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    ROTOR SHAFT WITH COOLING BORE INLETS
    1.
    发明申请
    ROTOR SHAFT WITH COOLING BORE INLETS 审中-公开
    带冷却孔的转子轴

    公开(公告)号：US20150267542A1

    公开(公告)日：2015-09-24

    申请号：US14661220

    申请日：2015-03-18

    Applicant: ALSTOM Technology Ltd.

    Inventor： Steffen Holzhaeuser ,  Carlos Simon-Delgado ,  Carl Berger

    IPC: F01D5/18 ,  F01D25/12 ,  F01D5/02

    CPC classification number: F01D5/18 ,  F01D5/02 ,  F01D5/063 ,  F01D5/087 ,  F01D25/12 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2240/60 ,  F05D2260/232 ,  F05D2260/941

    Abstract: The invention relates to a rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically or quasi-concentrically to the rotor axis inside the rotor shaft, and a plurality of cooling bores extending radially or quasi-radially outward from the inside to an outside of the rotor shaft. Each cooling bore having a bore inlet location and a distal bore outlet portion, the respective bore inlet location being adapted to abut on the rotor cavity. At least one side or part-side of the cooling bore inlet location is provided with an asymmetric edge fillet in order to maximize the wall thickness between two adjacent cooling bores.

    Abstract translation: 本发明涉及适于围绕其转子轴线旋转的转子轴。 转子轴包括与转子轴内的转子轴同心或准同心配置的转子腔，以及从转子轴的内侧向外径向或半径向外延伸的多个冷却孔。 每个冷却孔具有孔入口位置和远端孔出口部分，相应的孔入口位置适于邻接转子腔。 冷却孔入口位置的至少一侧或部分侧设置有不对称边缘，以使两个相邻冷却孔之间的壁厚最大化。

    Labyrinth seal
    2.
    发明授权
    Labyrinth seal 有权

    公开(公告)号：US09650907B2

    公开(公告)日：2017-05-16

    申请号：US14202571

    申请日：2014-03-10

    Applicant: ALSTOM Technology Ltd

    Inventor： Cyrille Bricaud ,  Ulrich Robert Steiger ,  Axel Heidecke ,  Carlos Simon-Delgado

    IPC: F01D11/02 ,  F16J15/44 ,  F16J15/447

    CPC classification number: F01D11/02 ,  F01D11/025 ,  F05D2300/50212 ,  F16J15/445 ,  F16J15/4472

    Abstract: A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition.

    SEAL SYSTEM FOR A GAS TURBINE
    3.
    发明申请
    SEAL SYSTEM FOR A GAS TURBINE 有权
    气体涡轮密封系统

    公开(公告)号：US20150176424A1

    公开(公告)日：2015-06-25

    申请号：US14574846

    申请日：2014-12-18

    Applicant: ALSTOM Technology Ltd.

    Inventor： Carlos Simon-Delgado ,  Christoph Didion ,  Marc Widmer ,  Martin Schaefer ,  Guenter Filkorn

    IPC: F01D11/18 ,  F01D11/12 ,  F01D11/02

    CPC classification number: F01D11/18 ,  F01D11/001 ,  F01D11/025 ,  F01D11/122 ,  F01D11/127 ,  F05D2250/283

    Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.

    Abstract translation: 本发明涉及一种用于在涡轮机定子和涡轮机转子之间的通道的密封系统，包括：第一臂从涡轮转子径向向外延伸并且朝向布置在定子上的第一密封件延伸，并且终止于第一密封件之外，从而产生 第一密封件和第一臂之间的第一间隙。 所述密封系统还包括布置在所述涡轮机定子上的第二密封件，以及从所述涡轮机转子朝向所述第二密封基座轴向延伸并且终止于所述第二密封件的第二臂，从而在所述第二密封件和所述第二臂之间形成第二间隙 。 本发明还涉及一种包括这种密封系统的燃气轮机。

    LABYRINTH SEAL
    4.
    发明申请
    LABYRINTH SEAL 有权

    公开(公告)号：US20140191476A1

    公开(公告)日：2014-07-10

    申请号：US14202571

    申请日：2014-03-10

    Applicant: ALSTOM Technology Ltd.

