FIELD: aircraft engineering.
SUBSTANCE: proposed aircraft engine comprises combustion chamber, resonant tube, air-fuel mix intake multi-ejector system, fuel injection nozzle, fuel system, superheater coil arranged at aircraft tail side. Fuel is fed from fuel system into air-fuel mix intake multi-ejector system. Outlet of said air-fuel mix intake multi-ejector system is communicated with combustion chamber front part at aircraft nose part. Fuel injection nozzle is arranged at inlet of said air-fuel mix intake multi-ejector system. Exhaust gases from resonant tube is directed opposite aircraft flight path. Said resonant tube is arranged outside the combustion chamber while superheater coil is located there inside. Axes of resistant tube, combustion chamber and air-fuel mix intake multi-ejector system are arranged in parallel. Exhaust gases are released from combustion chamber with 180 degrees turn relative to engine motion vector.
EFFECT: decreased overall dimension of air breather.
13 cl, 4 dwg
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