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    Cooled component for a gas turbine engine
    3.
    发明授权
    Cooled component for a gas turbine engine 有权

    公开(公告)号：US11326518B2

    公开(公告)日：2022-05-10

    申请号：US16751494

    申请日：2020-01-24

    Applicant: United Technologies Corporation

    Inventor： Maleek E. Wedderburn ,  Nurhak Erbas-Sen ,  John W. Mubeezi ,  Fumitaka Ichihashi ,  Roger O. Coffey

    IPC: F02C7/12 ,  F01D9/02

    Abstract: A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.

    COMBUSTOR WALL WITH TAPERED COOLING CAVITY
    4.
    发明申请
    COMBUSTOR WALL WITH TAPERED COOLING CAVITY 审中-公开
    COMBUSTOR墙与锥形冷却室

    公开(公告)号：US20160252249A1

    公开(公告)日：2016-09-01

    申请号：US15026761

    申请日：2014-10-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Nurhak Erbas-Sen ,  Frank J. Cunha

    IPC: F23R3/00 ,  F23R3/08

    CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/08 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

    Abstract: A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.

    Abstract translation: 为涡轮发动机提供燃烧器壁，并且包括燃烧器外壳和隔热罩。 隔热罩安装在外壳上，第一和第二腔在外壳和隔热罩之间延伸。 第一凹腔将壳体中限定的孔与第二腔流体耦合。 第二腔体将第一空腔与限定在隔热罩中的孔流体连接。 壳体和隔热罩围绕第二腔室彼此会聚。

    COOLED COMPONENT FOR A GAS TURBINE ENGINE
    6.
    发明申请
    COOLED COMPONENT FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20200256250A1

    公开(公告)日：2020-08-13

    申请号：US16751494

    申请日：2020-01-24

    Applicant: United Technologies Corporation

    Inventor： Maleek E. Wedderburn ,  Nurhak Erbas-Sen ,  John W. Mubeezi ,  Fumitaka Ichihashi ,  Roger O. Coffey

    IPC: F02C7/12 ,  F01D9/02

    Abstract: A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.

    Combustor wall with tapered cooling cavity
    8.
    发明授权
    Combustor wall with tapered cooling cavity 有权

    公开(公告)号：US10047958B2

    公开(公告)日：2018-08-14

    申请号：US15026761

    申请日：2014-10-06

    Applicant: United Technologies Corporation

    Inventor： Nurhak Erbas-Sen ,  Frank J. Cunha

    IPC: F23R3/06 ,  F23R3/00 ,  F23R3/08

    Abstract: A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.

    GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY
    9.
    发明申请
    GAS TURBINE ENGINE COMBUSTOR BULKHEAD ASSEMBLY 审中-公开
    气体涡轮发动机燃烧器大容量组件

    公开(公告)号：US20160169516A1

    公开(公告)日：2016-06-16

    申请号：US14908830

    申请日：2014-08-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Kevin J. Low ,  Nurhak Erbas-Sen

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

    CPC classification number: F23R3/06 ,  F02C3/14 ,  F02C7/18 ,  F05D2260/201 ,  F23R3/002 ,  F23R3/02 ,  F23R3/10 ,  F23R3/12 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle α with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle β with respect to the hot side of the bulkhead support shell. The angle α is different than the angle β.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的隔板组件包括具有多个旋流器开口的隔板支撑壳体。 多个旋流器开口中的每一个被第一多个冷却冲击通道包围，该第一多个冷却冲击通道相对于舱壁支撑壳体的热侧限定角度α，以及限定角度＆bgr的第二多个冷却冲击通道; 相对于舱壁支撑壳的热侧。 角度α与角度bgr不同。

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