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    Turbine blade
    2.
    发明专利
    Turbine blade 有权
    涡轮叶片

    公开(公告)号：JP2008031985A

    公开(公告)日：2008-02-14

    申请号：JP2007140112

    申请日：2007-05-28

    Applicant: Siemens Ag ,  シーメンス アクチエンゲゼルシヤフトSiemens Aktiengesellschaft

    Inventor： BERGANDER KATHARINA ,  BOSTANJOGLO GEORG ,  BUCHAL TOBIAS ,  ESSER WINFRIED ,  GOLDSCHMIDT DIRK ,  KOCH THORSTEN ,  KUEPERKOCH RUDOLF ,  MATTHEIS THORSTEN ,  MUENZER JAN ,  MUESGEN RALF ,  OECHSNER MATTHIAS ,  PICKERT URSULA ,  VOSBERG VOLKER

    IPC: F01D5/22

    CPC classification number: F01D5/20 ,  F01D5/147 ,  F05D2230/232

    Abstract: PROBLEM TO BE SOLVED: To modify turbine blades 10 of a gas turbine to surely join both shell elements. SOLUTION: In the turbine blades 10 of the gas turbine provided with an attachment part/blade base part 14, and having a blade profile part 16 with a blade profile part tip 36 including both side shell elements 28, 30 positioned with opposing each other adjoin the attachment part/blade base part 14, and having the shell elements 28, 30 mutually joined as a blade back side wall 18 or a blade face side wall 20 respectively, the both shell elements 28, 30 are protected from being mutually peeled off by meshing engagement in a region of the blade profile tip 36. COPYRIGHT: (C)2008,JPO&INPIT

    Abstract translation: 要解决的问题：修改燃气轮机的涡轮叶片10以确保地连接两个壳单元。 解决方案：在具有附接部分/叶片基部14的燃气轮机的涡轮机叶片10中，具有叶片轮廓部分16的叶片轮廓部分16具有叶片轮廓部分尖端36，叶片轮廓部分尖端36包括两个侧壳体元件28,30， 彼此邻接连接部分/叶片基部14，并且壳体元件28,30分别作为叶片后侧壁18或叶片侧壁20相互连接，两个壳体元件28,30被保护而不相互 通过在叶片轮廓尖端36的区域中的啮合接合而剥离。版权所有（C）2008，JPO＆INPIT

    METHOD OF MANUFACTURING TURBINE BLADE
    3.
    发明专利
    METHOD OF MANUFACTURING TURBINE BLADE 审中-公开

    公开(公告)号：JP2002349285A

    公开(公告)日：2002-12-04

    申请号：JP2002098225

    申请日：2002-04-01

    Applicant: SIEMENS AG

    Inventor： ESSER WINFRIED ,  HAENDLER MICHAEL ,  TIEMANN PETER

    IPC: F01D5/18 ,  B22C21/14 ,  F01D9/02 ,  F02C7/00

    Abstract: PROBLEM TO BE SOLVED: To guarantee the high-yield manufacturing of a turbine blade having cavities. SOLUTION: A core element 10 is joined to a separate core element and/or casting mold via a plurality of almost cylindrical spacers 14. A blade material is cast in the casting mold. After removing the core element 10 and the spacers 14, an opening formed by the spacers 14 and the cavities 4 and 6 formed by the core element 10 remain in the turbine blade 1. The opening is closed by a blocking element.

    Turbine blade with coolant passage in turbine
    4.
    发明专利
    Turbine blade with coolant passage in turbine 有权
    涡轮叶轮与涡轮机中的冷却液通道

    公开(公告)号：JP2008095693A

    公开(公告)日：2008-04-24

    申请号：JP2007266270

    申请日：2007-10-12

    Applicant: Siemens Ag ,  シーメンス アクチエンゲゼルシヤフトSiemens Aktiengesellschaft

    Inventor： BERGANDER KATHARINA ,  BOSTANJOGLO GEORG ,  BUCHAL TOBIAS ,  ESSER WINFRIED ,  GOLDSCHMIDT DIRK ,  KOCH THORSTEN ,  KUEPERKOCH RUDOLF ,  MATTHEIS THORSTEN ,  MUENZER JAN ,  MUESGEN RALF ,  OECHSNER MATTHIAS ,  PICKERT URSULA ,  VOSBERG VOLKER

    IPC: F01D5/18 ,  F02C7/16 ,  F02C7/18

    CPC classification number: F01D25/12 ,  F01D5/18 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/232 ,  F05D2230/238 ,  F05D2240/81 ,  F05D2260/36

