| 摘要 |
<p>A turbomachine having a compressor 8 connected by a shaft 22 to a turbine 10, the compressor and turbine comprising a plurality of stages of discs 12, 14 subjected to a thermal gradient, is provided with means for ventilating the discs to limit their thermal gradient, the ventilating means comprising first and second sources S1, S2 for taking gas at different positions from the gas flow path 16 through the compressor, and ducting means for directing, independently, the gas taken from the first source S1 and the gas taken from the second source S2 towards the compressor discs 12 and the turbine discs 14. The ducting means includes a gas duct 24 which coaxially surrounds the shaft 22 and defines an annular gas passage 26 between itself and the shaft. <IMAGE></p> |
