BYPASS TURBOJET ENGINE Russian patent published in 2018 - IPC F02K3/06 

FIELD: motors and pumps.

SUBSTANCE: two-circuit turbojet engine contains input device, fan, inner contour, outer contour, and tapered nozzle. Inside the internal circuit there are compressor with air bleeding for cooling turbine, combustion chamber, turbines. Inside the external circuit there is heat exchanger in which air coming from mixer circulates. Air coming from compressor and air coming from heat exchanger are mixing in mixing machine. Engine is equipped with heat exchanger, which is continuation of internal circuit, located inside external circuit – behind first heat exchanger and connects internal circuit with atmosphere through exhaust pipes.

EFFECT: use of exhaust nozzles allows to lower gas pressure behind turbines to lowest possible (less atmospheric) and thereby increase turbines specific operation, which allows to reduce air flow (fuel) through internal circuit – to increase engine economy.

4 cl, 6 dwg