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公开(公告)号：US09708920B2
公开(公告)日：2017-07-18
申请号：US14254985
申请日：2014-04-17
Applicant: ALSTOM Technology Ltd
Inventor： Remigi Tschuor , Sinisa Narancic , Guenter Filkorn
Abstract: A gas turbine includes a compressor, an annular combustion chamber, and a turbine, a combustion chamber shell of the combustion chamber adjoining the turbine inlet in a transition region in order to introduce the hot gases generated in the combustion chamber into the downstream turbine such that a thermal expansion-induced relative movement between the combustion chamber and the turbine inlet is possible. Combustion chamber shell support elements distributed on the periphery come into contact with a conical contour on the shaft cover due to the thermal expansion that occurs during operation and are supported on said contour. An improvement with respect to loading and service life is achieved in that the conical contour and the machine axis form an angle that allows the combustion chamber shell support elements to slide onto the conical contour.
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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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公开(公告)号：US20140223921A1
公开(公告)日：2014-08-14
申请号：US14254985
申请日：2014-04-17
Applicant: ALSTOM Technology Ltd
Inventor： Remigi TSCHUOR , Sinisa Narancic , Guenter Filkorn
Abstract: A gas turbine includes a compressor, an annular combustion chamber, and a turbine, a combustion chamber shell of the combustion chamber adjoining the turbine inlet in a transition region in order to introduce the hot gases generated in the combustion chamber into the downstream turbine such that a thermal expansion-induced relative movement between the combustion chamber and the turbine inlet is possible. Combustion chamber shell support elements distributed on the periphery come into contact with a conical contour on the shaft cover due to the thermal expansion that occurs during operation and are supported on said contour. An improvement with respect to loading and service life is achieved in that the conical contour and the machine axis form an angle that allows the combustion chamber shell support elements to slide onto the conical contour.
Abstract translation: 燃气轮机包括压缩机，环形燃烧室和涡轮机，燃烧室的燃烧室壳体与过渡区域中的涡轮机入口相邻，以便将在燃烧室中产生的热气体引入下游涡轮机，使得 燃烧室和涡轮机入口之间的热膨胀引起的相对运动是可能的。 分布在周边的燃烧室壳体支撑元件由于在操作期间发生的热膨胀而与轴套上的锥形轮廓接触并且被支撑在所述轮廓上。 实现了相对于装载和使用寿命的改进，其中锥形轮廓和机器轴线形成允许燃烧室壳体支撑元件滑动到圆锥形轮廓上的角度。
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