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    PREFABRICATED NOODLE
    11.
    发明申请
    PREFABRICATED NOODLE 有权

    公开(公告)号：US20240376017A1

    公开(公告)日：2024-11-14

    申请号：US18196594

    申请日：2023-05-12

    Applicant: Raytheon Technologies Corporation

    Inventor： Christian X. Campbell ,  Kathryn S. Read ,  James T. Roach ,  Robert A. White, III ,  Daniel Josiah Whitney

    IPC: C04B35/80 ,  C04B35/628 ,  C04B35/64 ,  C04B35/657

    Abstract: A method of forming a ceramic matrix composite includes fabricating a space filling insert by assembling the space filling insert from a fibrous ceramic material, placing the space filling insert into a tooling fixture, the tooling fixture having an internal shape complementary to a shape of the insert, and infiltrating the space filling insert with a first ceramic material. The method further includes forming a preform by laying up a plurality of fibrous ceramic plies and inserting the infiltrated space filling insert into a void defined by the plurality of plies. The method further includes infiltrating the preform with a second ceramic material.

    Composite component with damper for gas turbine engine
    14.
    发明授权
    Composite component with damper for gas turbine engine 有权

    公开(公告)号：US11879351B2

    公开(公告)日：2024-01-23

    申请号：US17549168

    申请日：2021-12-13

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim ,  James T. Roach

    IPC: F01D25/28 ,  F01D25/24

    CPC classification number: F01D25/28 ,  F01D25/24

    Abstract: An assembly for a gas turbine engine according to an aspect of the present disclosure includes a metallic damper including a first contact surface and a gas turbine engine component. The gas turbine engine component includes a main body extending in a first direction between a gaspath surface and a second contact surface. The first and second contact surfaces oppose each other along an interface extending in a second direction. The first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state. The main body is established by a composite including fibers in a matrix material. At least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction. A method of damping for a gas turbine engine is also disclosed.

    REINFORCING FIBERS FOR USE IN CERAMIC MATRIX COMPOSITES, METHODS OF MANUFACTURE AND ARTICLES COMPRISING THE SAME
    16.
    发明公开
    REINFORCING FIBERS FOR USE IN CERAMIC MATRIX COMPOSITES, METHODS OF MANUFACTURE AND ARTICLES COMPRISING THE SAME 审中-公开

    公开(公告)号：US20230192568A1

    公开(公告)日：2023-06-22

    申请号：US17554419

    申请日：2021-12-17

    Applicant: Raytheon Technologies Corporation

    Inventor： Jonas S. Banhos ,  Russell Kim ,  James T. Roach

    IPC: C04B41/45 ,  C04B41/51

    CPC classification number: C04B41/4596 ,  C04B41/51

    Abstract: Disclosed herein is a method of reinforcing a composite comprising determining a location of a first cooling hole in a plurality of plies; where a cooling gas is transported through the cooling hole; disposing a z-fiber in the plurality of plies at a location proximate to where the first cooling hole will be located; where the z-fiber enters the plurality of plies at either an upper surface or a lower surface; and where the z-fiber traverses a portion of the plurality of plies in the z-direction proximate to the first cooling hole; and traverses the plurality of plies in an x or y direction further away from the first cooling hole; where the z-direction is in the thickness direction of the plurality of plies and where the x and y-direction are perpendicular to the z-direction.

    Gas turbine engine component having an airfoil with internal cross-ribs
    18.
    发明授权
    Gas turbine engine component having an airfoil with internal cross-ribs 有权

    公开(公告)号：US12196095B2

    公开(公告)日：2025-01-14

    申请号：US18071121

    申请日：2022-11-29

    Applicant: Raytheon Technologies Corporation

    Inventor： James T. Roach ,  Jonas Banhos ,  Russell Kim

    IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02

    Abstract: A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.

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