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    CMC LAMINATE AIRFOIL WITH PLY DROPS
    11.
    发明公开
    CMC LAMINATE AIRFOIL WITH PLY DROPS 审中-公开

    公开(公告)号：US20230383657A1

    公开(公告)日：2023-11-30

    申请号：US18319586

    申请日：2023-05-18

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim ,  Howard J. Liles ,  Kathryn S. Read

    IPC: F01D5/28 ,  F01D5/14

    CPC classification number: F01D5/282 ,  F01D5/284 ,  F01D5/147 ,  F05D2300/6033 ,  F05D2300/6012 ,  F05D2300/6034

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that circumscribes an internal airfoil cavity and defines leading and trailing ends and pressure and suction sides. The airfoil wall is formed of a ceramic matrix composite (CMC) laminate comprised of fiber plies disposed in a ceramic matrix. The fiber plies include a skin fiber ply that defines an exterior of the airfoil section and at least one inner fiber ply that lines the skin fiber ply. At least one inner fiber ply locally terminates at one of the leading end or the trailing end such that the airfoil wall has fewer of the fiber plies in the leading end or the trailing end than in each of the pressure side and the suction side.

    CMC GAS TURBINE ENGINE COMPONENT WITH SEPARATED FIBER PLIES
    12.
    发明申请
    CMC GAS TURBINE ENGINE COMPONENT WITH SEPARATED FIBER PLIES 有权

    公开(公告)号：US20230056767A1

    公开(公告)日：2023-02-23

    申请号：US17883937

    申请日：2022-08-09

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim

    IPC: F01D25/00 ,  F01D5/28 ,  F01D9/02

    Abstract: A gas turbine engine component includes a component wall that has an exterior core gaspath side and an opposed interior side. The component wall is formed of a ceramic matrix composite that includes a plurality of fiber plies disposed in a ceramic matrix. The component wall includes a corner that connects first and second wall sections. The fiber plies extend continuously through the first wall section, the corner, and the second wall section. The fiber plies are in a stacked contiguous arrangement in the first and second wall sections and at least some of the fiber plies separate from one another in the corner to define one or more void pockets there between.

    Airfoil with fiber plies having interdigitated fingers in trailing end
    13.
    发明授权
    Airfoil with fiber plies having interdigitated fingers in trailing end 有权

    公开(公告)号：US11560800B1

    公开(公告)日：2023-01-24

    申请号：US17525005

    申请日：2021-11-12

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim ,  Jonas S. Banhos

    IPC: F01D5/14 ,  F01D5/28 ,  F01D5/20

    Abstract: An airfoil includes an airfoil section defining suction and pressure sides and leading and a trailing ends, the airfoil section being formed of a fiber-reinforced composite comprised of fiber plies, the fiber plies including at least one core fiber ply defining a tube that circumscribes an internal cavity and an overwrap fiber ply that wraps around the at least one core fiber ply, and aft of the internal cavity the overwrap fiber ply on the pressure side including first fingers and the overwrap ply on the suction side including second fingers, the first fingers being interdigitated with the second fingers to form an interlocked joint in the trailing end.

    Airfoil with serpentine fiber ply layup
    14.
    发明授权
    Airfoil with serpentine fiber ply layup 有权

    公开(公告)号：US11506065B1

    公开(公告)日：2022-11-22

    申请号：US17524809

    申请日：2021-11-12

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim ,  Jonas S. Banhos

    IPC: F01D5/28 ,  F02C3/04

    Abstract: An airfoil includes an airfoil section that is formed of a fiber-reinforced composite that has fiber plies. The fiber plies include at least one overwrap fiber ply, first and second support fiber plies, and a serpentine fiber ply. The overwrap fiber ply circumscribes an internal cavity and defines first and second sides and leading and trailing ends of the airfoil section. The first and second support fiber plies define respective first and second radial tubes in the internal cavity. The serpentine fiber ply winds from the first side and around the first radial tube to the second side, then from the second side back to the first side, and then from the first side and around the second radial tube back to the second side.

    AIRFOIL WITH SANDWICH COMPOSITE FLANGE
    15.
    发明申请
    AIRFOIL WITH SANDWICH COMPOSITE FLANGE 有权

    公开(公告)号：US20240401485A1

    公开(公告)日：2024-12-05

    申请号：US18328217

    申请日：2023-06-02

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

    IPC: F01D5/28 ,  F02C3/04

    Abstract: An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side, a flange that extends from the non-gaspath side, and a gaspath side from which the airfoil section extends. The flange is comprised of a sandwich composite that includes first and second ceramic matrix composite (CMC) skins that each have at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins.

    Composite component with damper for gas turbine engine
    18.
    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
    20.
    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.

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