| 摘要 |
The present invention relates to a device for bleeding off and cooling hot air in an aircraft engine, including: at least one hot air take-off at the outlet of the compressors of the engine, a cold air take-off downstream of the fan of the engine, a precooling heat exchanger between said hot air and said cold air. According to the invention, said precooling heat exchanger (18) comprises at least one (12A) of said linking arms (12) between the engine body (2) and the fan shroud (9), the said linking arm or arms (12A) acting as the exchanger, exhibiting a hollow structure traversed longitudinally by at least some of the hot air bled off at the outlet of the low pressure and/or high pressure stages of the compressors (3) of the engine.
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