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    Turbomachine with Alternatingly Spaced Rotor Blades
    62.
    发明申请
    Turbomachine with Alternatingly Spaced Rotor Blades 审中-公开

    公开(公告)号：US20200263547A1

    公开(公告)日：2020-08-20

    申请号：US16280531

    申请日：2019-02-20

    Applicant: General Electric Company

    Inventor： Alan Roy Stuart ,  Tsuguji Nakano ,  Thomas Ory Moniz ,  Andrew Breeze-Stringfellow ,  Richard Schmidt

    IPC: F01D5/06

    Abstract: A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.

    Noise Reducing Gas Turbine Engine Airfoil
    63.
    发明申请
    Noise Reducing Gas Turbine Engine Airfoil 审中-公开

    公开(公告)号：US20200132087A1

    公开(公告)日：2020-04-30

    申请号：US16170254

    申请日：2018-10-25

    Applicant: General Electric Company

    Inventor： Arun Kumar ,  Nitesh Jain ,  Nicholas Joseph Kray ,  Thomas Ory Moniz ,  Andrew Breeze-Stringfellow

    IPC: F04D29/66 ,  F01D5/14 ,  F02K3/06

    Abstract: A noise reducing airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a pressure side, a suction side, and a trailing edge sheath including an outer surface coupled to the trailing edge of the airfoil. The trailing edge sheath extends at least partially along the chord on the pressure and suction sides at each point along the span within the trailing edge sheath. The trailing edge sheath defines a fluid passageway extending along at least a portion of the span. Further, the trailing edge sheath defines at least one aperture on at least one of the pressure side, the suction side, or trailing edge fluidly coupling the fluid passageway to the outer surface.

    Vertical Takeoff and Landing Aircraft
    65.
    发明申请
    Vertical Takeoff and Landing Aircraft 审中-公开

    公开(公告)号：US20190047681A1

    公开(公告)日：2019-02-14

    申请号：US16042267

    申请日：2018-07-23

    Applicant: General Electric Company

    Inventor： Kurt David Murrow ,  Andrew Breeze-Stringfellow ,  Darek Tomasz Zatorski ,  Dominic Barone

    IPC: B64C3/32 ,  B64C29/00 ,  B64C3/38 ,  B64D27/24

    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.

    Reverse Thrust Engine
    68.
    发明申请
    Reverse Thrust Engine 审中-公开

    公开(公告)号：US20170226960A1

    公开(公告)日：2017-08-10

    申请号：US15018893

    申请日：2016-02-09

    Applicant: General Electric Company

    Inventor： Tsuguji Nakano ,  Andrew Breeze-Stringfellow

    IPC: F02K1/68 ,  F02K1/76

    CPC classification number: F02K1/68 ,  F02C9/18 ,  F02K1/66 ,  F02K1/766 ,  F02K3/075

    Abstract: A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit.

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