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    Turbine vane airfoil reconfiguration method
    1.
    发明授权
    Turbine vane airfoil reconfiguration method 失效
    涡轮叶片翼型重构方法

    公开(公告)号：US07730756B2

    公开(公告)日：2010-06-08

    申请号：US12372168

    申请日：2009-02-17

    申请人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

    发明人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

    IPC分类号： B21D53/78 ,  B21D3/16 ,  B23P6/00

    CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

    摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

    摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

    TURBINE VANE AIRFOIL RECONFIGURATION METHOD
    2.
    发明申请
    TURBINE VANE AIRFOIL RECONFIGURATION METHOD 失效
    涡轮风力发电机重构方法

    公开(公告)号：US20090260206A1

    公开(公告)日：2009-10-22

    申请号：US12372168

    申请日：2009-02-17

    申请人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

    发明人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

    IPC分类号： B23P6/00

    CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

    摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

    摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

    Turbine vane airfoil reconfiguration method
    3.
    发明授权
    Turbine vane airfoil reconfiguration method 有权
    涡轮叶片翼型重构方法

    公开(公告)号：US07536783B2

    公开(公告)日：2009-05-26

    申请号：US11591908

    申请日：2006-11-02

    申请人： Jefferson Davis ,  Martin C. Gosling ,  Yong Kang

    发明人： Jefferson Davis ,  Martin C. Gosling ,  Yong Kang

    IPC分类号： B21D53/78 ,  B23P6/00

    CPC分类号： F01D5/005 ,  B23P6/002 ,  F05D2230/80 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/4932 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49721

    摘要： A method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the method may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by heating the airfoil to no more than 750 degrees F. while applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. The load is up to 6000 lbf. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

    摘要翻译： 一种用于重新配置涡轮叶片段的翼型的方法。 在至少一个实施例中，该方法可以用于矫直涡轮叶片段的翼型以去除倾斜，扭转或翻倒，或其任何组合。 通过将翼型件加热至不超过750华氏度，同时在与涡轮叶片段的外护罩大致相切的方向上向内护罩施加负载的情况下，翼型件可被矫直。 负载高达6000 lbf。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

    Turbine vane airfoil reconfiguration system
    4.
    发明授权
    Turbine vane airfoil reconfiguration system 有权
    涡轮叶片翼型重构系统

    公开(公告)号：US07503113B2

    公开(公告)日：2009-03-17

    申请号：US11249791

    申请日：2005-10-13

    申请人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

    发明人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

    IPC分类号： B21D53/78

    CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

    摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

    摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

    Lubricant sealing means for a compressor shaft
    7.
    发明授权
    Lubricant sealing means for a compressor shaft 失效
    用于压缩机轴的润滑剂密封装置

    公开(公告)号：US4183714A

    公开(公告)日：1980-01-15

    申请号：US851351

    申请日：1977-11-14

    申请人： Martin C. Gosling

    发明人： Martin C. Gosling

    IPC分类号： F04D29/10 ,  F04D29/08

    CPC分类号： F04D29/104

    摘要： A compressor comprises one or more stages each including an impeller mounted for rotation on a shaft and rotatable in an impeller housing. A transmission is drivingly connected to the shaft and a bearing is provided supporting the shaft. Lubrication means are provided for the bearing which provide a continuous lubricant seal around the shaft between the shaft and the bearing to prevent air leaking through the bearing. A chamber is located between the impeller housing and the bearing for collecting excess lubricant and has an outlet for draining lubricant.

    摘要翻译： 压缩机包括一个或多个阶段，每个阶段包括叶轮，叶轮安装成可在轴上旋转并可在叶轮壳体中旋转。 变速器驱动地连接到轴，并且设置支撑轴的轴承。 为轴承提供润滑装置，其在轴和轴承之间围绕轴提供连续的润滑剂密封，以防止空气通过轴承泄漏。 腔室位于叶轮壳体和轴承之间，用于收集多余的润滑剂，并具有用于排出润滑剂的出口。