    Abstract: PROBLEM TO BE SOLVED: To cool a blade pedestal of a turbine blade and/or obtain, at an inexpensive manufacturing cost, a cooling function of the blade pedestal in a turbine blade (10) in a turbine in a thermal electric power station which is equipped with a blade pedestal (16) for partially bounding a working medium flow channel in the turbine and in which the blade pedestal (16) includes at least one coolant passage (20) that extends inside the blade pedestal and is used for guiding the coolant.
    SOLUTION: At least one coolant passage (20) communicates with an outside of the blade pedestal (16) in at least two connection openings (22). The turbine blade (10) includes at least one accessory (24, 26) equipped with a coupling passage (28) attachable to the blade pedestal (16). Further, the coupling passage (28) is designed to be connected with the connection openings (22) so as to be guidable for a flow.
    COPYRIGHT: (C)2008,JPO&INPIT

    Abstract translation: 要解决的问题：为了冷却涡轮机叶片的叶片基座和/或以廉价的制造成本获得在热电力的涡轮机中的涡轮叶片（10）中的叶片基座的冷却功能 其配备有用于部分地限制涡轮机中的工作介质流动通道的叶片基座（16），其中所述叶片基座（16）包括在所述叶片基座内部延伸的至少一个冷却剂通道（20），所述冷却剂通道 引导冷却液。 解决方案：至少一个冷却剂通道（20）在至少两个连接开口（22）中与叶片基座（16）的外部连通。 涡轮叶片（10）包括至少一个配备有可连接到叶片基座（16）的联接通道（28）的附件（24,26）。 此外，联接通道（28）设计成与连接开口（22）连接，以便引导流动。 版权所有（C）2008，JPO＆INPIT

    METHOD OF REMOVING METAL LAYER OF LAYER SYSTEM
    5.
    发明专利
    METHOD OF REMOVING METAL LAYER OF LAYER SYSTEM 审中-公开

    公开(公告)号：JP2003245857A

    公开(公告)日：2003-09-02

    申请号：JP2002363954

    申请日：2002-12-16

    Applicant: SIEMENS AG

    Inventor： ESSER WINFRIED ,  REICHE RALPH

    IPC: B24C1/00 ,  C23C4/02 ,  F01D5/28 ,  F01D25/00

    Abstract: PROBLEM TO BE SOLVED: To provide a method to effectively remove a metal layer for coating that covers a turbine blade without causing an unfavorable effect on a support and other layers of the turbine blade. SOLUTION: First, the metal layer is cooled to below room temperature (RT), for example, to a liquid nitrogen temperature, to make it brittle. Then, the embrittled metal layer is removed in a high-efficiency blast process, for example, a sandblast process. The process of metal layer removal is controlled by selecting blast process energy so as to remove the metal layer but avoid damage to the support. COPYRIGHT: (C)2003,JPO

    Dichtelement zur Dichtung eines Spaltes
    9.
    发明专利
    Dichtelement zur Dichtung eines Spaltes 未知

    公开(公告)号：DE102013205031A1

    公开(公告)日：2014-09-25

    申请号：DE102013205031

    申请日：2013-03-21

    Applicant: SIEMENS AG

    Inventor： BUCHAL TOBIAS ,  ESSER WINFRIED ,  KRACHT FREDERIC ETIENNE ,  KÜPERKOCH RUDOLF ,  PREUTEN FRANK ,  SCHÜLER MARCO ,  THERMANN HANS ,  WILKES JAN

    IPC: F01D11/00 ,  F16J15/08

    Abstract: Dichtelement (24) zur Dichtung eines Spaltes (22) zwischen zwei thermisch gegeneinander beweglichen Bauteilen (12, 20), die jeweils eine Bauteilnut (26, 28) aufweisen, wobei das Dichtelement (24) entlang einer Hauptlinie gerichtet ist und in einem im Wesentlichen zur Hauptlinie senkrechten Querschnitt einen ersten Endabschnitt (30) und einen zweiten Endabschnitt (32) sowie einen zwischen den Endabschnitten (30, 32) angeordneten Mittelbereich (34) aufweist, soll eine wirksame Dichtung auch bei radial vergleichsweise großen Wärmeausdehnungen der Bauteile gewährleisten und dennoch thermische Spannungen und Rissbildungen an den Bauteilen verringern. Dazu sind die Endabschnitte (30, 32) im Wesentlichen senkrecht zueinander ausgerichtet und der zweite Endabschnitt (32) hat eine erste Oberfläche (40), die gezahnt ist.

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