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    ROTOR BLADE RETENTION SYSTEM FOR A GAS TURBINE ENGINE
    193.
    发明申请
    ROTOR BLADE RETENTION SYSTEM FOR A GAS TURBINE ENGINE 有权

    公开(公告)号：US20220282626A1

    公开(公告)日：2022-09-08

    申请号：US17193064

    申请日：2021-03-05

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Elzbieta Kryj-Kos

    IPC: F01D5/30 ,  F02C7/047

    Abstract: A rotor blade retention system for a gas turbine engine includes a rotor blade connection component defining a slot, with the rotor blade connection component including a first set of electric leads. Furthermore, the rotor blade retention system includes a rotor blade having a root section received within the slot, with the rotor blade further including a second set of electric leads. In this respect, the first and second sets of electric leads are electrically coupled together to permit electric current to be supplied to the rotor blade.

    VARIABLE STIFFNESS DAMPER SYSTEM
    194.
    发明申请
    VARIABLE STIFFNESS DAMPER SYSTEM 有权

    公开(公告)号：US20220154580A1

    公开(公告)日：2022-05-19

    申请号：US16950940

    申请日：2020-11-18

    Applicant: General Electric Company

    Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Naleen Kumar Verma ,  Nicholas Joseph Kray

    IPC: F01D5/10 ,  F01D25/16

    Abstract: A variable stiffness damper system including an inner spring positioned between a first wall and a second wall, in which the inner spring includes a first member and a second member each coupled together at a distal end by an inner bumper. The first member and the second member are each contoured toward one another. The first member, the second member, and the inner bumper form a cavity therebetween. An outer spring is positioned between the inner spring and the first wall or the second wall. The outer spring includes a spring arm contoured toward the inner spring. The outer spring includes an outer bumper positioned between the inner bumper and the first wall or the second wall. The inner bumper and the outer bumper are selectively couplable to one another based on a load applied to the damper system.

    Blade Dovetail and Retention Apparatus
    195.
    发明申请
    Blade Dovetail and Retention Apparatus 有权

    公开(公告)号：US20220098991A1

    公开(公告)日：2022-03-31

    申请号：US17410754

    申请日：2021-08-24

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Ian F. Prentice

    IPC: F01D5/30

    Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a slot to accommodate a blade of an engine. An example blade apparatus includes: a collet including a slot to receive an end of a blade; and a plurality of retainers including a first retainer positioned on a first end of the collet and a second retainer positioned on a second end of the collet to provide axial retention for the blade in the slot.

    GAS TURBINE ENGINE ROTOR BLADE HAVING A ROOT SECTION WITH COMPOSITE AND METALLIC PORTIONS
    196.
    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.

    Composite Components Having Piezoelectric Fibers
    199.
    发明申请
    Composite Components Having Piezoelectric Fibers 有权

    公开(公告)号：US20210062717A1

    公开(公告)日：2021-03-04

    申请号：US16550721

    申请日：2019-08-26

    Applicant: General Electric Company

    Inventor： Sai Venkata Karthik Saripella ,  Nagamohan Govinahalli Prabhakar ,  Nicholas Joseph Kray

    IPC: F02C7/047 ,  B32B38/18 ,  B32B5/02 ,  B32B5/26 ,  F01D5/14

    Abstract: Composite components and methods for forming composite components are provided. For example, a composite component of a gas turbine engine comprises a composite material, a plurality of piezoelectric fibers, and an anti-icing mechanism. The anti-icing mechanism is in operative communication with the piezoelectric fibers such that the anti-icing mechanism is activated by one or more electrical signals from the piezoelectric fibers. In exemplary embodiments, the composite component is a composite airfoil and the anti-icing mechanism is one or more heating elements. Methods for forming composite components may comprise forming piezoelectric plies comprising piezoelectric fibers embedded in a matrix material; forming reinforcing plies comprising reinforcing fibers embedded in the matrix material; laying up the piezoelectric and reinforcing plies to form a ply layup; and processing the ply layup to form the composite component. Methods including forming a piece of piezoelectric material that is adhered to a composite component also are provided.

    Metallic compliant tip fan blade
    200.
    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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