    Inventor： Cyrille Bricaud ,  Ulrich Robert Steiger ,  Axel Heidecke ,  Carlos Simon-Delgado

    IPC: F01D11/02

    CPC classification number: F01D11/02 ,  F01D11/025 ,  F05D2300/50212 ,  F16J15/445 ,  F16J15/4472

    Abstract: A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition.

    Abstract translation: 提供迷宫式密封件用于密封汽轮机或燃气轮机的转子和定子之间的环形间隙。 迷宫式密封件包括多个密封条，其沿轴向串联设置并固定在定子上并投入到间隙中。 密封条与密封效应相互作用，转子侧密封元件以交错方式布置。 通过在冷安装状态下的密封条相对于对称位置偏移来实现改进的密封效果，其中所述偏移具有与密封条相对于相邻转子相对位移的距离相反的方向和相同的量， 由于固定和旋转的部件和支撑结构在从冷的安装状态被加热到热的稳态操作状态时的热膨胀的结果导致侧面密封元件。

    Gas turbine and turbine blade for such a gas turbine
    6.
    发明授权
    Gas turbine and turbine blade for such a gas turbine 有权
    用于这种燃气轮机的燃气轮机和涡轮叶片

    公开(公告)号：US09482094B2

    公开(公告)日：2016-11-01

    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 ,  F01D5/18

    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 includes a plurality of blades arranged annularly on the rotor. 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 the hot gas channel and adjoining with an axially oriented root surface to an annular rim cavity. A cooling device is provided at the root of each blade to receive cooling air injected into the rim cavity through stationary injectors. An optimized cooling is achieved by providing an essentially plane root surface and the cooling device includes a scoop for capturing and redirecting at least part of the injected cooling air, which scoop is 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。 转子包括环形地设置在转子上的多个叶片。 每个叶片安装有一个根部，位于转子边缘上的相应的轴向槽中，其径向延伸，翼型进入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叶片的根部处以接收通过固定喷射器注入到轮辋腔中的冷却空气。 通过提供基本上平面的根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，该铲斗是相对于根表面的凹部。

    METHOD AND COOLING SYSTEM FOR COOLING BLADES OF AT LEAST ONE BLADE ROW IN A ROTARY FLOW MACHINE
    9.
    发明申请
    METHOD AND COOLING SYSTEM FOR COOLING BLADES OF AT LEAST ONE BLADE ROW IN A ROTARY FLOW MACHINE 有权
    用于冷却旋转流动机中的一个叶片的叶片的方法和冷却系统

    公开(公告)号：US20140086743A1

    公开(公告)日：2014-03-27

    申请号：US14031660

    申请日：2013-09-19

    Applicant: ALSTOM Technology Ltd

    Inventor： Sascha JUSTL ,  Carlos Simon-Delgado ,  Axel Heidecke ,  Sven Olmes

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/08 ,  F01D5/187 ,  F01D5/225 ,  F01D11/10

    Abstract: A method and a cooling system for cooling blades of at least one blade row in a rotary flow machine includes an axial flow channel which is radially limited on the inside by a rotor unit and at the outside by at least one stationary component, the blades are arranged at the rotary unit and provide a shrouded blade tip facing radially to said stationary component. Pressurized cooling air is fed through from radially outside towards the tip of each of said blades in the at least one blade row, and the pressurized cooling air enters the blades through at least one opening at the shrouded blades' tip.

    Abstract translation: 用于在旋转流动机械中至少一个叶片排的叶片的冷却方法和冷却系统包括轴向流动通道，该轴向流动通道由转子单元在内部径向限制，并且在外部由至少一个固定部件限定，叶片是 布置在所述旋转单元处并且提供面向所述静止部件的径向的被覆盖的叶片尖端。 加压冷却空气从至少一个叶片排中的径向外侧向每个所述叶片的顶端供给，并且加压冷却空气通过所覆盖的叶片尖端处的至少一个开口进入叶片。

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