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    Composite component with damper for gas turbine engine
    3.
    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

    申请人： RAYTHEON TECHNOLOGIES CORPORATION

    发明人： Russell Kim ,  James T. Roach

    IPC分类号： F01D25/28 ,  F01D25/24

    CPC分类号： F01D25/28 ,  F01D25/24

    摘要： 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
    5.
    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

    申请人： Raytheon Technologies Corporation

    发明人： Jonas S. Banhos ,  Russell Kim ,  James T. Roach

    IPC分类号： C04B41/45 ,  C04B41/51

    CPC分类号： C04B41/4596 ,  C04B41/51

    摘要： 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.

    COMPOSITE COMPONENT WITH DAMPER FOR GAS TURBINE ENGINE
    9.
    发明公开
    COMPOSITE COMPONENT WITH DAMPER FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20230184136A1

    公开(公告)日：2023-06-15

    申请号：US17549168

    申请日：2021-12-13

    申请人： RAYTHEON TECHNOLOGIES CORPORATION

    发明人： Russell Kim ,  James T. Roach

    IPC分类号： F01D25/28 ,  F01D25/24

    CPC分类号： F01D25/28 ,  F01D25/24

    摘要： 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.

    CMC gas turbine engine component with separated fiber plies
    10.
    发明授权
    CMC gas turbine engine component with separated fiber plies 有权

    公开(公告)号：US12104496B2

    公开(公告)日：2024-10-01

    申请号：US17883937

    申请日：2022-08-09

    申请人： RAYTHEON TECHNOLOGIES CORPORATION

    发明人： Russell Kim

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

    CPC分类号： F01D25/005 ,  F01D5/282 ,  F01D9/02 ,  F05D2220/32 ,  F05D2300/6033

    摘要： 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.