FIELD: flying vehicle; turbojet engines.
SUBSTANCE: exhaust unit of bypass turbojet engine of flying vehicle has housing and dividing partition forming channel of second loop, central turbine fairing with perforated surface and pipeline to deliver air into inner space of turbine fairing. Spacing of perforation holes on surface of fairing is at least one hole per sq. cm. at permeability within 0.5 and 2%. Air delivery pipeline is connected from one side channel of second loop and at other side, with inner space of turbine fairing.
EFFECT: reduced level of infrared radiation of engine.
2 cl, 1 dwg
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