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    ANTI-ROTATION SHROUD DAMPENING PIN AND TURBINE SHROUD ASSEMBLY
    2.
    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.

    TURBINE BUCKET ASSEMBLY AND TURBINE SYSTEM
    3.
    发明申请
    TURBINE BUCKET ASSEMBLY AND TURBINE SYSTEM 审中-公开
    涡轮泵组件和涡轮机系统

    公开(公告)号：US20150345314A1

    公开(公告)日：2015-12-03

    申请号：US14290164

    申请日：2014-05-29

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Dwight Eric DAVIDSON ,  Herbert Chidsey ROBERTS, III ,  John McConnell DELVAUX ,  Brian Denver POTTER ,  Stephen Paul WASSYNGER

    IPC: F01D5/30

    CPC classification number: F01D5/30 ,  F01D5/282 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3084 ,  F05D2240/80 ,  F05D2300/175 ,  F05D2300/6033

    Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a non-segmented airfoil having a root section and a tip section integral with the root section, the tip section having a tip end with a second axial length, the second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The turbine wheel includes a turbine wheel material and the single-lobe joint and the non-segmented airfoil include a turbine bucket material, the turbine bucket material having a higher heat resistance and a lower thermal expansion than the turbine wheel material.

    Abstract translation: 公开了一种涡轮机桶组件和涡轮机系统。 涡轮叶片组件包括具有整体平台的单瓣接头，该接头具有第一轴向长度; 一个非分段翼型件，其具有根部和与该根部一体的尖端部分，该末端部分具有一个具有第二轴向长度的末端，该第二轴向长度小于该第一轴向长度; 以及涡轮机轮，具有具有对应于单瓣接头的几何形状并且联接到单瓣接头的插座。 涡轮机叶轮包括涡轮叶轮材料，单瓣接头和非分段翼型件包括涡轮机叶片材料，涡轮机叶片材料具有比涡轮机轮材料更高的耐热性和更低的热膨胀性。

    CERAMIC MATRIX COMPOSITE COMPONENT, TURBINE SYSTEM AND FABRICATION PROCESS
    8.
    发明申请
    CERAMIC MATRIX COMPOSITE COMPONENT, TURBINE SYSTEM AND FABRICATION PROCESS 审中-公开
    陶瓷基体复合材料，涡轮机系统和制造工艺

    公开(公告)号：US20150093237A1

    公开(公告)日：2015-04-02

    申请号：US14041262

    申请日：2013-09-30

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John McConnell DELVAUX

    IPC: F01D5/20 ,  F01D5/28 ,  F01D11/12

    CPC classification number: F01D5/20 ,  F01D5/282 ,  F01D5/288 ,  F01D11/122

    Abstract: A ceramic matrix composite component, turbine system and fabrication process are disclosed. The ceramic matrix composite (CMC) component includes a CMC material, an environmental barrier coating (EBC) on the CMC material, and a hard wear coating applied over the EBC. The turbine system includes a rotatable CMC component having a hard wear coating, and a stationary turbine component, the stationary turbine component having an abradable coating arranged and disposed to be cut by the silicon carbide material. The fabrication process includes positioning the rotatable CMC a pre-determined distance from the stationary turbine component and rotating the rotatable CMC component. The hard wear coating on the rotatable CMC component cuts the abradable coating on the stationary turbine component.

    Abstract translation: 公开了陶瓷基体复合材料组件，涡轮系统和制造工艺。 陶瓷基质复合材料（CMC）组分包括CMC材料，CMC材料上的环境阻隔涂层（EBC）和施加在EBC上的硬磨损涂层。 涡轮机系统包括具有硬磨损涂层的可旋转CMC组件和固定涡轮机部件，固定涡轮机部件具有布置和设置为被碳化硅材料切割的可磨损涂层。 制造过程包括将可旋转的CMC定位成来自固定涡轮机部件的预定距离并旋转可旋转的CMC部件。 可旋转的CMC部件上的硬磨损涂层切割固定涡轮机部件上的可磨损涂层。

    TURBINE SHROUD ASSEMBLY
    10.
    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.

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