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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：US10822101B2
公开(公告)日：2020-11-03
申请号：US15699349
申请日：2017-09-08
Applicant: General Electric Company
Inventor： Kurt David Murrow , Darek Tomasz Zatorski , Andrew Breeze-Stringfellow , Randy M. Vondrell , Dominic Barone
IPC: B64D27/24 , B64C3/32 , B64C29/00 , B64C3/38 , B64D29/04 , B64D27/08 , B64D35/02 , B64D33/04 , B64D31/06 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a hybrid-electric propulsion system. The hybrid-electric propulsion system includes a power source including a combustion engine and an electric generator; a plurality of vertical thrust electric fans integrated into the wing and oriented to generate thrust along the vertical direction, the plurality of vertical thrust electric fans arranged along a length of the wing and driven by the power source; and a forward thrust propulsor. The forward thrust propulsor it is selectively or permanently mechanically coupled to the combustion engine.
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公开(公告)号：US10436151B2
公开(公告)日：2019-10-08
申请号：US14943058
申请日：2015-11-17
Applicant: General Electric Company
Abstract: A gas turbine engine includes a core and a tie shaft. The tie shaft is rotatable about an axial direction of the gas turbine engine by the core of the gas turbine engine. The gas turbine engine additionally includes a modular fan having a plurality of fan blades and a frame. The plurality fan blades are attached to the frame and the frame is slidably received on the tie shaft of the gas turbine engine. The modular fan additionally includes an attachment member removably attaching the frame to the tie shaft of the gas turbine engine to removably install the modular fan in the gas turbine engine.
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公开(公告)号：US10384773B2
公开(公告)日：2019-08-20
申请号：US15259622
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 and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a propulsion system having a port propulsor and a starboard propulsor. The port and starboard propulsors are each attached to the wing assembly on opposing sides of the fuselage and are rotatable between a forward thrust position and a vertical thrust position. The propulsion system also includes a supplemental propulsor mounted to the fuselage to provide certain efficiencies for the aircraft.
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75.发明申请公开(公告)号：US20190136958A1
公开(公告)日：2019-05-09
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
CPC classification number: F16H57/0006 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/96 , F16H1/28 , F16H57/082
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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Patent Agency Ranking
公开(公告)号：US10252810B2
公开(公告)日：2019-04-09
申请号：US15132304
申请日：2016-04-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.01×RFP−0.311, such that the propulsion engine may operate at a desired efficiency.
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公开(公告)号：US20180355804A1
公开(公告)日：2018-12-13
申请号：US15417710
申请日：2017-01-27
Applicant: General Electric Company
CPC classification number: F02C9/00 , F01D5/147 , F01D5/284 , F01D9/04 , F01D9/041 , F02C3/04 , F02C7/141 , F02C7/18 , F02C9/18 , F02K3/06 , F05D2220/3212 , F05D2220/323 , F05D2240/128 , F05D2240/24 , F05D2270/02 , F05D2300/13 , F05D2300/6033 , Y02T50/672 , Y02T50/673
Abstract: A gas turbine engine includes a compressor section defining a compressor exit temperature, T3. The gas turbine engine also includes a combustion section and a turbine section, with the turbine section defining a turbine inlet temperature, T4. A ratio, T4:T3, of the turbine inlet temperature, T4, to compressor exit temperature, T3, during operation of the gas turbine engine at a rated speed is less than or equal to 1.85.
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公开(公告)号：US20180065743A1
公开(公告)日：2018-03-08
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
CPC classification number: B64C29/0033 , B64C3/385 , B64C21/06 , B64C27/28 , B64C29/00 , B64C29/0008 , B64D27/14 , B64D27/24 , B64D2027/026 , B64D2221/00 , H02P9/04 , Y02T50/64
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：US20180065739A1
公开(公告)日：2018-03-08
申请号：US15259523
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
CPC classification number: B64C29/0033 , B64D27/14 , B64D27/24 , B64D2027/026 , B64D2221/00
Abstract: An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a hybrid electric propulsion system having a port propulsor and a starboard propulsor, with the port and starboard propulsors attached to the wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position. The hybrid electric propulsion system additionally includes an electric power source including a combustion engine and an electric generator, with the electric generator being driven by the combustion engine. The electric generator is in electrical communication with each of the port and starboard propulsors for powering the port and starboard propulsors.
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公开(公告)号：US20180051701A1
公开(公告)日：2018-02-22
申请号：US15242827
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Daniel Alan Niergarth , Randy M. Vondrell , Paul Robert Gemin
IPC: F04D25/06 , F02C3/04 , F01D5/02 , F01D5/10 , F02C7/36 , F01D25/24 , B64D27/18 , B64D27/10 , F04D19/00
CPC classification number: F04D25/06 , B64D27/02 , B64D27/24 , B64D2027/026 , F01D5/02 , F01D5/10 , F01D25/24 , F02C3/04 , F02C6/00 , F02C7/32 , F02C7/36 , F04D19/002 , F05D2220/32 , F05D2220/76 , F05D2220/766 , F05D2240/24 , F05D2260/40311 , F05D2260/96 , H02K5/15 , H02K5/1732 , H02K7/083 , H02K7/116 , H02K7/1823 , Y02T50/672 , Y02T50/673
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.
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