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    VANE ASSEMBLY FOR OPEN FAN ENGINE
    13.
    发明申请
    VANE ASSEMBLY FOR OPEN FAN ENGINE 有权

    公开(公告)号：US20250043688A1

    公开(公告)日：2025-02-06

    申请号：US18230611

    申请日：2023-08-04

    Applicant: General Electric Company

    Inventor： Sara Elizabeth Carle ,  Daniel L. Tweedt ,  Syed Arif Khalid

    IPC: F01D9/04

    Abstract: The present disclosure is generally related to a vane assembly for an open fan engine having a rotor and a stator. The vane assembly is a plurality of vanes each arranged about the stator. Each of the vanes of the vane assembly has a leading edge (LE) with a leading edge angle (LEA). A combination of aircraft angle of attack, sideslip, and upwash due to lifting bodies can create a flow angularity into the engine. The leading edge angle (LEA) of each of the vanes varies depending upon the circumferential location about the stator so that the impact on the flow angularity into the engine is reduced or increased in different circumferential regions.

    UNDUCTED PROPULSION SYSTEM
    14.
    发明公开
    UNDUCTED PROPULSION SYSTEM 审中-公开

    公开(公告)号：US20230322360A1

    公开(公告)日：2023-10-12

    申请号：US18205794

    申请日：2023-06-05

    Applicant: General Electric Company

    Inventor： Daniel L. Tweedt ,  Syed Arif Khalid

    IPC: B64C11/48 ,  F01D9/02

    CPC classification number: B64C11/48 ,  F01D9/02 ,  F05D2220/325 ,  F05D2220/323

    Abstract: Apparatuses and systems are provided herein for unducted propulsion systems. The system includes a forward housing for high efficiency for high subsonic sustained flight. A plurality of blades are affixed to the forward housing, wherein the forward housing defines a flowpath curve extending from the forward-most end of the forward housing through the axial extent of a forward blade root. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes a first point having a first radius where the radius reaches a maximum forward of the forward blade root and a second point aft of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.029.

    Low-noise blade for an open rotor
    15.
    发明授权
    Low-noise blade for an open rotor 有权

    公开(公告)号：US11608743B1

    公开(公告)日：2023-03-21

    申请号：US17665483

    申请日：2022-02-04

    Applicant: General Electric Company

    Inventor： Daniel L. Tweedt ,  Syed Arif Khalid

    IPC: F01D5/14

    Abstract: A blade for an open rotor includes a pressure side and a suction side, the pressure side and the suction side intersecting at a leading edge and a trailing edge, wherein for at least 30% of a span of the blade, the meanline of the airfoil section is shaped such that a relative curvature parameter is greater than 1.75 in a first region, less than 0.75 in a second region, and greater than 1.2 in a third region, wherein the relative curvature parameter of a region is defined by Δζn/Δζtot/Δ(x/c)n wherein ζ corresponds to the inverse tangent of the slope of a meanline curve, subscript n indicates the region, and x/c is a chordwise location normalized by the chord, and wherein the first region comprises at least x/c=0.0 to 0.10 and the third region comprises at least x/c=0.85 to 1.0.

    GAS TURBINE ENGINE OUTLET GUIDE VANE ASSEMBLY
    16.
    发明申请
    GAS TURBINE ENGINE OUTLET GUIDE VANE ASSEMBLY 有权

    公开(公告)号：US20210222575A1

    公开(公告)日：2021-07-22

    申请号：US17061594

    申请日：2020-10-02

    Applicant: General Electric Company

    Inventor： Andrew Breeze-Stringfellow ,  Syed Arif Khalid

    IPC: F01D9/04 ,  F01D17/16

    Abstract: A single unducted rotor engine is provided. The single unducted rotor engine defines an axial direction and a radial direction, the engine including: a power source; a casing surrounding the power source; an unducted rotor assembly driven by the power source comprising a single row of rotor blades; and an outlet guide vane assembly comprising a plurality of pairs of outlet guide vanes, each pair of the plurality of pairs of outlet guide vanes including first outlet guide vane extending from the casing at a location downstream from the single row of rotor blades of the unducted rotor assembly and a second outlet guide vane also positioned downstream from the single row of rotor blades of the unducted rotor assembly; wherein the first outlet guide vane of each pair of outlet guide vanes defines a first geometry, wherein the second outlet guide vane of each pair of outlet guide vanes defines a second geometry, and wherein the first geometry is not equal to the second geometry.

    ADVANCE RATIO FOR SINGLE UNDUCTED ROTOR ENGINE
    17.
    发明申请
    ADVANCE RATIO FOR SINGLE UNDUCTED ROTOR ENGINE 有权

    公开(公告)号：US20210108572A1

    公开(公告)日：2021-04-15

    申请号：US17071271

    申请日：2020-10-15

    Applicant: General Electric Company

    Inventor： Syed Arif Khalid ,  Andrew Breeze-Stringfellow

    IPC: F02C9/00 ,  F02C7/36 ,  F01D5/12 ,  F01D9/02

    Abstract: A method is provided of operating a single unducted rotor engine, the single unducted rotor engine comprising a single stage of unducted rotor blades. The method includes operating the single unducted rotor engine to define a flight speed, V0, in a length unit per second and an angular speed, n, in revolutions per second, the single stage of unducted rotor blades defining a diameter, D, in the length unit; wherein operating the single unducted rotor engine comprises operating the single unducted rotor engine to define an advance ratio greater than 3.8 while operating the single unducted rotor engine at a net efficiency of at least 0.8, the advance ratio defined by the equation V0/(n×D).

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