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    DAMPING INLAY FOR TURBINE BLADES
    2.
    发明申请
    DAMPING INLAY FOR TURBINE BLADES 审中-公开
    用于涡轮叶片的阻尼内衬

    公开(公告)号：US20160130953A1

    公开(公告)日：2016-05-12

    申请号：US14932313

    申请日：2015-11-04

    Applicant: ALSTOM Technology Ltd

    Inventor： Herbert BRANDL ,  Arrigo BERETTA-MÜLLER

    IPC: F01D5/26 ,  F01D5/14 ,  F01D5/18

    CPC classification number: F01D5/26 ,  F01D5/147 ,  F01D5/16 ,  F01D5/186 ,  F05D2220/30 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/232 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2230/25 ,  F05D2230/30 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2260/96

    Abstract: The invention concerns a turbine blade comprising a surface, a recess within the surface, and a damping inlay within the recess. The damping inlay comprises a chamber with a damping material, for example particles. The damping inlay should substantially maintain the aerodynamic profile of the blade to enable normal operation. A further embodiment of the invention describes the method of manufacture of a turbine blade with a damping inlay. The method comprises the steps of manufacturing a turbine blade having a surface and a recess in the surface, and providing one or more damping inlays within the recess such that the damping inlay substantially maintains the aerodynamic profile of the blade, the damping inlay comprising a chamber and a damping material disposed within the chamber.

    Abstract translation: 本发明涉及一种涡轮机叶片，其包括表面，表面内的凹部和凹部内的阻尼嵌体。 阻尼嵌体包括具有阻尼材料的室，例如颗粒。 阻尼嵌体应基本上保持叶片的空气动力学特性以使其能够正常运行。 本发明的另一实施例描述了具有阻尼嵌体的涡轮叶片的制造方法。 该方法包括以下步骤：制造具有在表面中的表面和凹部的涡轮叶片，并且在凹槽内提供一个或多个阻尼嵌体，使得阻尼嵌体基本上保持叶片的空气动力学特性，阻尼嵌体包括腔室 以及设置在所述腔室内的阻尼材料。

    TURBINE BLADE OR VANE
    3.
    发明申请
    TURBINE BLADE OR VANE 有权
    涡轮叶片或风扇

    公开(公告)号：US20150017007A1

    公开(公告)日：2015-01-15

    申请号：US14499386

    申请日：2014-09-29

    Applicant: ALSTOM Technology Ltd

    Inventor： Herbert BRANDL

    IPC: F01D5/22

    CPC classification number: F01D5/22 ,  F01D5/147 ,  F01D5/3007 ,  F01D5/326 ,  F01D11/008 ,  F05B2240/57 ,  F05D2230/50 ,  F05D2230/51 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/36 ,  F05D2260/96

    Abstract: The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state.

    Abstract translation: 本发明涉及一种涡轮叶片，其包括具有前边缘和后边缘的叶片，该叶片借助于轴转变成设计成用于紧固涡轮叶片的叶根，并且包括布置在下部的平台 以便结合流动通道。 该平台设计为单独的部件，并且可以以适合形式的方式连接到刀片。 实现灵活的应用是，平台由几个单独的平台元件组成，其将叶片包围在组装状态。

    ARRANGEMENT FOR COOLING A COMPONENT IN THE HOT GAS PATH OF A GAS TURBINE
    4.
    发明申请
    ARRANGEMENT FOR COOLING A COMPONENT IN THE HOT GAS PATH OF A GAS TURBINE 有权
    在气体涡轮机的热气道中冷却组分的装置

    公开(公告)号：US20150110612A1

    公开(公告)日：2015-04-23

    申请号：US14505588

    申请日：2014-10-03

    Applicant: ALSTOM Technology Ltd

    Inventor： Herbert BRANDL ,  Andrey Anatolievich SEDLOV ,  Artem IVANOV

    IPC: F01D9/06 ,  F01D25/14

    CPC classification number: F01D9/065 ,  F01D9/06 ,  F01D11/08 ,  F01D25/14 ,  F05D2240/11 ,  F05D2240/15

    Abstract: The invention relates to a cooled wall segment in the hot gas path of a gas turbine, particularly to a cooled stator heat shield. Such components have to be properly cooled in order to avoid thermal damages of these components and to ensure a sufficient lifetime. The wall segment according to the invention includes a first surface, exposed to a medium of relatively high temperature, a second surface, exposed to a medium of relatively low temperature, and side surfaces connecting said first and said second surface and defining a height of the wall segment. At least one cooling channel for a flow-through of a fluid cooling medium extends through the wall segment. Each cooling channel is provided with an inlet for the cooling medium and an outlet for the cooling medium. The at least one cooling channel includes at least two heat transfer sections, a first (in the direction of flow of the cooling medium) heat transfer section extending essentially parallel to the surface of relatively high temperature in a first distance and a second heat transfer section extending essentially parallel to the surface of relatively high temperature in a second distance, whereby the second distance is lower than the first distance.

