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    GAS TURBINE AND TURBINE BLADE FOR SUCH A GAS TURBINE
    1.
    发明申请
    GAS TURBINE AND TURBINE BLADE FOR SUCH A GAS TURBINE 有权
    气体涡轮机和涡轮叶片用于这种气体涡轮机

    公开(公告)号：US20140112798A1

    公开(公告)日：2014-04-24

    申请号：US14061018

    申请日：2013-10-23

    Applicant: ALSTOM Technology Ltd

    Inventor： Sascha JUSTL ,  Carlos SIMON-DELGADO ,  Thomas ZIERER ,  Sven OLMES

    IPC: F01D5/08

    CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/187 ,  F05B2240/801

    Abstract: A gas turbine includes a rotor concentrically surrounded by a casing, with an annular hot gas channel axially extending between the rotor and the casing. The rotor is equipped with a plurality of blades, which are arranged on the rotor in an annular fashion. Each of the blades is mounted with a root in a respective axial slot on a rim of the rotor radially extending with an airfoil into said hot gas channel and adjoining with an axially oriented root surface to an annular rim cavity. Cooling means are provided at the root of each of said blades to receive cooling air being injected into said rim cavity through stationary injecting means. An optimized cooling is achieved by providing the root surface to be an essentially plane surface and the cooling means including a scoop for capturing and redirecting at least part of the injected cooling air, which scoop is designed as a recess with respect to the root surface.

    Abstract translation: 燃气轮机包括同轴地由壳体包围的转子，其中环形热气通道在转子和壳体之间轴向延伸。 转子配备有多个叶片，其以环形的方式布置在转子上。 每个叶片安装有根部，位于转子边缘上的相应轴向槽中，其径向延伸，翼型进入所述热气通道并与轴向定向的根表面邻接到环形边缘空腔。 冷却装置设置在每个所述叶片的根部处以接收通过静态喷射装置注入到所述边缘空腔中的冷却空气。 通过将根表面设置为基本上平面的表面来实现优化的冷却，并且冷却装置包括用于捕获和重定向至少部分喷射的冷却空气的铲斗，该铲斗被设计为相对于根表面的凹部。

    FLUID SEAL ARRANGEMENT AND METHOD FOR CONSTRICTING A LEAKAGE FLOW THROUGH A LEAKAGE GAP
    3.
    发明申请
    FLUID SEAL ARRANGEMENT AND METHOD FOR CONSTRICTING A LEAKAGE FLOW THROUGH A LEAKAGE GAP 审中-公开
    流体密封装置和通过泄漏漏气约束泄漏流量的方法

    公开(公告)号：US20150050125A1

    公开(公告)日：2015-02-19

    申请号：US14341264

    申请日：2014-07-25

    Applicant: ALSTOM Technology Ltd

    Inventor： Carlos SIMON-DELGADO ,  Vasileios STEFANIS ,  Sergey SHCHUKIN ,  Joerg KRUECKELS

    IPC: F01D11/10 ,  F16J15/40

    CPC classification number: F01D11/10 ,  F16J15/162 ,  F16J15/40 ,  F16J15/444 ,  F16J15/4472

    Abstract: The invention refers to a fluid seal arrangement for constricting a leakage flow directed through a leakage gap bordered by a rotational and a stationary component including at least one nozzle opening in the rotating and/or stationary component facing towards the rotating or stationary component of an opposite side of the leakage gap respectively in order for injecting a liquid or gaseous fluid flow through the nozzle opening into the leakage gap. The at least one nozzle opening is fluidly connected to a cooling channel inside said rotating and/or stationary component, so that said fluid flow emanating at the nozzle opening consists of a cooling fluid of the rotating and/or stationary component exclusively.

    Abstract translation: 本发明涉及一种流体密封装置，用于限制通过由旋转和静止部件界定的泄漏间隙的泄漏流动，所述泄漏间隙包括旋转和/或固定部件中的至少一个喷嘴开口，所述喷嘴开口面向相对的旋转部件或固定部件 以便将液体或气体流体流经喷嘴开口注入到泄漏间隙中。 至少一个喷嘴开口流体地连接到所述旋转和/或固定部件内的冷却通道，使得在喷嘴开口处发出的所述流体流由仅旋转和/或静止部件的冷却流体组成。

    TURBINE BLADE AND TURBINE WITH IMPROVED SEALING
    4.
    发明申请
    TURBINE BLADE AND TURBINE WITH IMPROVED SEALING 有权
    涡轮叶片和涡轮改进密封

    公开(公告)号：US20150037167A1

    公开(公告)日：2015-02-05

    申请号：US14336152

    申请日：2014-07-21

    Applicant: ALSTOM Technology Ltd

    Inventor： Carlos SIMON-DELGADO ,  Christoph Didion ,  Stefan Biedermann ,  Beat Von Arx ,  Thomas Zierer

    IPC: F01D25/12 ,  F01D5/14

    CPC classification number: F01D25/12 ,  F01D5/081 ,  F01D5/142 ,  F01D5/147 ,  F01D11/001 ,  F01D11/005 ,  F05D2260/941

    Abstract: The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.

    Abstract translation: 本发明涉及具有燃气轮机叶片和转子隔热罩的涡轮机，用于分离热工作介质从涡轮机的转子装置内部的空间区域流过的空间区域。 转子隔热罩包括形成轴向隔热部分的平台，该平台基本上平行于转子的表面布置，并且在轴向隔热部分的上游端处具有径向隔热部分，该部分沿远离方向延伸 从轴向隔热部分的表面朝向热气体。 此外，涡轮机包括叶片后腔，其由平台的下游端和/或叶片脚的下游端限定，即径向隔热部分。 本发明进一步涉及为这种涡轮机设计的燃气轮机叶片和转子隔热罩。

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