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    Airfoil for a gas turbine engine
    71.
    发明授权
    Airfoil for a gas turbine engine 有权

    公开(公告)号：US11898464B2

    公开(公告)日：2024-02-13

    申请号：US17232822

    申请日：2021-04-16

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Nitesh Jain

    IPC: F01D5/28 ,  F01D5/14

    CPC classification number: F01D5/282 ,  F01D5/147 ,  F05D2220/36 ,  F05D2300/603

    Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.

    FAN BLADES FOR FRANGIBILITY
    76.
    发明申请
    FAN BLADES FOR FRANGIBILITY 有权

    公开(公告)号：US20220341330A1

    公开(公告)日：2022-10-27

    申请号：US17241948

    申请日：2021-04-27

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  David Crall

    IPC: F01D5/14

    Abstract: Fan blades for frangibility are disclosed. An example airfoil for use in a gas turbine engine includes a root portion to be disposed adjacent to a disk of the gas turbine engine, a tip portion including a cavity disposed therein, and wherein the tip portion and cavity are configured to fragment when exposed to a threshold force corresponding to a high-stress event.

    GAS TURBINE ENGINE ROTOR BLADE HAVING A ROOT SECTION WITH COMPOSITE AND METALLIC PORTIONS
    78.
    发明申请
    GAS TURBINE ENGINE ROTOR BLADE HAVING A ROOT SECTION WITH COMPOSITE AND METALLIC PORTIONS 有权

    公开(公告)号：US20220074307A1

    公开(公告)日：2022-03-10

    申请号：US17012595

    申请日：2020-09-04

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Nitesh Jain

    IPC: F01D5/02

    Abstract: A rotor blade for a gas turbine engine includes an airfoil section and a root section extending along a longitudinal direction between an upstream surface and a downstream surface. The root section further extends along a radial direction between an inner surface positioned at an inner end of the root section and an outer end coupled to the airfoil section. Moreover, the root section extends along a circumferential direction between a first side surface and a second side surface. Furthermore, the root section defines a longitudinal centerline extending along the longitudinal direction and positioned equidistant from the inner surface and the outer end in the radial direction. The root section includes a first portion formed from a composite material and a second portion formed from a metallic material, with the longitudinal centerline extending through the second portion of the root section.

    Metallic compliant tip fan blade
    79.
    发明授权
    Metallic compliant tip fan blade 有权

    公开(公告)号：US10920607B2

    公开(公告)日：2021-02-16

    申请号：US16145759

    申请日：2018-09-28

    Applicant: General Electric Company

    Inventor： Nitesh Jain ,  Kishore Budumuru ,  Nicholas Joseph Kray ,  Daniel Edward Mollmann

    IPC: F01D5/14 ,  F01D21/04 ,  F01D5/18

    Abstract: A blade for a propulsion apparatus. The blade includes a body having opposed pressure and suction sides. The blade extends in span between a root and a tip and the blade extends in chord between a leading edge and a trailing edge. The blade includes a fracture structure that is defined within the body and positioned such that it is spaced-away from the tip. The fracture structure includes at least one chamber. A first fracture wall is disposed between the at least one chamber and the pressure side, and a second fracture wall is disposed between the at least one chamber and the suction side. The fracture structure is configured to fail when a predetermined force is applied to the tip such that the tip separates from the remainder of the body.

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