    Abstract translation: 本发明涉及一种在燃气轮机的热气路径中的冷却壁段，特别涉及一种冷却的定子隔热罩。 这些组件必须被适当地冷却，以避免这些部件的热损伤并确保足够的寿命。 根据本发明的壁段包括暴露于较高温度的介质的第一表面，暴露于较低温度的介质的第二表面和连接所述第一和所述第二表面的侧表面，并限定 墙段。 用于流体冷却介质的流过的至少一个冷却通道延伸穿过壁段。 每个冷却通道设置有用于冷却介质的入口和用于冷却介质的出口。 所述至少一个冷却通道包括至少两个传热部分，第一传热部分（在冷却介质的流动方向上）传热部分基本上平行于第一距离的较高温度的表面延伸，第二传热部分 基本平行于第二距离的较高温度的表面延伸，由此第二距离低于第一距离。

    STATOR COMPONENT WITH SEGMENTED INNER RING FOR A TURBOMACHINE
    6.
    发明申请
    STATOR COMPONENT WITH SEGMENTED INNER RING FOR A TURBOMACHINE 有权
    用于涡轮发动机的定期内环

    公开(公告)号：US20140328672A1

    公开(公告)日：2014-11-06

    申请号：US14335203

    申请日：2014-07-18

    Applicant: ALSTOM Technology Ltd

    Inventor： Herbert BRANDL ,  Hans-Peter BOSSMANN

    IPC: F01D11/18 ,  F01D11/12

    CPC classification number: F01D11/18 ,  F01D9/04 ,  F01D11/08 ,  F01D11/122 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2300/20 ,  F05D2300/21 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/50212

    Abstract: A stator component of a turbomachine is composed substantially of at least one axially extending outer ring (10) which serves as a frame of an inner ring composed of partial segments (20). The partial segments are arranged on one another such that, on the rotor side, they form a coherent circular circumferential surface in relation to the rotational movement of rotor blades (30). The individual partial segment (20) is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behaviour as a function of the load ranges of the turbomachine.

    Abstract translation: 涡轮机的定子部件基本上由至少一个轴向延伸的外环（10）组成，其用作由部分段（20）构成的内环的框架。 部分片段彼此布置，使得在转子侧，它们相对于转子叶片（30）的旋转运动形成相干的圆周表面。 单个部分段（20）由均匀构造的材料或至少在径向方向上由由不同材料（例如陶瓷）构成的多个部分体构成，其中如此形成的部分段呈现预定的应力和/ 或膨胀行为作为涡轮机的负载范围的函数。

    MODULAR BLADE OR VANE FOR A GAS TURBINE AND GAS TURBINE WITH SUCH A BLADE OR VANE
    7.
    发明申请
    MODULAR BLADE OR VANE FOR A GAS TURBINE AND GAS TURBINE WITH SUCH A BLADE OR VANE 审中-公开
    用于气体涡轮机的模块式叶片或叶片和具有这种叶片或叶片的气体涡轮机

    公开(公告)号：US20140234088A1

    公开(公告)日：2014-08-21

    申请号：US14012101

    申请日：2013-08-28

    Applicant: ALSTOM TECHNOLOGY LTD

    Inventor： Herbert BRANDL

    IPC: F01D5/08 ,  F01D9/02 ,  F01D5/30

    CPC classification number: F01D5/081 ,  F01D5/147 ,  F01D5/186 ,  F01D5/189 ,  F01D5/30 ,  F01D9/02 ,  F05D2230/51 ,  F05D2240/10 ,  F05D2240/20 ,  F05D2240/80 ,  Y02T50/673 ,  Y02T50/676

