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    Gas turbine engine flowpath component including vectored cooling flow holes
    1.
    发明授权
    Gas turbine engine flowpath component including vectored cooling flow holes 有权

    公开(公告)号：US11415020B2

    公开(公告)日：2022-08-16

    申请号：US16702887

    申请日：2019-12-04

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Brian R. Pelletier

    IPC: F01D25/12 ,  F01D11/24 ,  F01D9/04

    Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.

    GAS TURBINE ENGINE FLOWPATH COMPONENT INCLUDING VECTORED COOLING FLOW HOLES
    2.
    发明申请
    GAS TURBINE ENGINE FLOWPATH COMPONENT INCLUDING VECTORED COOLING FLOW HOLES 有权

    公开(公告)号：US20210172335A1

    公开(公告)日：2021-06-10

    申请号：US16702887

    申请日：2019-12-04

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Brian R. Pelletier

    IPC: F01D25/12 ,  F01D11/24

    Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.

    RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER
    6.
    发明申请
    RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER 审中-公开
    具有轴向反应构件的壳体支撑结构的径向位置控制

    公开(公告)号：US20160053624A1

    公开(公告)日：2016-02-25

    申请号：US14781263

    申请日：2014-04-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  Brandon T. Rouse ,  Mark Borja ,  Igor S. Garcia ,  John R. Farris ,  Thomas Almy ,  Brian R. Pelletier

    IPC: F01D11/08 ,  F01D9/04 ,  F01D25/24

    CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/12 ,  F01D11/14 ,  F01D11/20 ,  F01D11/22 ,  F01D11/24 ,  F01D25/24 ,  Y02T50/672

    Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.

    Abstract translation: 用于燃气涡轮发动机级的径向位置控制组件包括壳体结构。 支撑结构由壳体结构可操作地支撑。 支撑环可操作地支撑所支撑的结构。 支撑结构和支撑环具有不同的热膨胀系数。 密封结构与支撑结构相邻。 基于相邻的支撑结构之间的周向间隙，并且基于支撑环和支撑结构之间的径向间隙，支撑环在热瞬变期间的间隙处相对于密封结构保持支撑结构。 销支撑相对于壳体结构的支撑结构，并且被配置为将支撑环与支撑结构上的负载隔离开。

    Segmented Clearance Control Ring
    7.
    发明申请
    Segmented Clearance Control Ring 审中-公开
    分段间隙控制环

    公开(公告)号：US20150337673A1

    公开(公告)日：2015-11-26

    申请号：US14759317

    申请日：2013-02-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  Igor Garcia ,  John R. Farris ,  Brian R. Pelletier ,  Thomas Almy ,  Brandon T. Rouse ,  Mark Borja

    IPC: F01D11/08 ,  B23P19/00 ,  F01D9/04

    CPC classification number: F01D11/08 ,  B23P19/00 ,  F01D9/04 ,  F01D11/20 ,  F01D25/246 ,  Y10T29/49325

    Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.

    Abstract translation: 公开了具有至少两个段的间隙控制环。 每个片段与相邻的片段互锁以形成完整的箍间隙控制环。 分离的载体和密封件或一体式载体和密封件可以安装在间隙控制环上。 间隙控制环的分段结构允许与现有技术的单件间隙控制环相比，用于燃气涡轮发动机的分段壳体更简单的组装。 分段结构还可以与单件预组装和多级转子一起使用。

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