BYPASS TURBOJET ENGINE Russian patent published in 2018 - IPC F02K3/04 F02K3/115 

FIELD: engine building.

SUBSTANCE: two-circuit turbojet engine with separate circuits with a two-contour ratio of more than ten consists of an input device, a fan; internal contour, inside of which there are a compressor (compressors), a combustion chamber, turbines; outer contour consisting of an annular channel and a nozzle. Engine is equipped with a diffuser outlet branch pipe, which is a continuation of the inner contour and consisting of expanding channels, located inside the outer contour and communicated with the atmosphere.

EFFECT: invention makes it possible to increase the pressure drop in the fan drive turbine, transfer part of the heat from the internal circuit to the external circuit, thereby increasing the effective and flight efficiency.

1 cl, 3 dwg