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    TURBINE SHROUD ASSEMBLY
    2.
    发明申请
    TURBINE SHROUD ASSEMBLY 审中-公开

    公开(公告)号：US20180363498A1

    公开(公告)日：2018-12-20

    申请号：US15623990

    申请日：2017-06-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Glenn Curtis TAXACHER ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

    IPC: F01D25/04 ,  F01D9/04

    CPC classification number: F01D25/04 ,  F01D9/04 ,  F01D11/08 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2260/42 ,  F05D2300/175 ,  F05D2300/6033

    Abstract: A turbine shroud assembly is disclosed including an inner shroud, an outer shroud, a shroud dampening pin, and a biasing apparatus. The inner shroud is adjacent to a hot gas path. The outer shroud is adjacent to the inner shroud and distal from the hot gas path, and includes a channel extending from an aperture adjacent to the inner shroud. The shroud dampening pin is within the channel and contacts the inner shroud, and includes a shaft, a contact surface, and a cap. The shaft is within the channel. The contact surface extends through the aperture in contact with the inner shroud. The cap is distal across the shaft from the contact surface. The biasing apparatus contacts the cap, is driven by a pressurized fluid, and provides a biasing force away from the outer shroud along the shroud dampening pin to the inner shroud through the contact surface.

    COATED CERAMIC MATRIX COMPOSITE OF METALLIC COMPONENT AND METHOD FOR FORMING A COMPONENT
    3.
    发明申请
    COATED CERAMIC MATRIX COMPOSITE OF METALLIC COMPONENT AND METHOD FOR FORMING A COMPONENT 审中-公开

    公开(公告)号：US20180363477A1

    公开(公告)日：2018-12-20

    申请号：US15623802

    申请日：2017-06-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Matthew Troy HAFNER ,  Joshua Lee MARGOLIES

    IPC: F01D5/28 ,  F23R3/00 ,  F01D9/04 ,  F01D9/02

    Abstract: A coated ceramic matrix composite or metallic component and a gas turbine assembly is provided. The component comprises a substrate comprising a first surface and a hot gas path surface. The hot gas path surface is arranged and disposed to contact a hot gas flow when the component is installed in the gas turbine. The first surface is disposed at an angle to the hot gas path surface and opposes at least one adjacent component when the component is installed in the gas turbine. The component further comprises an angled or rounded feature extending from the first surface to the hot gas path surface. The component further comprises an environmental barrier coating or thermal barrier coating on at least a portion of the hot gas path surface. The angled or rounded feature reduces an incidence angle of the hot gas flow onto the first surface. The gas turbine assembly comprises a plurality of the coated components.

    TURBINE SHROUD ASSEMBLY
    8.
    发明申请
    TURBINE SHROUD ASSEMBLY 有权
    涡轮SHROUD总成

    公开(公告)号：US20170051627A1

    公开(公告)日：2017-02-23

    申请号：US14827698

    申请日：2015-08-17

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Matthew Troy HAFNER ,  Victor John MORGAN ,  Frederic Woodrow ROBERTS

    IPC: F01D11/22 ,  F01D25/00 ,  F01D25/08 ,  F01D25/04

    CPC classification number: F01D11/22 ,  F01D11/14 ,  F01D11/20 ,  F01D25/005 ,  F01D25/04 ,  F01D25/08 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/52 ,  F05D2260/96 ,  F05D2300/17 ,  F05D2300/171 ,  F05D2300/502 ,  F05D2300/6033

    Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.

    Abstract translation: 公开了一种涡轮机护罩组件，其包括具有与热气体路径相邻的表面的内护罩，外护罩，设置在内护罩和外护罩之间的阻尼块，第一偏压装置和第二偏压装置。 第一偏置装置向内护罩提供第一偏置力，从而朝向热气体路径并远离外护罩的方向偏压内护罩的第一偏转距离。 第二偏压装置向阻尼器块提供第二偏压力，使阻尼器块沿朝向热气体路径并远离外护罩的方向偏置第二偏转距离。 第二偏转距离大于第一偏转距离。

    ANTI-ROTATION SHROUD DAMPENING PIN AND TURBINE SHROUD ASSEMBLY
    10.
    发明申请
    ANTI-ROTATION SHROUD DAMPENING PIN AND TURBINE SHROUD ASSEMBLY 审中-公开

    公开(公告)号：US20180363504A1

    公开(公告)日：2018-12-20

    申请号：US15623938

    申请日：2017-06-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Glenn Curtis TAXACHER ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

    IPC: F01D25/24 ,  F01D9/04

    Abstract: An anti-rotation shroud dampening pin is disclosed including a shaft, an anti-rotation dampening tip at a first end of the shaft, and a cap at a second end of the shaft. The anti-rotation dampening tip includes a pin non-circular cross-section. A turbine shroud assembly is disclosed, including an inner shroud, an outer shroud, the anti-rotation shroud dampening pin, and a biasing apparatus. The inner shroud includes an anti-rotation depression having a depression non-circular cross-section. The outer shroud includes a channel extending from an aperture adjacent to the inner shroud. The anti-rotation shroud dampening pin is disposed within the channel and in contact with the inner shroud, and extends through the aperture into the anti-rotation depression. The biasing apparatus contacts the cap and provides a biasing force to the inner shroud through the anti-rotation dampening tip. The pin non-circular cross-section mates non-rotatably into the depression non-circular cross-section.

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