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    GAS LIQUID SEPARATOR
    332.
    发明申请
    GAS LIQUID SEPARATOR 审中-公开
    气体液体分离器

    公开(公告)号：US20160175750A1

    公开(公告)日：2016-06-23

    申请号：US14963612

    申请日：2015-12-09

    Applicant: ALSTOM Technology Ltd

    Inventor： Loris PADOVAN

    IPC: B01D45/08

    Abstract: The invention relates to a gas liquid separator, for separating liquid droplets from a gas flowing generally in a main gas flow direction through the gas liquid separator. The gas liquid separator comprises a plurality of plates, mutually parallel and spaced apart to form a flow channel there between. Each plate having a plurality of corrugations wherein at least one of the corrugations has an extrados wing profile shaped camber.

    Abstract translation: 本发明涉及一种气液分离器，用于从通常通过气液分离器的主气流方向流动的气体分离液滴。 气液分离器包括彼此平行并间隔开的多个板，以在其间形成流动通道。 每个板具有多个波纹，其中至少一个波纹具有外形翼型轮廓形状的弧形。

    ROTATING MACHINE
    334.
    发明申请
    ROTATING MACHINE 审中-公开
    旋转机

    公开(公告)号：US20160138410A1

    公开(公告)日：2016-05-19

    申请号：US15007542

    申请日：2016-01-27

    Applicant: ALSTOM TECHNOLOGY LTD

    Inventor： Jaroslaw Leszek SZWEDOWICZ ,  Alexey MOZHAROV ,  Stefan IRMISCH

    IPC: F01D9/02 ,  F01D25/12 ,  F01D17/16

    CPC classification number: F01D9/02 ,  F01D5/08 ,  F01D5/187 ,  F01D17/14 ,  F01D17/16 ,  F01D25/08 ,  F01D25/12 ,  F05D2270/303 ,  F05D2300/505

    Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

    Abstract translation: 由主流和双流引导通过旋转机器的冷却介质冷却的旋转机械包括转子。 定子包括构造成引导二次流以从预旋喷嘴排出的涡流通道。 至少一个控制装置包括设置在预旋喷嘴的区域中的形状记忆合金，并被配置为基于自动化的温度来控制二次流。

    Seal between static turbine parts
    335.
    发明授权
    Seal between static turbine parts 有权
    静态涡轮机部件之间的密封

    公开(公告)号：US09341072B2

    公开(公告)日：2016-05-17

    申请号：US14574803

    申请日：2014-12-18

    Applicant: ALSTOM Technology Ltd

    Inventor： Hariharan Hanumanthan ,  Christos Georgakis

    IPC: F01D11/00 ,  F02C7/28 ,  F16J15/08 ,  F16J3/04

    CPC classification number: F01D11/005 ,  F02C7/28 ,  F05D2240/11 ,  F05D2240/57 ,  F16J3/047 ,  F16J15/0887

    Abstract: The invention relates to a seal between static components of a turbine. The seal includes at least one middle piece, which has at its opposite ends end pieces. The end pieces are arranged in a respective groove of the static components and adjoining the inside surfaces of the grooves. The middle piece has at least two parts. The middle piece parts are rotatably coupled to one another via a pivot. The pivot is an annular ring in cross section formed by at least two cylinder elements being coaxially interfitted and slidable relative to each other. The inner surface of the pivot is wrapped with metallic cloth material. Advantages of the invention are higher flexibility due to the pivoting to accommodate larger relative movements of the turbine components and reduced wear with aging while maintaining good sealing performance.

    Abstract translation: 本发明涉及涡轮静态部件之间的密封。 密封件包括至少一个中间件，其在相对端具有端件。 端片布置在静电部件的相应凹槽中并与凹槽的内表面相邻。 中间部分至少有两部分。 中间件通过枢轴可转动地彼此连接。 枢轴是由至少两个气缸元件形成的横截面的环形环，其相对于彼此同轴地配合和滑动。 枢轴的内表面用金属布材料包裹。 本发明的优点是由于枢转以适应涡轮机部件的较大的相对运动并且通过老化减少的磨损而保持良好的密封性能而具有较高的灵活性。

    DAMPING INLAY FOR TURBINE BLADES
    336.
    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。

    COMBUSTOR ARRANGEMENT FOR A GAS TURBINE
    337.
    发明申请
    COMBUSTOR ARRANGEMENT FOR A GAS TURBINE 审中-公开
    燃气轮机的配气装置

    公开(公告)号：US20160123597A1

    公开(公告)日：2016-05-05

    申请号：US14925527

    申请日：2015-10-28

    Applicant: ALSTOM Technology Ltd

    Inventor： Douglas Anthony PENNELL ,  Urs BENZ ,  Adnan EROGLU ,  Ewald FREITAG ,  Mirko Ruben BOTHIEN ,  Andrea CIANI

