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    Film cooling a combustor wall of a turbine engine
    11.
    发明授权
    Film cooling a combustor wall of a turbine engine 有权

    公开(公告)号：US10533745B2

    公开(公告)日：2020-01-14

    申请号：US15113558

    申请日：2015-02-03

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

    IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06 ,  F02C7/12

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

    Grommet assembly and method of design
    12.
    发明授权
    Grommet assembly and method of design 有权

    公开(公告)号：US10443848B2

    公开(公告)日：2019-10-15

    申请号：US14677520

    申请日：2015-04-02

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr. ,  Andreas Sadil

    IPC: F23R3/06 ,  F02C7/18 ,  F23R3/00 ,  F23R3/04 ,  F23R3/50

    Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.

    Combustor quench aperture cooling
    13.
    发明授权
    Combustor quench aperture cooling 有权

    公开(公告)号：US10378768B2

    公开(公告)日：2019-08-13

    申请号：US15037555

    申请日：2014-12-04

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

    IPC: F23R3/00 ,  F23R3/06 ,  F02C7/18

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

    COOLING A COMBUSTOR HEAT SHIELD PROXIMATE A QUENCH APERTURE
    14.
    发明申请
    COOLING A COMBUSTOR HEAT SHIELD PROXIMATE A QUENCH APERTURE 审中-公开
    冷却COMBUSTOR热风罩可以放置一个孔

    公开(公告)号：US20160298843A1

    公开(公告)日：2016-10-13

    申请号：US15100374

    申请日：2014-12-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr. ,  Randal G. McKinney

    IPC: F23R3/06 ,  F02C3/04 ,  F23R3/00

    Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 涡轮发动机组件的燃烧器壁包括外壳和隔热罩。 燃烧器壁限定了通过壳体和隔热罩的淬火孔。 热屏蔽限定了与骤冷孔的距离等于渗出口宽度的大约二十五倍到七十五倍之间的渗出口。

    Film cooling a combustor wall of a turbine engine
    16.
    发明授权
    Film cooling a combustor wall of a turbine engine 有权

    公开(公告)号：US11320146B2

    公开(公告)日：2022-05-03

    申请号：US16703211

    申请日：2019-12-04

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

    IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06 ,  F02C7/12

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

    Cooling a quench aperture body of a combustor wall
    18.
    发明授权
    Cooling a quench aperture body of a combustor wall 有权

    公开(公告)号：US10386068B2

    公开(公告)日：2019-08-20

    申请号：US15038774

    申请日：2014-12-03

    Applicant: United Technologies Corporation

    Inventor： Stanislav Kostka, Jr. ,  Frank J. Cunha

    IPC: F23R3/00 ,  F23R3/04 ,  F23R3/06 ,  F23R3/50

    Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.

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