公开(公告)号：US09816393B2

公开(公告)日：2017-11-14

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 ,  F01D5/08 ,  F01D11/00

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.

公开(公告)号：US20140030077A1

公开(公告)日：2014-01-30

申请号：US13950344

申请日：2013-07-25

Applicant: ALSTOM Technology Ltd

Inventor： Beat Von Arx ,  Herbert Brandl

IPC: F01D5/00

CPC classification number: F01D5/005 ,  F01D9/042 ,  Y10T29/49229

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Abstract translation: 本发明涉及一种具有至少一个涡轮级的固定式燃气轮机装置，该至少一个涡轮级包括至少第一排叶片，其安装在设置在第一排叶片的径向外侧的固定部件处并径向延伸到涡轮机的环形入口 面向燃烧器的下游端。 另外，对固定式燃气轮机进行维修工作的方法进行说明。 本发明的特征在于，固定部件为每个叶片提供设计和布置用于径向插入和移除叶片的径向取向的通孔，并且每个叶片包括翼型件，其翼端在其一端径向向外指向轮廓 适于通过可拆卸的固定装置密封通孔。

公开(公告)号：US09494039B2

公开(公告)日：2016-11-15

申请号：US13950344

申请日：2013-07-25

Applicant: ALSTOM Technology Ltd

Inventor： Beat Von Arx ,  Herbert Brandl

IPC: F01D5/00 ,  F01D9/04

CPC classification number: F01D5/005 ,  F01D9/042 ,  Y10T29/49229

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Abstract translation: 本发明涉及一种具有至少一个涡轮级的固定式燃气轮机装置，该至少一个涡轮级包括至少第一排叶片，其安装在设置在第一排叶片的径向外侧的固定部件处并径向延伸到涡轮机的环形入口 面向燃烧器的下游端。 另外，对固定式燃气轮机进行维修工作的方法进行说明。 本发明的特征在于，固定部件为每个叶片提供设计和布置用于径向插入和移除叶片的径向取向的通孔，并且每个叶片包括翼型件，其翼端在其一端径向向外指向轮廓 适于通过可拆卸的固定装置密封通孔。

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。