FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, namely, to turbojet engine for airborne vehicle. The turbojet engine placed in pod contains heat exchanger (13) for cooling hot fluid drawn from propulsive system of this turbojet engine before the second injection of this partially cooled hot fluid into the mentioned propulsive system. The heat exchanger (8, 13, 18) represents radial heat exchanger passing in the lower part of turbojet engine at the level of bottom manifolding (6, 16) of this turbojet engine located downstream of fan and blades of fan directing vanes of this fan of turbojet engine. In this structure, the mentioned heat exchanger passes partially on outer side wall (10) of the mentioned bottom manifolding.
EFFECT: higher efficiency of turbojet engine heat exchanger operation.
6 cl, 4 dwg
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