AIRCRAFT TURBOJET ENGINE WITH PRESSURE CHAMBER Russian patent published in 2010 - IPC F02K1/54 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises air inlet, air compressor with supercharging, combustion chamber and rear nozzle. Pressure chamber is arranged between rear nozzle that creates forward thrust and combustion chamber. Aforesaid air compressor comprises inlet compressor, larger pressure compressor and smaller pressure compressor, both coupled with transmission front shaft. It additionally comprises front drive turbine and rear drive turbine coupled with transmission rear shaft. Gearbox is arranged between transmission front and rear shafts, gearbox front section accommodating nozzle. High-temperature gas forced into pressure chamber can effuse through rear nozzle to push aircraft forward or lower nozzle to lift or down the aircraft, or to effect whatever maneuver.

EFFECT: reduced noise and higher efficiency.

6 cl, 9 dwg