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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
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。
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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
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.
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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
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。
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