FIELD: engines and pumps.
SUBSTANCE: jet turbine engine includes a housing, in which a turbine with an exhaust cone, a mixer, an afterburner duct and a nozzle are located in series. The exhaust cone includes cooled and non-cooled parts. The cooled part is provided with an annular channel formed with an inner shell and a perforated surface of the exhaust cone. The mixer forms together with the housing a cold air channel, and with the non-cooled part of the exhaust cone a hot air channel. The afterburner duct includes annular flame stabilisers. A small annular flame stabiliser is of a cooled type and installed so that it screens the non-cooled part of the exhaust cone on the nozzle side.
EFFECT: invention allows reducing the infrared emission level of the jet turbine engine to rear semi-sphere of the aircraft and full pressure losses, and reducing overall dimensions and weight of the engine exhaust unit.
5 cl, 3 dwg
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