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    Variable-pitch vane assembly
    1.
    发明授权
    Variable-pitch vane assembly 有权

    公开(公告)号：US10815818B2

    公开(公告)日：2020-10-27

    申请号：US15653064

    申请日：2017-07-18

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace ,  Robert L. Hazzard ,  Mark Borja

    IPC: F01D17/16

    Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.

    CONTROL RINGS
    4.
    发明申请
    CONTROL RINGS 审中-公开

    公开(公告)号：US20200308976A1

    公开(公告)日：2020-10-01

    申请号：US16800257

    申请日：2020-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark Borja

    IPC: F01D11/18 ,  F16J15/44

    Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.

    Blade tip clearance systems
    6.
    发明授权
    Blade tip clearance systems 有权

    公开(公告)号：US09976435B2

    公开(公告)日：2018-05-22

    申请号：US14884015

    申请日：2015-10-15

    Applicant: United Technologies Corporation

    Inventor： Mark Borja ,  Paul W. Palmer

    IPC: F01D11/18 ,  F01D5/02 ,  F01D25/24

    CPC classification number: F01D11/18 ,  F01D5/02 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2240/24 ,  F05D2240/307

    Abstract: A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.

    RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER
    7.
    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
    8.
    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。

    VARIABLE-PITCH VANE ASSEMBLY
    10.
    发明申请
    VARIABLE-PITCH VANE ASSEMBLY 审中-公开

    公开(公告)号：US20190024530A1

    公开(公告)日：2019-01-24

    申请号：US15653064

    申请日：2017-07-18

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace ,  Robert L. Hazzard ,  Mark Borja

    IPC: F01D17/16

    CPC classification number: F01D17/162 ,  F05D2230/60 ,  F05D2240/128 ,  F05D2260/30 ,  F05D2260/50

    Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.

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