    Abstract: The invention relates to a modular blade or vane for a gas turbine, which includes the modular components of a platform element with a planar or contoured surface defining a platform level and a through-opening therein, and an airfoil, extending through the platform element. The airfoil includes a load carrying structure extending along a longitudinal axis of the airfoil, having a root portion for fastening on a blade or vane carrier of the gas turbine, having a tip portion, and having at least one interior passage, extending from the root portion to the tip portion of the airfoil. An aerodynamically shaped shell extends in a distance over the carrying structure and defining the outer contour of the airfoil. A longitudinally extending gap, is disposed between the carrying structure and the shell. A number of through-holes in the carrying structure direct a cooling medium from the interior passage into the gap. The shell is integrally joined to said carrying structure by a first joint in a region below the platform level of the platform element. The shell is joined to the carrying structure by at least one additional joint, wherein said at least one additional joint is a form-fit joint, allowing relative movement in longitudinal direction between shell and carrying structure.

    Abstract translation: 本发明涉及一种用于燃气轮机的模块化叶片或叶片，其包括平台元件的模块化部件，平台元件具有限定平台高度的平面或轮廓表面和其中的通孔，以及延伸穿过平台元件的翼型件。 翼型件包括沿着翼型件的纵向轴线延伸的载重结构，具有用于紧固在燃气涡轮机的叶片或叶片载体上的根部，具有尖端部分，并且具有至少一个内部通道，从根部延伸出来 部分到翼型的末端部分。 空气动力学形状的壳在承载结构上延伸一定距离，并且限定翼型的外轮廓。 纵向延伸的间隙设置在承载结构和外壳之间。 承载结构中的多个通孔将冷却介质从内部通道引导到间隙中。 壳体通过平台元件的平台平台下方的区域中的第一接头与所述承载结构一体地接合。 壳体通过至少一个附加接头连接到承载结构，其中所述至少一个附加接头是成形配合接头，允许在壳体和承载结构之间的纵向方向上的相对运动。

    ROTOR BLADE ARRANGEMENT AND GAS TURBINE
    9.
    发明申请
    ROTOR BLADE ARRANGEMENT AND GAS TURBINE 有权
    转子叶片布置和气体涡轮机

    公开(公告)号：US20150098831A1

    公开(公告)日：2015-04-09

    申请号：US14568706

    申请日：2014-12-12

    Applicant: ALSTOM Technology Ltd

    Inventor： Herbert BRANDL ,  Hans-Peter BOSSMANN ,  Philipp INDLEKOFER

    IPC: F01D5/30 ,  F01D9/04

    CPC classification number: F01D5/303 ,  F01D5/147 ,  F01D5/3007 ,  F01D5/3092 ,  F01D9/04 ,  F01D11/008 ,  F05D2240/30 ,  F05D2260/36

    Abstract: A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).

    Abstract translation: 一种特别用于燃气轮机的转子叶片装置（20），其可以紧固在叶片载体（19）上并且在每种情况下包括叶片翼型件（10）和平台元件（14），其中平台元件 叶片排形成一个连续的内护罩。 利用这种叶片装置，延长使用寿命的机械解耦通过叶片机翼元件（10）和平台元件（14）形成为分离的元件并且能够在每种情况下分开地固定在 叶片载体（19）。

    LIGHT WEIGHT SHROUD FIN FOR A ROTOR BLADE
    10.
    发明申请
    LIGHT WEIGHT SHROUD FIN FOR A ROTOR BLADE 有权
    旋转叶片的轻重量

    公开(公告)号：US20130058788A1

    公开(公告)日：2013-03-07

    申请号：US13668136

    申请日：2012-11-02

    Applicant: Alstom Technology Ltd

    Inventor： Herbert BRANDL ,  Igor TSYPKAKYIN ,  Philipp INDLEKOFER

    IPC: F01D5/08 ,  B23P15/02 ,  F01D5/02

    CPC classification number: F01D5/225 ,  F01D5/187 ,  Y10T29/49341

    Abstract: A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.

    Abstract translation: 涡轮机叶片被设置并且包括承载护罩的末端和至少一个翅片，其从护罩径向延伸。 翅片包括第一侧壁和第二侧壁，第一侧壁和第二侧壁间隔开，彼此平行设置并且连接到护罩，以及连接到第一和第二侧壁的切割边缘。 因此，切割边缘在侧壁，护罩和切割边缘之间形成中空空间，并进一步从第一和第二侧壁径向延伸。 还提供了通过将叶片与中空翅片一体铸造或通过锻造叶片来制造叶片的方法; 并且加工翅片以产生第一和第二侧壁和切割刃，从而打开所述侧壁和切割边缘之间的中空空间。

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