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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
申请人： RTX Corporation
IPC分类号： F02C7/36
CPC分类号： F02C7/36 , F05D2220/36 , F05D2260/40311
摘要： 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：US12103699B2
公开(公告)日：2024-10-01
申请号：US17860751
申请日：2022-07-08
申请人： RTX Corporation
CPC分类号： B64D37/30 , B64D37/34 , B64D41/00 , F02C3/22 , F02C7/224 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/40311
摘要： 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
申请人： RTX Corporation
摘要： 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：US20240344466A1
公开(公告)日：2024-10-17
申请号：US18660309
申请日：2024-05-10
申请人： RTX Corporation
发明人： Bradley C. Schafer , Brian V. Winebrenner , Jason B. Solomonides , Marc J. Muldoon , John P. Virtue, JR.
CPC分类号： F01D25/36 , F01D21/04 , F05D2270/114
摘要： 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
申请人： RTX Corporation
发明人： Marc J. Muldoon , Bradley C. Schafer , John P. Virtue, Jr. , Brian V. Winebrenner , Jason B. Solomonides
摘要： 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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公开(公告)号：US12049850B1
公开(公告)日：2024-07-30
申请号：US18370511
申请日：2023-09-20
申请人： RTX CORPORATION
CPC分类号： F02C7/36 , F01D25/18 , F02C7/06 , F05D2220/36 , F05D2260/40311 , F05D2260/98
摘要： 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
申请人： RTX Corporation
发明人： Bradley C. Schafer , Brian V. Winebrenner , Jason B. Solomonides , Marc J. Muldoon , John P. Virtue, Jr.
CPC分类号： F01D25/36 , F01D21/04 , F05D2270/114
摘要： 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
申请人： RTX Corporation
CPC分类号： B64D37/30 , B64D15/12 , B64D41/00 , F02C3/22 , F02C7/32 , F05D2220/323 , F05D2220/76
摘要： 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：US11867069B2
公开(公告)日：2024-01-09
申请号：US17360480
申请日：2021-06-28
申请人： RTX Corporation
发明人： John R. Farris , Marc J. Muldoon
CPC分类号： F01D17/16 , F01D17/24 , F05D2220/323 , F05D2220/76 , F05D2270/62
摘要： 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：US12055098B2
公开(公告)日：2024-08-06
申请号：US17860215
申请日：2022-07-08
申请人： RTX Corporation
摘要： 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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