| 摘要 |
In a gas turbine engine having a ceramic nozzle guide vane 18 supported by a metal turbine casing 28, 29 the radially outer end portion 23 of the vane is provided with a support arrangement comprising opposed frustoconical sections 26, 27 which converge towards each other onto a middle cylindrical section 25. The support arrangement also includes a metal split ring 30 which surrounds the cylindrical section 25, and the ends of the ring abut the frustoconical sections. The split ring may be provided with a flange 35 which cooperates with a groove structure on the turbine casing, thus enclosing the split ring to the casing. A locking insert 38 then fastens together two sections 28, 29 of the casing either side of the vane, thereby holding the split ring 30 against the vane. On increase in temperature the split ring expands more than does the portion 23. The ends of the split ring therefore slide against the frustoconical surfaces of the portion 23 to take up the expansion, and in so doing maintain contact with the vane. Seals 39, 40, 46 may be provided. The support arrangement could be applied to structures other than gas turbine engines. <IMAGE>
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