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公开(公告)号：US20220355916A1
公开(公告)日：2022-11-10
申请号：US17504618
申请日：2021-10-19
Applicant: General Electric Company
Inventor： Dhananjaya Rao Gottapu , Kurt David Murrow , Narendra Digamber Joshi
IPC: B64C23/00
Abstract: An aircraft having distributed fans for boundary layer ingestion is provided. In one aspect, an aircraft includes a fuselage extending between a forward end and an aft end. The aircraft includes a plurality of boundary layer ingestion fans arranged in an array. Each fan of the array is mounted to and arranged circumferentially around the aft end of the fuselage. The fans are positioned so as to ingest boundary layer airflow flowing along the fuselage. At least two fans of the array are different sizes. Each fan of the fan array is operatively coupled with an electric machine. The electric machines are operable to drive their respective fans to produce thrust. The fans of the array are independently controlled in accordance with the boundary layer suction requirements of the aircraft.
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公开(公告)号：US20220234746A1
公开(公告)日：2022-07-28
申请号：US17722882
申请日：2022-04-18
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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公开(公告)号：US11124308B2
公开(公告)日：2021-09-21
申请号：US16042522
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow
IPC: B64D27/24 , B64C29/00 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64D35/02 , B64C3/38 , 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 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：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：US11111858B2
公开(公告)日：2021-09-07
申请号：US15417710
申请日：2017-01-27
Applicant: General Electric Company
IPC: F02C9/00 , F02C3/04 , F02K3/06 , F01D5/28 , F02C9/18 , F02C7/141 , F01D9/04 , F02C7/18 , F01D5/14
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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Patent Agency Ranking
公开(公告)号：US20200244199A1
公开(公告)日：2020-07-30
申请号：US16838165
申请日：2020-04-02
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：US10677158B2
公开(公告)日：2020-06-09
申请号：US14982793
申请日：2015-12-29
Applicant: General Electric Company
IPC: F02C3/107 , F02K3/065 , F02K3/077 , F01D5/02 , F01D25/30 , F02C7/04 , F02C7/36 , F04D29/32 , F02K3/062 , F02K3/06
Abstract: A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.
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公开(公告)号：US20200023959A1
公开(公告)日：2020-01-23
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
IPC: B64C29/00
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：US20190329896A1
公开(公告)日：2019-10-31
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：US10414508B2
公开(公告)日：2019-09-17
申请号：US15977588
申请日：2018-05-11
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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