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    PRESSURE EQUALIZING ORIFICE FOR BAFFLES IN VANES
    2.
    发明申请
    PRESSURE EQUALIZING ORIFICE FOR BAFFLES IN VANES 审中-公开

    公开(公告)号：US20180347919A1

    公开(公告)日：2018-12-06

    申请号：US15608795

    申请日：2017-05-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler ,  Atul Kohli

    IPC: F28F13/02 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12

    CPC classification number: F01D9/065 ,  F05D2240/126

    Abstract: Disclosed is a module for a gas turbine engine, the module including: a disk rotatable about an engine central axis and a vane fixedly disposed upstream of the disk, the vane being hollow and including a vane cavity, the vane cavity having a vane longitudinal span between a vane upstream opening and vane downstream opening, the vane including: a baffle fixedly supported within the vane cavity, the baffle having a hollow interior and having a baffle longitudinal span between a baffle upstream surface and a baffle downstream surface, the baffle longitudinal span being less than the vane longitudinal span to define a partial space eater baffle; wherein a baffle opening area fluidly connects the vane cavity to the baffle interior, and the baffle opening area is between 5.0×10̂−5 square inches and 1.5×10̂−3 square inches.

    AIRFOIL WITH VARYING WALL THICKNESS
    5.
    发明申请
    AIRFOIL WITH VARYING WALL THICKNESS 审中-公开

    公开(公告)号：US20190271230A1

    公开(公告)日：2019-09-05

    申请号：US16003755

    申请日：2018-06-08

    Applicant: United Technologies Corporation

    Inventor： Atul Kohli ,  Jaime G. Ghigliotty ,  James B. Downey

    IPC: F01D5/18 ,  F02C3/04

    Abstract: An airfoil includes an airfoil body that has a peripheral wall that defines an exterior side and an interior side that bounds an internal cavity in the airfoil body. The peripheral wall has first and second wall sections joined by a transition section. The first wall section is thicker than the second wall section. The transition section provides a change in thickness between the first wall section and the second wall section. The second wall section includes a cooling hole that has a first end that opens to the internal cavity at the interior side and a second end that opens to the exterior side.

    Gas turbine engine airfoil with showerhead cooling holes near leading edge
    6.
    发明授权
    Gas turbine engine airfoil with showerhead cooling holes near leading edge 有权

    公开(公告)号：US11286787B2

    公开(公告)日：2022-03-29

    申请号：US15266855

    申请日：2016-09-15

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Dominic J. Mongillo ,  Atul Kohli

    IPC: F01D5/18 ,  F01D25/12 ,  F04D29/58 ,  F01D9/02 ,  F01D11/08 ,  F04D29/08 ,  F04D29/32 ,  F04D29/54

    Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges to provide an exterior airfoil surface. The pressure and suction side walls are spaced apart from one another in a thickness direction. A stagnation line is located near the leading edge. A cooling passage is provided between the pressure and suction side walls. The showerhead cooling holes are arranged at least one of adjacent to or on the stagnation line. At least one of the showerhead cooling holes has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole is arranged on each of opposing sides of the stagnation line. Each showerhead cooling hole has the diffuser with a first diffuser angle that expands downstream in the thickness direction in opposing directions from one another when separated by the stagnation line.

    Internal cooling cavity with trip strips
    7.
    发明授权
    Internal cooling cavity with trip strips 有权

    公开(公告)号：US10605094B2

    公开(公告)日：2020-03-31

    申请号：US14602035

    申请日：2015-01-21

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

    IPC: F01D5/18

    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

    Baffle insert for a gas turbine engine component and component with baffle insert
    8.
    发明授权
    Baffle insert for a gas turbine engine component and component with baffle insert 有权

    公开(公告)号：US10422233B2

    公开(公告)日：2019-09-24

    申请号：US14961726

    申请日：2015-12-07

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Atul Kohli

    IPC: F02C1/00 ,  F01D5/18 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F23R3/00

    Abstract: A component of a gas turbine engine having: an internal cooling cavity; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; at least one separating feature located between a pair of ends of a pair of the plurality of trip strips, wherein the plurality of trip strips and the at least one separating feature are spaced from an interior surface of the internal cooling cavity; a plurality of trip strips extending upwardly from the interior surface; and at least one separating feature located between a pair of ends of the plurality of trip strips located on the interior surface of the internal cooling cavity, wherein the plurality of trip strips and the at least one separating feature of the interior surface are spaced from the exterior surface of the baffle insert.

    Baffle insert for a gas turbine engine component and method of cooling
    9.
    发明授权
    Baffle insert for a gas turbine engine component and method of cooling 有权

    公开(公告)号：US10280841B2

    公开(公告)日：2019-05-07

    申请号：US14961694

    申请日：2015-12-07

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Atul Kohli

    IPC: F02C7/18 ,  F01D25/08 ,  F01D5/18

    Abstract: A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine. The method including the steps of: directing a cooling fluid between an interior surface of an internal cooling cavity of the component and an exterior surface of a baffle insert located in the internal cooling cavity; and creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity, wherein the internal cooling cavity is elliptical in shape.

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