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39 条记录 (耗时 0.016 秒)

    3D non-axisymmetric combustor liner
    2.
    发明授权
    3D non-axisymmetric combustor liner 有权

    公开(公告)号：US10514171B2

    公开(公告)日：2019-12-24

    申请号：US15195383

    申请日：2016-06-28

    申请人： United Technologies Corporation

    发明人： Joel H. Wagner ,  Paul M. Lutjen

    IPC分类号： F23R3/16 ,  F23C3/00 ,  F23R3/00 ,  F23R3/50

    摘要： A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.

    DIRT SEPARATOR FOR INTERNALLY COOLED COMPONENTS
    3.
    发明申请
    DIRT SEPARATOR FOR INTERNALLY COOLED COMPONENTS 审中-公开

    公开(公告)号：US20190218940A1

    公开(公告)日：2019-07-18

    申请号：US15873475

    申请日：2018-01-17

    申请人： United Technologies Corporation

    发明人： Tracy A. Propheter-Hinckley ,  Joel H. Wagner

    IPC分类号： F01D25/32 ,  F01D5/18

    摘要： Aspects of the disclosure are directed to a gas turbine engine internally cooled component airfoil having a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from a proximate end to a distal end. The gas turbine engine internally cooled component airfoil may include a cooling system having at least one or more passages bounded in part by the peripheral wall, where 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 may be greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the interior protrusion to vent the first of the one or more passages to the pressure side surface.

    Cast-in film cooling hole structures
    5.
    发明授权
    Cast-in film cooling hole structures 有权

    公开(公告)号：US10913106B2

    公开(公告)日：2021-02-09

    申请号：US16131695

    申请日：2018-09-14

    申请人： United Technologies Corporation

    发明人： John Paulus ,  Dustin W. Davis ,  Joel H. Wagner

    IPC分类号： B22C9/10 ,  B22C7/02 ,  B22C9/24 ,  B22D25/02 ,  F01D5/18

    摘要： A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

    Self-cooled orifice structure
    7.
    发明授权
    Self-cooled orifice structure 有权

    公开(公告)号：US09851105B2

    公开(公告)日：2017-12-26

    申请号：US14790970

    申请日：2015-07-02

    申请人： United Technologies Corporation

    发明人： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

    IPC分类号： F23R3/06 ,  F23R3/00

    CPC分类号： F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    摘要： A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.