| 摘要 |
<p>The invention relates to an aircraft turbomachine (10) comprising a nacelle and an engine (12) comprising at least one outflowing jet of air, characterised in that a heat exchanger (20) of the precooler type for supplying air to the aircraft is mounted in the nacelle, said exchanger comprising a primary circuit, the inlet of which is connected to means for taking compressed air from the engine and the outlet of which is connected to means for supplying air to the aircraft, and a secondary circuit supplied with air taken from said air flow.</p> |
