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公开(公告)号：US12006031B2
公开(公告)日：2024-06-11
申请号：US17366749
申请日：2021-07-02
Applicant: General Electric Company
IPC: B64C29/00 , B64C3/10 , B64C3/32 , B64C3/38 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/40 , H02K7/18
CPC classification number: B64C29/0025 , B64C3/10 , B64C3/32 , B64C3/38 , B64C29/00 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/026 , B64D27/40 , F05D2220/76 , F05D2270/093 , H02K7/1823
Abstract: An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.
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公开(公告)号：US20240067351A1
公开(公告)日：2024-02-29
申请号：US17900296
申请日：2022-08-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas William Brown , Paul Robert Gemin , Di Pan , Dominic Barone
IPC: B64D31/06 , B64D27/24 , H02P29/032
CPC classification number: B64D31/06 , B64D27/24 , H02P29/032 , B64D2221/00
Abstract: Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.
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公开(公告)号：US11440673B2
公开(公告)日：2022-09-13
申请号：US16688108
申请日：2019-11-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas William Brown , Paul Robert Gemin , Di Pan , Dominic Barone
IPC: H02P29/032 , B64D27/24 , B64D31/06
Abstract: Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, a voltage regulator, and at least one propeller. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.
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公开(公告)号：US11117675B2
公开(公告)日：2021-09-14
申请号：US16042216
申请日：2018-07-23
Applicant: General Electric Company
IPC: B64D27/24 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64C35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64C29/00 , B64D35/02 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.
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公开(公告)号：US11428171B2
公开(公告)日：2022-08-30
申请号：US16705341
申请日：2019-12-06
Applicant: General Electric Company
Inventor： Thomas William Brown , Justin Paul Smith , Dominic Barone
Abstract: A multi-spool turbomachine having an electric machine that can be controlled to input power to one of the spools of the turbomachine is provided. In one aspect, the multi-spool turbomachine can be a hybrid electric gas turbine engine for an aircraft. The hybrid electric gas turbine engine can include a first spool, a second spool, and an electric machine operatively coupled with the first spool. In response to an increase in thrust demand, the electric motor receives electrical power from an electrical power source. In turn, the electric machine applies a torque to the first spool, causing the first spool to increase in rotational speed. In this manner, the electric machine can electrically assist the turbomachine to meet the increase in thrust demand.
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Patent Agency Ranking
公开(公告)号：US11124307B2
公开(公告)日：2021-09-21
申请号：US16042403
申请日：2018-07-23
Applicant: General Electric Company
IPC: B64D27/24 , B64C29/00 , B64C3/38 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64D35/02 , B64D33/04 , B64D31/06 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along the wing, the wing including one or more components being moveable to selectively expose the plurality of vertical thrust electric fans, the wing further including a diffusion assembly positioned downstream of at least one vertical thrust electric fan of the plurality of vertical thrust electric fans, the diffusion assembly defining a diffusion area ratio greater than 1:1 and less than about 2:1.
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公开(公告)号：US20190047681A1
公开(公告)日：2019-02-14
申请号：US16042267
申请日：2018-07-23
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.
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公开(公告)号：US20230126222A1
公开(公告)日：2023-04-27
申请号：US18086792
申请日：2022-12-22
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Arthur Vorwerk Radun , Dominic Barone
Abstract: The present disclosure is directed to turbine engines and systems for active stability control of rotating compression systems utilizing an electric machine operatively coupled thereto. In one exemplary aspect, an electric machine operatively coupled with a compression system, e.g., via a shaft system, is controlled to provide shaft damping for instability fluctuations of the pressurized fluid stream within the compression system. Based on control data indicative of a system state of the compression system, a control parameter of the electric machine is adjusted to control or change an output of the shaft system. Adjusting the shaft system output by adjusting one or more control parameters of the electric machine allows the compression system to dampen instability fluctuations of the fluid stream within the compression system. A method for active stability control of a compression system operatively coupled with an electric machine via a shaft system is also provided.
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公开(公告)号：US10934008B2
公开(公告)日：2021-03-02
申请号：US15429934
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Glenn David Crabtree , Dominic Barone
Abstract: An aircraft includes an electric power source having a combustion engine and an electric generator. The electric generator is powered by the combustion engine. The aircraft also includes a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor. The aircraft also includes an electrical outlet configured for connection with an outside power sink. The electrical outlet and the propulsion assembly are selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly.
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公开(公告)号：US20210033101A1
公开(公告)日：2021-02-04
申请号：US16526184
申请日：2019-07-30
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Arthur Vorwerk Radun , Dominic Barone
Abstract: The present disclosure is directed to turbine engines and systems for active stability control of rotating compression systems utilizing an electric machine operatively coupled thereto. In one exemplary aspect, an electric machine operatively coupled with a compression system, e.g., via a shaft system, is controlled to provide shaft damping for instability fluctuations of the pressurized fluid stream within the compression system. Based on control data indicative of a system state of the compression system, a control parameter of the electric machine is adjusted to control or change an output of the shaft system. Adjusting the shaft system output by adjusting one or more control parameters of the electric machine allows the compression system to dampen instability fluctuations of the fluid stream within the compression system. A method for active stability control of a compression system operatively coupled with an electric machine via a shaft system is also provided.
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