    IPC: F23R3/34 ,  F23R3/36

    CPC classification number: F23R3/346 ,  F23C6/042 ,  F23C6/045 ,  F23C6/047 ,  F23C2900/07021 ,  F23D2900/14004 ,  F23R3/06 ,  F23R3/283 ,  F23R3/34 ,  F23R3/36 ,  F23R2900/03341

    Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

    Abstract translation: 用于燃气轮机的燃烧器装置包括第一燃烧器，第一燃烧室，混合器，用于将稀释气体混合到在运行期间离开第一燃烧室的气体;第二燃烧器和第二燃烧室，其依次布置在流体流中 连接。 燃烧器装置的这些元件被排列成一行以形成在第一燃烧室和第二燃烧器之间延伸的流路。 燃烧器装置包括设置在流动路径内并且从第一燃烧器通过第一燃烧室延伸到混合器中并进入第二燃烧器的中心喷枪体，其中喷枪体包括用于为第一燃烧器提供燃料的燃料管道和/或 为第二个燃烧器。

    DEVICE AND METHOD FOR MOUNTING OR DISMANTLING, REPLACEMENT AND MAINTENANCE OF A CAN-COMBUSTOR
    338.
    发明申请
    DEVICE AND METHOD FOR MOUNTING OR DISMANTLING, REPLACEMENT AND MAINTENANCE OF A CAN-COMBUSTOR 审中-公开
    CAN-COMBUSTOR的安装或拆卸，更换和维护的设备和方法

    公开(公告)号：US20160108759A1

    公开(公告)日：2016-04-21

    申请号：US14835991

    申请日：2015-08-26

    Applicant: ALSTOM Technology Ltd

    Inventor： Jost IMFELD ,  Hans-Christian MATHEWS

    IPC: F01D25/28

    CPC classification number: F01D25/285 ,  F05D2230/68 ,  F05D2230/70 ,  F05D2230/80 ,  Y10T29/49318 ,  Y10T29/4932 ,  Y10T29/49346 ,  Y10T29/49718 ,  Y10T29/49721

    Abstract: The present invention concerning of a device for mounting or dismantling, replacement and maintenance of a can-combustor of a gas turbine engine including an assembly tool or assembly tool with additional frame having at least one lifting beam, at least one linear driver, wheels, at least one eccentric rolling hook for fixation of the gas turbine housing, optionally spacers for building the interface to the can-combustor, adapters, lifting points for the main crane. The eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing.

    Abstract translation: 本发明涉及一种用于安装或拆卸，更换和维护燃气涡轮发动机的罐式燃烧器的装置，其包括具有至少一个提升梁的附加框架的组装工具或组装工具，至少一个线性驱动器， 用于固定燃气轮机壳体的至少一个偏心滚动钩，用于建立与罐式燃烧器的接口的可选间隔件，适配器，用于主起重机的提升点。 偏心滚动钩通过在轴向或准轴向方向上连接到燃气轮机壳体上，用于将燃气轮机壳体上的罐式燃烧器安装或拆卸。

    Static vane assembly for an axial flow turbine
    339.
    发明授权
    Static vane assembly for an axial flow turbine 有权
    用于轴流式涡轮机的静叶片组件

    公开(公告)号：US09316107B2

    公开(公告)日：2016-04-19

    申请号：US13937635

    申请日：2013-07-09

    Applicant: ALSTOM Technology Ltd

    Inventor： Benjamin Megerle ,  Ivan William McBean ,  Timothy Stephen Rice ,  Said Havakechian

    IPC: F01D9/02 ,  F01D9/04 ,  F01D5/14

    CPC classification number: F01D9/041 ,  F01D5/142 ,  F05D2220/31 ,  F05D2220/3215 ,  F05D2240/122 ,  F05D2260/961

    Abstract: An axial flow turbine is described having a casing defining a flow path for a working fluid therein, a rotor co-axial to the casing, a plurality of stages, each including a stationary row of vanes circumferentially mounted on the casing a rotating row blades, circumferentially mounted on the rotor, with within a stage n vanes have an extension such that at least a part of the trailing edge of each of the n vanes reaches into the annular space defined by the trailing edges of the remaining N-n vanes and the leading edges of rotating blades of the same stage.

    Abstract translation: 描述了一种轴流涡轮机，其具有限定其中的工作流体的流动路径的壳体，与壳体同轴的转子，多个级，每个级包括周向地安装在壳体上的旋转行叶片的静止叶片， 周向地安装在转子上，在一个阶段中，n个叶片具有延伸部，使得每个n个叶片的后缘的至少一部分到达由剩余的Nn叶片的后缘限定的环形空间中，并且前缘 的相同阶段的旋转叶片。

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