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公开(公告)号：US20250027425A1
公开(公告)日：2025-01-23
申请号：US18235417
申请日：2023-08-18
Applicant: RTX Corporation
Inventor： Graham R. Philbrick , Gary Collopy , John P. Virtue, Jr.
Abstract: An operating method is provided during which a command is received to increase thrust generated by a propulsor rotor from a first thrust level to a second thrust level. The propulsor rotor is operatively coupled to an engine core and an electric machine. The engine core includes a flowpath, a compressor section, a combustor section and a turbine section. The engine core is operated in a transient state to increase power output from the engine core to the propulsor rotor from a first power level to a second power level in response to the command. The electric machine is operated to boost the power output from the engine core to the propulsor rotor while the engine core is operating in the transient state. A clearance control system for the engine core is operated based on the operation of the electric machine.
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公开(公告)号：US12123310B2
公开(公告)日：2024-10-22
申请号：US18480627
申请日：2023-10-04
Applicant: RTX CORPORATION
Inventor： Stephen G. Pixton , Gary Collopy , Ozhan Turgut
CPC classification number: F01D15/12 , F02C3/00 , F02C7/32 , F05D2220/323
Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a propulsor section including a propulsor having a plurality of propulsor blades, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a first turbine, the first driving the propulsor through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.
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公开(公告)号：US12092038B2
公开(公告)日：2024-09-17
申请号：US16991275
申请日：2020-08-12
Applicant: RTX Corporation
Inventor： Gary Collopy , Arthur M. Salve, Jr. , Michael Winter
CPC classification number: F02C7/36 , B64D27/02 , B64D27/026 , F05D2220/323 , F05D2270/023 , F05D2270/053 , F05D2270/304
Abstract: Hybrid electric propulsion systems are described. The systems include a gas turbine engine having low and high speed spools, each spool having a respective compressor and turbine. A mechanical power transmission is configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric machine is configured to augment rotational power of at least one of the spools, and a controller is operable to determine a rotational speed of the low speed spool, determine a rotational speed of the high speed spool, determine if a predetermined operational zone of operation based on the determined rotational speeds is present, and when a predetermined operational zone is determined, control a power augmentation of at least one spool to limit dwell operation of the gas turbine engine within the predetermined operational zone.
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Patent Agency Ranking
公开(公告)号：US20240301834A1
公开(公告)日：2024-09-12
申请号：US18652699
申请日：2024-05-01
Applicant: RTX Corporation
Inventor： Michael M. Romero , Gary Collopy
CPC classification number: F02C9/16 , F02C7/32 , F05D2270/101 , F05D2270/62
Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.
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公开(公告)号：US20240240569A1
公开(公告)日：2024-07-18
申请号：US18480627
申请日：2023-10-04
Applicant: RTX CORPORATION
Inventor： Stephen G. Pixton , Gary Collopy , Ozhan Turgut
CPC classification number: F01D15/12 , F02C3/00 , F02C7/32 , F05D2220/323
Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a propulsor section including a propulsor having a plurality of propulsor blades, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a first turbine, the first driving the propulsor through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.
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公开(公告)号：US11821369B2
公开(公告)日：2023-11-21
申请号：US16991143
申请日：2020-08-12
Applicant: RTX Corporation
Inventor： Gary Collopy
CPC classification number: F02C7/262 , F02C6/20 , F02C7/268 , B64D2027/026 , F05D2220/323 , F05D2260/85 , F05D2270/091 , F05D2270/101
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; and a controller to: detect an in-flight windmill re-start condition of the gas turbine engine; and cause power to be supplied from a power source to the electric motor in order to augment rotational power of the high speed or the low speed spool during the detected in-flight windmill re-start condition.
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公开(公告)号：US12209501B1
公开(公告)日：2025-01-28
申请号：US18235394
申请日：2023-08-18
Applicant: RTX Corporation
Inventor： Graham R. Philbrick , Gary Collopy , John P. Virtue, Jr.
Abstract: An operating method is provided during which a command is received to decrease thrust generated by a propulsor rotor from a first thrust level to a second thrust level. The propulsor rotor is operatively coupled to an engine core and an electric machine. The engine core includes a flowpath, a compressor section, a combustor section and a turbine section. The engine core is operated in a transient state to decrease total power of the engine core from a first power level to a second power level in response to the command. The electric machine is operated as a generator to reduce power output from the engine core to the propulsor rotor while the engine core is operating in the transient state. A clearance control system for the engine core is operated based on the operation of the electric machine.
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公开(公告)号：US20250027424A1
公开(公告)日：2025-01-23
申请号：US18235394
申请日：2023-08-18
Applicant: RTX Corporation
Inventor： Graham R. Philbrick , Gary Collopy , John P. Virtue, Jr.
Abstract: An operating method is provided during which a command is received to decrease thrust generated by a propulsor rotor from a first thrust level to a second thrust level. The propulsor rotor is operatively coupled to an engine core and an electric machine. The engine core includes a flowpath, a compressor section, a combustor section and a turbine section. The engine core is operated in a transient state to decrease total power of the engine core from a first power level to a second power level in response to the command. The electric machine is operated as a generator to reduce power output from the engine core to the propulsor rotor while the engine core is operating in the transient state. A clearance control system for the engine core is operated based on the operation of the electric machine.
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