| 摘要 |
<p>A variable stator vane 6 in a gas turbine engine has a journal 18 provided with a circumferential recess 28. An aperture 34 extends from the recess 28 to a face of the journal directed towards the aerofoil portion 14 of the vane 6. In operation of the engine, heated air, for example from a downstream compressor stage of the engine is admitted to the recess 28 and flows through the aperture 34 to, for example, the pressure surface of the aerofoil portion 14. The aerofoil portion 14 is thereby heated, so preventing ice accretion on the vane 6.</p> |
