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    FAN BLADES FOR FRANGIBILITY
    75.
    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
    77.
    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
    78.
    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.

    Noise reducing gas turbine engine airfoil
    80.
    发明授权
    Noise reducing gas turbine engine airfoil 有权

    公开(公告)号：US10788053B2

    公开(公告)日：2020-09-29

    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.

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