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    Dirt separator for internally cooled components
    102.
    发明授权
    Dirt separator for internally cooled components 审中-公开

    公开(公告)号：US10669896B2

    公开(公告)日：2020-06-02

    申请号：US15873475

    申请日：2018-01-17

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Joel H. Wagner

    IPC: F01D25/32 ,  F01D5/18

    Abstract: A gas turbine engine internally cooled component airfoil includes a peripheral wall and a cooling system. The peripheral wall has an external surface including a suction surface and a pressure surface laterally spaced from the suction surface. The cooling system includes at least one or more passages bounded in part by the peripheral wall. At least a first of the one or more passages includes a first passage pressure side surface that includes an interior protrusion including a first sloped surface extending to a peak of the interior protrusion and a second sloped surface extending from the peak substantially in the direction of the pressure side surface. The slope of the second sloped surface is greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the interior protrusion.

    COMBUSTOR-VANE INTERFACE FEATHER SEAL
    104.
    发明申请
    COMBUSTOR-VANE INTERFACE FEATHER SEAL 审中-公开

    公开(公告)号：US20200157959A1

    公开(公告)日：2020-05-21

    申请号：US16195925

    申请日：2018-11-20

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Steven D. Porter ,  Caroline Karanian

    IPC: F01D11/00 ,  F01D9/02 ,  F23R3/00

    Abstract: A gas turbine engine includes a combustor disposed about an engine central axis and a circumferential row of vanes adjacent an exit region of the combustor. The combustor includes a combustor wall and a combustion chamber. The combustor wall has a lip at the exit region. Each vane includes a platform and an airfoil section extending from the platform. The forward edges of the platforms are adjacent the lip of the combustor wall. The lip defines a first annular slot and the forward edges of the vanes collectively define a second annular slot. The first and second annular slots together define an annular seal slot. An annular feather seal is entrapped in the annular seal slot between the combustor wall and the platform.

    AIRFOIL WITH SKINCORE PASSAGE RESUPPLY
    105.
    发明申请
    AIRFOIL WITH SKINCORE PASSAGE RESUPPLY 审中-公开

    公开(公告)号：US20200149416A1

    公开(公告)日：2020-05-14

    申请号：US16532594

    申请日：2019-08-06

    Applicant: United Technologies Corporation

    Inventor： Allan N. Arisi ,  Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley

    IPC: F01D5/18 ,  F04D29/58

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. First and second platforms are attached, respectively, with the first and second ends. A cooling passage circuit extends at least in the first platform and the airfoil section. The cooling passage circuit includes a first plenum in the first platform adjacent at least the first side of the airfoil wall, a hybrid skin core passage embedded in the first side of the airfoil wall and that extends longitudinally, and a resupply passage that connects the first plenum with the hybrid skin core passage.

    AIRFOIL WITH CONVEX SIDES AND MULTI-PIECE BAFFLE
    106.
    发明申请
    AIRFOIL WITH CONVEX SIDES AND MULTI-PIECE BAFFLE 审中-公开

    公开(公告)号：US20200149402A1

    公开(公告)日：2020-05-14

    申请号：US16532626

    申请日：2019-08-06

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley

    IPC: F01D5/14

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second convex sides that join the leading end and the trailing end. The first and second convex sides span in a longitudinal direction between first and second ends. The first and second convex sides define lateral bounds of an internal core cavity, and the first and second convex sides converge toward each other at each of the first and second ends such that the internal core cavity constricts at the first and second ends. A multi-piece baffle is disposed in the internal core cavity and has a shape that is complementary to the first and second convex sides.

    Airfoil having impingement leading edge
    107.
    发明授权
    Airfoil having impingement leading edge 有权

    公开(公告)号：US10584593B2

    公开(公告)日：2020-03-10

    申请号：US15791464

    申请日：2017-10-24

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Airfoils bodies having a first end, a second end, a leading edge, and a trailing edge with a leading edge channel having a first channel wall and a second channel wall that join at a channel base to define the leading edge channel. The leading edge channel extends in a radial direction along the leading edge. A first leading edge impingement cavity is located proximate the leading edge and the first channel wall defines a portion of the first leading edge impingement cavity and a second leading edge impingement cavity with the second channel wall forming a portion of the second leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled such that air flowing from the first leading edge impingement cavity and through the first leading edge impingement hole impinges upon a portion of the second channel wall.

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