| 摘要 |
An exhaust gas liner (18) for a gas turbine comprises an annular inner shell (21) and an annular outer shell (19), which are arranged concentrically around a machine axis of said gas turbine to define an annular exhaust gas channel in between, whereby said inner shell (21) and/or said outer shell (19) are composed of a plurality of liner segments (22, 23; 26, 27; 28), which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads said liner segments (22, 23; 26, 27; 28) are fixed to said support structure at certain fixation spots (29a-c; 30a-c), which are distributed over the area of said liner segments (22, 23; 26, 27; 28), such that said liner segments (22, 23; 26, 27; 28) are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion. |
