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    Method for evaluating compressor stall/surge margin requirements
    1.
    发明授权
    Method for evaluating compressor stall/surge margin requirements 有权

    公开(公告)号：US06574584B2

    公开(公告)日：2003-06-03

    申请号：US09732811

    申请日：2000-12-11

    申请人： Chung-Hei Yeung ,  Joseph Anthony Cotroneo ,  John David Stampfli

    发明人： Chung-Hei Yeung ,  Joseph Anthony Cotroneo ,  John David Stampfli

    IPC分类号： G06F1500

    CPC分类号： F04D27/02

    摘要： A method is provided for evaluating stall/surge margin of a machine of interest. The method includes identifying a vital factor where each the vital factors corresponds to operation of the machine of interest. Raw data relating to the vital factor is provided. A contribution of the vital factor to the stall/surge margin is determined from at least the provided raw data. The contribution of the vital factor to the stall/surge margin is statistically analyzed. A stall/surge margin is allocated based on the statistical analysis of the contribution of the vital factor. An operating limit line is defined based on the allocation of the stall/surge margin.

    EXHAUST DIFFUSER FOR TURBINE
    5.
    发明申请
    EXHAUST DIFFUSER FOR TURBINE 审中-公开
    用于涡轮的排气歧管

    公开(公告)号：US20130243564A1

    公开(公告)日：2013-09-19

    申请号：US13419860

    申请日：2012-03-14

    申请人： Prakash Bavanjibhai Dalsania ,  Joseph Anthony Cotroneo ,  Sudhakar Neeli

    发明人： Prakash Bavanjibhai Dalsania ,  Joseph Anthony Cotroneo ,  Sudhakar Neeli

    IPC分类号： F01D1/00 ,  F01D25/00

    CPC分类号： F01D25/30 ,  F01D5/143 ,  F01D5/225 ,  F01D9/02

    摘要： An exhaust diffuser for a turbine includes an inlet configured to receive exhaust gas from a last stage bucket of the turbine and an exhaust gas guide surface configured to guide the exhaust gas. A curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70. A method of diffusing exhaust of a turbine includes energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine.

    摘要翻译： 用于涡轮机的排气扩散器包括被配置为接收来自涡轮机的最后级别的排气的入口和被构造成引导废气的废气引导表面的入口。 引导表面的曲率包括相对于涡轮机的轴线的第一角度和引导表面轴向长度与最后一级铲斗的有效长度的比率在约0.45至0.70之间。 一种扩散涡轮机排气的方法包括沿着涡轮机的最后一级铲斗的尖端泄漏使排气扩散器的弯曲排气流引导表面激励边界层。

    TURBOMACHINE HAVING CLEARANCE CONTROL CAPABILITY AND SYSTEM THEREFOR
    6.
    发明申请
    TURBOMACHINE HAVING CLEARANCE CONTROL CAPABILITY AND SYSTEM THEREFOR 审中-公开
    具有间隙控制能力和系统的涡轮机

    公开(公告)号：US20130315716A1

    公开(公告)日：2013-11-28

    申请号：US13477839

    申请日：2012-05-22

    申请人： Joseph Anthony Cotroneo

    发明人： Joseph Anthony Cotroneo

    IPC分类号： F01D7/00

    CPC分类号： F01D11/22 ,  F05D2230/644

    摘要： A turbomachine having clearance control capability is provided and includes a turbine stage including a blade configured to rotate around a centerline, a movable portion of a casing circumferentially surrounding the turbine stage and a rotatable cam operably coupled to the movable portion and thereby configured to control an axial position of the movable portion. A radially outermost tip of the blade and an interior surface of the movable portion are sloped with respect to the centerline such that the controlled axial position of the movable portion is determinative of a clearance between the blade and the movable portion.

    摘要翻译： 提供了具有间隙控制能力的涡轮机，并且包括涡轮级，其包括构造成围绕中心线旋转的叶片，周向围绕涡轮级的壳体的可动部分以及可操作地联接到可移动部分的旋转凸轮，从而构造成控制 可动部的轴向位置。 叶片的径向最外端和可动部分的内表面相对于中心线倾斜，使得可动部分的受控轴向位置决定于叶片与可动部分之间的间隙。

    TURBOMACHINE BLADE TIP SHROUD WITH PARALLEL CASING CONFIGURATION
    7.
    发明申请
    TURBOMACHINE BLADE TIP SHROUD WITH PARALLEL CASING CONFIGURATION 有权
    TURBOMACHINE BLADE TIP SHROUD具有平行的壳体配置

    公开(公告)号：US20130272888A1

    公开(公告)日：2013-10-17

    申请号：US13447134

    申请日：2012-04-13

    申请人： Rohit Chouhan ,  Sylvain Pierre ,  Gunnar Leif Siden ,  Santhosh Kumar Vijayan ,  Joseph Anthony Cotroneo

    发明人： Rohit Chouhan ,  Sylvain Pierre ,  Gunnar Leif Siden ,  Santhosh Kumar Vijayan ,  Joseph Anthony Cotroneo

    IPC分类号： F04D29/38

    CPC分类号： F01D5/225 ,  F01D11/08 ,  F05D2250/312

    摘要： Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.

    摘要翻译： 本公开的实施例包括具有涡轮机叶片和固定结构部件的涡轮机。 涡轮机叶片包括具有前缘部分的前端部分，其中前缘部分具有第一表面。 固定结构部件围绕涡轮机叶片设置并且包括对应于尖端护罩的前缘部分的对应部分，其中对应部分具有第二表面，其中第一表面和第二表面具有大致平行的轮廓。