| 摘要 |
A gas turbine has an annular combustion chamber (10 fig 1) with walls 13 (12 fig 1) made of ceramic material mounted inside a metal casing (30, 40, fig 1) by first linking members fastened to the chamber by brazing. Each linking member has a plurality of linking tabs 60 (50 fig 3) which include a first portion 64a (54a fig 3) fastened to the external combustion chamber wall by brazing. The tabs are arranged in a spaced apart circumferential relationship, and may be integral with a continuous ring or ferrule 64 (54 fig 3). The tabs and integral ferrule may be made of a ceramic matrix composite material and provide linkage to the inner (12 fig 1) and outer (13 fig 1) combustion chamber walls. The tabs may also include a second portion 61 (51 fig 3) which is fastened to the metal casing, by direct means, or via a second linking part (65, 55, fig 4) which is metallic and flexible. The flexible linking part may also include an end portion (56, 66, fig 4) connected by bolting to one end of the corresponding tab of the first linking members (50, 60, fig 4), and an integral annular metal ferrule (58, 68, fig 4). This ferrule may provide an annular flange that can be clamped between flanges of the metal casing, or alternatively, a means for bolting directly to the casing. |
