| 摘要 |
The invention relates to a fixing and sealing device for guide vanes of a gas turbine engine and in particular for combustion chamber guide vanes. The aerodynamically shaped part 31 of the vane 16 extends beyond the internal and external hoops 23, 24 in order to form ridges 32, 33 comprising claws for fixing to the fixed structure of the engine, the said hoops ending in upstream and downstream sealing cheeks 21, 22, 25, 26. Since the aerodynamic forces exerted on 31 are transmitted via the ridges, the hoops may be thin and easily cooled and the fixing device is located away from the streams of hot gases. <IMAGE>
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