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公开(公告)号：US20240190574A1
公开(公告)日：2024-06-13
申请号：US18079072
申请日：2022-12-12
Inventor： David Marion Ostdiek , William Joseph Solomon , Mohamed Osama , Arthur William Sibbach , Randy M. Vondrell
Abstract: An electric propulsor is provided. The electric propulsor includes a core cowl and an outer cowl. A first air flowpath is defined radially outward of the outer cowl and a second air flowpath is defined between the core cowl and the outer cowl. The electric propulsor also includes one or more electric machines, a fan rotatably drivable by at least one electric machine, and a booster having a plurality of airfoils disposed at least in part in the second air flowpath, the booster being rotatably drivable by at least one electric machine for compressing air flowing along the second air flowpath. The electric propulsor further includes a heat exchanger disposed within the second air flowpath downstream of the booster, the heat exchanger being in thermal communication with at least one of the one or more electric machines and/or a gearbox mechanically coupled with the fan.
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公开(公告)号：US20230407761A1
公开(公告)日：2023-12-21
申请号：US17844940
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Erich Alois Krammer , Douglas Scott Jacobs , Joseph Alfred Iannotti
CPC classification number: F01D21/02 , F02C9/28 , F02C9/46 , F05D2270/021 , F05D2270/304 , F05D2270/335
Abstract: A method for providing overspeed protection for a gas turbine engine having an engine shaft includes monitoring, via an overspeed protection system, a torque of the engine shaft. The method also includes determining, via the overspeed protection system, at least one additional condition of the engine shaft. Further, the method includes determining, via the overspeed protection system, an overspeed condition of the gas turbine engine when the torque of the engine shaft drops below a torque threshold and the at least one additional condition of the engine shaft is indicative of the gas turbine engine being in an operational state. Thus, the overspeed condition is indicative of an above normal rotational speed of the engine shaft. In addition, the method includes initiating a shutdown procedure for the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.
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公开(公告)号：US11808281B2
公开(公告)日：2023-11-07
申请号：US17686673
申请日：2022-03-04
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Arthur William Sibbach
CPC classification number: F04D29/542 , F04D19/002
Abstract: A gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle, wherein the inlet pre-swirl feature is transitionable between a first angle with respect to the longitudinal axis of the nacelle and a second angle with respect to the longitudinal axis of the nacelle.
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公开(公告)号：US20230332513A1
公开(公告)日：2023-10-19
申请号：US18330000
申请日：2023-06-06
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Daniel Alan Niergarth , Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F01D25/10 , F02C7/12 , F01D25/12 , F05D2260/213 , F05D2220/32 , F05D2260/20
Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.
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公开(公告)号：US11767790B2
公开(公告)日：2023-09-26
申请号：US17408786
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F02C7/05 , F02C6/20 , F02C7/04 , F02K3/00 , F05D2220/36
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.
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Patent Agency Ranking
公开(公告)号：US11761344B1
公开(公告)日：2023-09-19
申请号：US17724074
申请日：2022-04-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Brian Lewis Devendorf , Jeffrey Douglas Rambo , Brian Gene Brzek , Kevin Edward Hinderliter , Erich Alois Krammer , Arthur William Sibbach
CPC classification number: F01D19/02 , F01D25/10 , F01D25/18 , F05D2260/213 , F05D2260/232 , F05D2260/607 , F05D2260/85 , F05D2260/98
Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.
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公开(公告)号：US20230279817A1
公开(公告)日：2023-09-07
申请号：US17687960
申请日：2022-03-07
Applicant: General Electric Company
Inventor： Arthur William Sibbach
CPC classification number: F02C9/28 , F01D21/003 , F02C7/18 , F05D2260/232 , F05D2270/301 , F05D2270/303 , F05D2270/333 , F05D2270/80
Abstract: A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.
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公开(公告)号：US20230279784A1
公开(公告)日：2023-09-07
申请号：US17687976
申请日：2022-03-07
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F01D21/003 , F02C9/28 , H03H9/0009 , H03H9/0014 , F05D2270/3015 , F05D2270/303 , F05D2270/333 , F05D2270/804
Abstract: A liquid fuel system for a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a fuel supplied to the turbine engine through a fuel pathway, and a controller configured to generate control commands configured to control one or more controllable components of the liquid fuel system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors. The fuel may include hydrogen. The fuel may have a liquid phase state.
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公开(公告)号：US20230265862A1
公开(公告)日：2023-08-24
申请号：US17676454
申请日：2022-02-21
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F01D9/041 , F01D25/24 , F05D2220/32 , F05D2240/127 , F05D2240/14 , F05D2260/14
Abstract: A turbofan engine is provided. The turbofan engine includes a fan having a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a radius and a longitudinal axis; and an inlet pre-swirl vane located upstream of the plurality of fan blades and defining a chord, the inlet pre-swirl vane coupled to the nacelle, wherein the inlet pre-swirl vane is angled at a first angle with respect to the radius of the nacelle, and wherein the chord of the inlet pre-swirl vane is angled at a second angle with respect to the longitudinal axis of the nacelle.
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公开(公告)号：US11725526B1
公开(公告)日：2023-08-15
申请号：US17689010
申请日：2022-03-08
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F01D9/041 , F01D25/24 , F05D2240/12 , F05D2240/14 , F05D2250/51 , F05D2260/14
Abstract: A turbofan engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle including an inlet at a leading edge of the nacelle, the inlet defining an interior inlet surface that is non-annular, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle.
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