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    AIRFOIL FOR A TURBOFAN ENGINE
    53.
    发明公开
    AIRFOIL FOR A TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20230383675A1

    公开(公告)日：2023-11-30

    申请号：US17828112

    申请日：2022-05-31

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

    IPC: F01D5/18 ,  F01D9/04

    CPC classification number: F01D5/18 ,  F01D9/041 ,  F05D2240/121 ,  F05D2260/961 ,  F05D2250/184

    Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.

    REVERSE THRUST TURBOFAN ENGINE
    54.
    发明公开
    REVERSE THRUST TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20230340927A1

    公开(公告)日：2023-10-26

    申请号：US18299102

    申请日：2023-04-12

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Thomas Malkus ,  Kishore Ramakrishnan

    IPC: F02K1/66

    CPC classification number: F02K1/66

    Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.

    LOW-NOISE BLADE FOR AN OPEN ROTOR
    55.
    发明公开
    LOW-NOISE BLADE FOR AN OPEN ROTOR 审中-公开

    公开(公告)号：US20230249810A1

    公开(公告)日：2023-08-10

    申请号：US18169757

    申请日：2023-02-15

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Valeria Andreoli ,  Daniel L. Tweedt

    IPC: B64C27/473 ,  B64C27/467

    CPC classification number: B64C27/473 ,  B64C27/467

    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 1.2 in a first region, less than 0.75 in a second region, and greater than 0.9 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 0.15 and the third region comprises at least x/c=0.80 to 1.0.

    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN
    58.
    发明申请
    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN 有权

    公开(公告)号：US20210147065A1

    公开(公告)日：2021-05-20

    申请号：US17108431

    申请日：2020-12-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché ,  Angela Knepper ,  Nicholas Bown ,  Rathakrishnan Bhaskaran

    IPC: B64C11/18 ,  B64D33/02 ,  B64C11/14

    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

    AIRFOIL FOR A ROTARY MACHINE INCLUDING A PROPELLOR ASSEMBLY
    59.
    发明申请
    AIRFOIL FOR A ROTARY MACHINE INCLUDING A PROPELLOR ASSEMBLY 审中-公开

    公开(公告)号：US20200010174A1

    公开(公告)日：2020-01-09

    申请号：US16550868

    申请日：2019-08-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

    IPC: B64C11/18

    Abstract: In some embodiments, an airfoil comprises a proximal end; a distal end opposite said proximal end; a distal portion extending adjacent said distal end; an edge extending between said proximal end and said distal end; and a surface extending between said proximal end and said distal end, said edge and said surface defining a sweep and a cahedral through said distal portion, wherein the distal portion extends over an acoustically active portion of the airfoil.

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