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1.发明申请公开(公告)号：US20250145301A1
公开(公告)日：2025-05-08
申请号：US18351786
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
IPC: B64D31/18
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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公开(公告)号：US11834186B2
公开(公告)日：2023-12-05
申请号：US17006965
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
CPC classification number: B64D27/02 , B64C23/00 , B64D27/24 , B64D31/12 , F04D25/166
Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.
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公开(公告)号：US11671040B2
公开(公告)日：2023-06-06
申请号：US17242386
申请日：2021-04-28
Applicant: General Electric Company
CPC classification number: H02P9/04 , F01D15/10 , F01D19/00 , F02C7/36 , F02C9/32 , H02P9/008 , F05D2220/32 , F05D2220/76 , F05D2270/023 , F05D2270/101 , F05D2270/20 , F05D2270/303 , F05D2270/304 , F05D2270/3013 , F05D2270/62
Abstract: A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component.
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公开(公告)号：US11447259B2
公开(公告)日：2022-09-20
申请号：US16450131
申请日：2019-06-24
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.
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公开(公告)号：US20220063819A1
公开(公告)日：2022-03-03
申请号：US17007026
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Kurt David Murrow , Alexis Raquel Nunes
Abstract: A hybrid propulsion system for an aircraft can include a propulsor assembly having at least one propulsor and a power generation system. The power generation system can include a first power assembly, a second power assembly, a first electric machine, and a second electric machine. The first power assembly can be drivingly coupled to the first electric machine to produce a first amount of electric power. The second power assembly can be drivingly coupled to the second electric machine to produce a second amount of electric power. A controller can be operably coupled to the first power assembly, the first electric machine, or both and to the second power assembly, the second power assembly, or both. The controller can be configured to combine at least a portion of the first and second amount of power for electric transfer to the propulsor assembly.
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Patent Agency Ranking
公开(公告)号：US20220063792A1
公开(公告)日：2022-03-03
申请号：US17383031
申请日：2021-07-22
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon
Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
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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：US20210249978A1
公开(公告)日：2021-08-12
申请号：US17242386
申请日：2021-04-28
Applicant: General Electric Company
Abstract: A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component.
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公开(公告)号：US10998837B2
公开(公告)日：2021-05-04
申请号：US16838165
申请日：2020-04-02
Applicant: General Electric Company
Abstract: A turbomachine and method for operation turbomachine are provided, the method including adjusting a first load at a first electric machine operably coupled to a first rotatable component, in which the first electric machine is operably coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second electric machine operably coupled to a second rotatable component, in which the second electric machine is operably coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring energy generated from at least one of the first electric machine or the second electric machine.
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公开(公告)号：US20190326789A1
公开(公告)日：2019-10-24
申请号：US16454419
申请日：2019-06-27
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Manoj Ramprasad Shah , James William Bray , Randy Marinus Vondrell , Kurt David Murrow , Jeffrey Anthony Hamel , Samuel Jacob Martin
Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core including a stator winding to produce electrical currents. The stator assembly extending along a longitudinal axis with an inner surface defining a cavity. The rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and rotates about the longitudinal axis. The rotor assembly including a plurality of permanent magnets for generating a magnetic field which interacts with the stator winding to produce the electrical currents in response to rotation of the rotor assembly. within one or more cavities formed in a sleeve component. The sleeve component is configured to include a plurality of cavities or voids into which the permanent magnets are disposed to retain the permanent magnets therein and form an interior permanent magnet generator.
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