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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：US20150176424A1
公开(公告)日：2015-06-25
申请号：US14574846
申请日：2014-12-18
Applicant: ALSTOM Technology Ltd.
Inventor： Carlos Simon-Delgado , Christoph Didion , Marc Widmer , Martin Schaefer , Guenter Filkorn
CPC classification number: F01D11/18 , F01D11/001 , F01D11/025 , F01D11/122 , F01D11/127 , F05D2250/283
Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.
Abstract translation: 本发明涉及一种用于在涡轮机定子和涡轮机转子之间的通道的密封系统，包括：第一臂从涡轮转子径向向外延伸并且朝向布置在定子上的第一密封件延伸，并且终止于第一密封件之外，从而产生 第一密封件和第一臂之间的第一间隙。 所述密封系统还包括布置在所述涡轮机定子上的第二密封件，以及从所述涡轮机转子朝向所述第二密封基座轴向延伸并且终止于所述第二密封件的第二臂，从而在所述第二密封件和所述第二臂之间形成第二间隙 。 本发明还涉及一种包括这种密封系统的燃气轮机。
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