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    RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER
    11.
    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
    12.
    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。

    SEAL COATING
    13.
    发明申请
    SEAL COATING 审中-公开

    公开(公告)号：US20200025014A1

    公开(公告)日：2020-01-23

    申请号：US16388219

    申请日：2019-04-18

    Applicant: United Technologies Corporation

    Inventor： John R. Farris ,  Michael G. McCaffrey

    IPC: F01D11/12 ,  B05D3/00 ,  F01D25/00 ,  C23C4/01 ,  C23C28/04 ,  C23C4/18 ,  C23C4/11

    Abstract: A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.

    ENHANCED ADHESION THERMAL BARRIER COATING
    19.
    发明申请
    ENHANCED ADHESION THERMAL BARRIER COATING 审中-公开

    公开(公告)号：US20170159460A1

    公开(公告)日：2017-06-08

    申请号：US14959057

    申请日：2015-12-04

    Applicant: United Technologies Corporation

    Inventor： Mosheshe Camara-Khary Blake ,  Thomas N. Slavens ,  John R. Farris

    IPC: F01D5/28 ,  F02C7/00 ,  F01D25/08 ,  F01D11/08 ,  F01D25/24 ,  F02C3/04 ,  F01D9/04

    Abstract: A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality of gas path components exposed to a primary fluid flowpath through the compressor section, the combustor section and the turbine section. At least one of the gas path components includes an exterior facing surface, a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface, and a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.

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