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公开(公告)号：US10392106B2
公开(公告)日：2019-08-27
申请号：US15259564
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 port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.
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公开(公告)号：US20190047719A1
公开(公告)日：2019-02-14
申请号：US16042522
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust propulsor driven by the power source; and a wing extending from the fuselage, the vertical thrust propulsor positioned on or at least partially within the wing, the wing including a diffusion assembly, the diffusion assembly including at least one diffusion member fixed in position and located downstream of the vertical thrust propulsor for diffusing an airflow from the vertical thrust propulsor.
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公开(公告)号：US20180257787A1
公开(公告)日：2018-09-13
申请号：US15977588
申请日：2018-05-11
Applicant: General Electric Company
Inventor： Jeffrey Anthony Hamel , Kurt David Murrow
CPC classification number: B64D27/24 , B64C21/06 , B64D27/18 , B64D27/20 , B64D2027/026 , B64D2205/00 , Y02T50/166 , Y02T50/62 , Y10S903/905 , Y10S903/906 , Y10S903/907
Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
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公开(公告)号：US20180065741A1
公开(公告)日：2018-03-08
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
CPC classification number: B64C29/0033 , B64C3/32 , B64C11/001 , B64C11/28 , B64C11/46 , B64C27/08 , B64C2201/027 , B64D27/24 , B64D2027/026 , Y02T50/64
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：US09821917B2
公开(公告)日：2017-11-21
申请号：US14859514
申请日：2015-09-21
Applicant: General Electric Company
CPC classification number: B64D27/14 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/00 , B64D29/04 , B64D2027/264 , B64D2033/0226
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
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Patent Agency Ranking
公开(公告)号：US09815560B2
公开(公告)日：2017-11-14
申请号：US14859566
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D29/04 , B64C1/16 , B64C21/06 , B64D27/20 , B64D33/02 , B64D2033/0226 , Y02T50/166
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：US20170081036A1
公开(公告)日：2017-03-23
申请号：US14859556
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D27/14 , B64C1/16 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/04 , B64D33/02 , Y02T50/166
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. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow for a maximum amount of airflow into the aft engine.
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公开(公告)号：US20150380999A1
公开(公告)日：2015-12-31
申请号：US14317294
申请日：2014-06-27
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
CPC classification number: H02K1/28 , H02K1/182 , H02K1/278 , H02K1/30 , H02K21/026 , H02K21/24 , H02K49/108 , Y02E10/725
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 configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.
Abstract translation: 永磁机和用于永磁机的转子组件。 永磁体机器包括定子组件，该定子组件包括定子铁心，该定子铁心构造成产生磁场并且沿纵向轴线延伸，内表面限定空腔，转子组件包括转子芯和转子轴。 转子芯设置在定子腔内部并且构造成围绕纵向轴线旋转。 转子组件还包括多个永磁体，用于产生与定子磁场相互作用以产生转矩的磁场。 永磁体设置在形成在套筒部件中的一个或多个空腔内。 套筒部件构造成在其中包括多个空腔或空隙，从而为永磁机提供最小的重量。 永磁机提供增加的离心负载能力，增加功率密度和改善的电气性能。
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公开(公告)号：US20230415883A1
公开(公告)日：2023-12-28
申请号：US18466922
申请日：2023-09-14
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon
CPC classification number: B64C11/305 , F01D5/12 , F02C6/20 , F02C9/00 , F05D2220/323
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：US11312502B2
公开(公告)日：2022-04-26
申请号：US16542834
申请日：2019-08-16
Applicant: General Electric Company
Inventor： Jeffrey Anthony Hamel , Kurt David Murrow
Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
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