| 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 low pressure and/or high pressure stages of the compressors of the engine, a cold air take-off downstream of the fan of the a engine, a precooling heat exchanger between said hot air and said cold air, and hot air and/or cold air flow rate regulating valves. According to the invention, said heat exchanger (18) is arranged at the forward part (13A) of the engine (1) support pylon (13), being traversed by said air stream (21) which leaves the fan (6) and is not directed toward the compressors (3).
|
