2023-10-04
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Michael G. McCaffrey , Paul R. Hanrahan
Abstract: A particle separator configured to be disposed within a turbine engine diffuser flow path is provided. The particle separator includes a housing that extends between a forward end and an aft end, first and second swirl vane stages, and first and second air flow exits. The first swirl vane stage is configured to cause an air flow passing through the first swirl vane stage to swirl within the housing as the air flow travels axially in a direction from the forward end toward the aft end of the housing. The second swirl vane stage is configured to cause a first portion of the air flow passing through the second swirl vane stage to redirect into a substantially axially directed flow that enters the second air flow exit.
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公开(公告)号：US12188417B1
公开(公告)日：2025-01-07
申请号：US18370505
申请日：2023-09-20
Applicant: RTX CORPORATION
Inventor： David Allen Stachowiak , Marc J. Muldoon
Abstract: A fan drive gear system for a turbine engine includes a carrier that supports rotation of the plurality of intermediate gears and is configured for rotation about the axis. A rotating oil inlet and rotating gutter are attached to the carrier. A transfer bearing is fixed to a static engine structure and engaged to communicate oil to the rotating oil inlet. A static baffle that is disposed radially outward of the transfer bearing and configured to direct oil that is expelled from the transfer bearing into the rotating gutter.
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公开(公告)号：US20240344466A1
公开(公告)日：2024-10-17
申请号：US18660309
申请日：2024-05-10
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：US12060839B1
公开(公告)日：2024-08-13
申请号：US18299431
申请日：2023-04-12
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , Bradley C. Schafer , John P. Virtue, Jr. , Brian V. Winebrenner , Jason B. Solomonides
Abstract: A bowed rotor prevention system includes a gas turbine engine, an electric motor, and a core turning controller in signal communication with the electric motor. The gas turbine engine includes a rotor that is rotatably coupled to a drive shaft. The electric motor rotatably is coupled to a motor shaft, which is mechanically coupled to the drive shaft so as to rotate therewith. The core turning controller is configured to invoke an anti-rotor bowing mode, and to control the electric motor to periodically rotate the rotor into a plurality of rotor positions during a given time period in response to invoking the anti-rotor bowing mode.
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