FIELD: machine building.
SUBSTANCE: jet turbine engine comprises an intermediate heat exchanger, the primary circuit of which is connected at the outlet with the last stage of the compressor. Last cascade including centrifugal compressor, engine combustion chamber and centripetal turbine is located along engine axis and inside its external circuit. Intermediate heat exchanger with inlet and outlet branch pipes is located inside engine pylon. Primary circuit of the intermediate heat exchanger is connected to the output of the penultimate cascade of the compressor, and the secondary circuit of the intermediate heat exchanger is communicated with the atmosphere. Inlet hole of the inlet duct of the intermediate heat exchanger is located in the area of the unperturbed flow of fuselage.
EFFECT: invention is aimed at increasing flight range, reducing the number of engines, reducing labor costs during their manufacture and finishing.
5 cl, 4 dwg
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