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公开(公告)号：US20240291008A1
公开(公告)日：2024-08-29
申请号：US18404083
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: H01M8/0612 , F02C7/22
CPC classification number: H01M8/0618 , F02C7/22 , H01M8/0625 , H01M2250/20
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.
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公开(公告)号：US11097849B2
公开(公告)日：2021-08-24
申请号：US16126269
申请日：2018-09-10
Applicant: General Electric Company
Inventor： Nikolai N. Pastouchenko , Randy M. Vondrell , Kurt David Murrow , Jixian Yao , Brandon Wayne Miller , Patrick Michael Marrinan , Daniel Alan Niergarth , Narendra Digamber Joshi
Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.
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公开(公告)号：US10816078B2
公开(公告)日：2020-10-27
申请号：US16136829
申请日：2018-09-20
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , Donald Albert Bradley , Bugra Han Ertas
Abstract: A planet gear train for an engine casing includes a sun gear rotatable by a shaft, a ring gear, a plurality of planet gears rotatably mounted in a planet carrier and meshing with the sun gear and the ring gear, and a damping system. The damping system includes a soft mount disposed about the shaft and coupling the planet carrier the engine casing. The soft mount includes a flexible inner sleeve and a flexible outer sleeve. The flexible inner sleeve and the flexible outer sleeve are fixedly coupled together at respective central portions thereof near the shaft. The damping system further includes a plurality of damping couplers disposed about an outer flange of the planet carrier. The plurality of damping couplers is configured to flexibly couple the flexible inner sleeve to the flexible outer sleeve.
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公开(公告)号：US10807729B2
公开(公告)日：2020-10-20
申请号：US15597571
申请日：2017-05-17
Applicant: General Electric Company
IPC: B64D27/24 , B64D27/10 , H02K1/27 , H02K7/18 , F02K3/12 , F01D15/10 , H02K16/04 , H02K21/14 , B64D27/18 , F02K3/06 , H02K3/28 , H02K5/173 , B64D27/02
Abstract: A propulsion system for an includes a combustion engine, a propulsor, and an electric machine configured to either be driven by the combustion engine or configured to drive the propulsor. The electric machine defines an axis. The electric machine includes a rotor extending along and rotatable about the axis, and a stator having a plurality of winding assemblies, the plurality of winding assemblies spaced along the axis of the electric machine, each winding assembly operable with the rotor independently of an adjacent winding assembly during operation of the electric machine.
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公开(公告)号：US20200085988A1
公开(公告)日：2020-03-19
申请号：US16502913
申请日：2019-07-03
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
Abstract: A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.
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Patent Agency Ranking
公开(公告)号：US20200079513A1
公开(公告)日：2020-03-12
申请号：US16126269
申请日：2018-09-10
Applicant: General Electric Company
Inventor： Nikolai N. Pastouchenko , Randy M. Vondrell , Kurt David Murrow , Jixian Yao , Brandon Wayne Miller , Patrick Michael Marrinan , Daniel Alan Niergarth , Narendra Digamber Joshi
Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.
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公开(公告)号：US10384774B2
公开(公告)日：2019-08-20
申请号：US15259654
申请日：2016-09-08
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
Abstract: A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.
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公开(公告)号：US20190217963A1
公开(公告)日：2019-07-18
申请号：US16366453
申请日：2019-03-27
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Daniel Alan Niergarth , Randy M. Vondrell
IPC: B64D27/24 , F02C7/32 , F02K3/06 , F04D19/02 , B64D27/12 , H02K1/27 , F04D25/06 , F02K5/00 , F01D25/18 , F01D15/10 , F02C7/24 , H02K7/18
CPC classification number: B64D27/24 , B64D27/12 , B64D2027/026 , F01D15/10 , F01D25/183 , F02C7/24 , F02C7/32 , F02K3/06 , F02K5/00 , F04D19/02 , F04D25/06 , F05D2220/323 , F05D2220/768 , F05D2260/98 , H02K1/27 , H02K7/1823
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US10252797B2
公开(公告)日：2019-04-09
申请号：US15259596
申请日：2016-09-08
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
Abstract: An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a first primary thrust propulsor and a first secondary thrust propulsor, the first primary thrust propulsor being different than the first secondary thrust propulsor. Both the first primary thrust propulsor and the first secondary thrust propulsor are mounted to the same one of: a starboard side of the aft wing assembly, a port side of the aft wing assembly, a starboard side of the forward wing assembly, or a port side of the forward wing assembly.
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公开(公告)号：US10227928B2
公开(公告)日：2019-03-12
申请号：US14761698
申请日：2014-01-14
Applicant: General Electric Company
Inventor： Craig Miller Kuhne , Christopher Charles Glynn , Randy M. Vondrell , Andrew Breeze-Stringfellow , Kurt David Murrow , Darek T. Zatorski , Donald Scott Yeager , Nicholas Rowe Dinsmore , Samuel Jacob Martin , Donald Albert Bradley
Abstract: A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.
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