| 摘要 |
A stage of guide vanes 20 in a gas turbine engine are cooled by compressor air delivered via piping 36, 38 and by leakage air in the space volume bounded by the combustion apparatus and the turbine shafting. The leakage air is drawn through tubing 40 by the compressor air which is directed via space 43 over the exit ends of the tubing 40 to create the necessary pressure drop in the tubing 40.
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