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41.发明公开公开(公告)号：US20240228054A9
公开(公告)日：2024-07-11
申请号：US18351745
申请日：2023-07-13
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Kurt David Murrow , Paul Robert Gemin , Philip M. Cioffi , John Russell Yagielski
Abstract: A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.
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42.发明公开公开(公告)号：US20240175400A1
公开(公告)日：2024-05-30
申请号：US18351735
申请日：2023-07-13
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Kurt David Murrow , Paul Robert Gemin , Philip M. Cioffi , John Russell Yagielski
CPC classification number: F02C9/56 , F01D15/12 , F02C7/32 , F01D15/10 , F05D2220/323 , F05D2240/40 , F05D2270/052 , F05D2270/07 , F05D2270/335 , F05D2270/44 , F05D2270/62
Abstract: A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.
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43.发明申请公开(公告)号：US20220350348A1
公开(公告)日：2022-11-03
申请号：US17244280
申请日：2021-04-29
Applicant: General Electric Company
Inventor： Alexis Raquel Nunes , Kurt David Murrow
Abstract: An aircraft equipped with a multi-fan propulsion system for controlling flight orientation transitions is provided. In one example aspect, an aircraft includes a fuselage and a pair of wings. The aircraft includes a propulsion system having a first propulsor and a second propulsor each mounted to the fuselage. The first propulsor has a fan positioned primarily above and the second propulsor has a fan positioned primarily below the pair of wings. The aircraft also includes a computing system having one or more processors configured to cause, in response to a demand to change an orientation of the aircraft for a flight orientation transition, the fans of the first and second propulsors to produce different amounts of thrust with respect to one another so that the aircraft performs the flight orientation transition. The thrust differential causes the aircraft to transition between orientations.
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公开(公告)号：US11352132B2
公开(公告)日：2022-06-07
申请号：US16042141
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Andrew Breeze-Stringfellow , Daniel Lawrence Tweedt , Syed Arif Khalid , Kurt David Murrow
Abstract: A lift fan apparatus includes: a rotor having at least one rotatable hub carrying at least one row of blades; a duct surrounding the rotor, the duct including spaced-apart peripheral walls extending between an inlet and an exit, the peripheral walls collectively defining a flow channel which includes a diffuser disposed downstream of the rotor, in which a flow area at the exit is greater than a flow area at the rotor; and a plurality of spaced-apart splitters disposed in the diffuser, each of the splitters having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the splitters divide the diffuser into a plurality of side-by-side flow passages.
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公开(公告)号：US20220063793A1
公开(公告)日：2022-03-03
申请号：US17007503
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
Abstract: An aircraft equipped with a distributed unducted fan propulsion system is provided. In one aspect, an aircraft includes a body defining a lateral centerline that separates the body into a first side and a second side. One or more first unducted fans are mounted to the first side of the body. The one or more first unducted fans are rotatable in a first direction. One or more second unducted fans are mounted to the second side of the body. The one or more second unducted fans are rotatable in a second direction that is opposite the first direction.
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Patent Agency Ranking
公开(公告)号：US11117676B2
公开(公告)日：2021-09-14
申请号：US16042267
申请日：2018-07-23
Applicant: General Electric Company
IPC: B64D27/24 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64D35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64C29/00 , 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 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：US11053014B2
公开(公告)日：2021-07-06
申请号：US16042299
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: A method for operating a vertical takeoff and landing aircraft includes modifying a first variable component of a wing associated with a first portion of the plurality of vertical thrust electric fans relative to a second variable component of the wing associated with a second portion of the plurality of vertical thrust electric fans to adjust an exposure ratio of the first portion of the plurality of vertical thrust electric fans relative to the second portion of the plurality of vertical thrust electric fans.
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公开(公告)号：US10710735B2
公开(公告)日：2020-07-14
申请号：US16042439
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Kurt David Murrow
IPC: B64D27/24 , B64C29/00 , B64D29/04 , B64C3/32 , B64C11/30 , B64C27/26 , B64D27/08 , B64D35/02 , B64C3/38 , B64C11/46 , B64C3/10 , B64D27/04 , B64D33/04 , B64D31/06 , F02C7/36 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: A method is provided for operating a propulsion system of a vertical takeoff and landing aircraft, the propulsion system including a turbomachine, an electric machine, a forward thrust propulsor, and a plurality of vertical thrust electric fans. The method includes driving the forward thrust propulsor with the turbomachine; rotating the electric machine with the turbomachine to generate electrical power; determining a failure condition of the turbomachine; and providing electrical power to the electric machine to drive the forward thrust propulsor with the electric machine in response to determining the failure condition of the turbomachine.
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公开(公告)号：US20190047717A1
公开(公告)日：2019-02-14
申请号：US16042370
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Kurt David Murrow , Darek Tomasz Zatorski , Dominic Barone
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan oriented to generate thrust along a vertical direction and powered by the power source; and a wing extending from the fuselage and including the vertical thrust electric fan positioned at least partially therein. The wing includes a variable geometry assembly having partial wing assembly, the partial wing assembly including a frame and a first member, the partial wing assembly moveable generally along a longitudinal direction when the variable geometry assembly is moved between a forward thrust position and a vertical thrust position, the first member moveable relative to the frame to form an exhaust path for the vertical thrust electric fan.
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公开(公告)号：US20190047680A1
公开(公告)日：2019-02-14
申请号：US16042216
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 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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