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

IPC: F01D9/02 ,  F01D25/28 ,  F23R3/00

CPC classification number: F01D9/023 ,  F01D25/28 ,  F02C7/20 ,  F23R3/002 ,  F23R3/60 ,  F23R2900/00012

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。