BYPASS TURBOJET ENGINE Russian patent published in 2018 - IPC F02K3/02 

FIELD: engines and pumps.

SUBSTANCE: two-circuit turbojet engine, which contains: high and low pressure compressors, separated by an intermediate casing, main combustion chamber, air-to-air heat exchanger, high and low pressure turbines, mixer, reverse thrust, front-end device, afterburner combustion chamber, jet nozzle turning mechanism and all-mode slewing jet nozzle. Engine is also equipped with a reverse thrust located behind the mixer in front of the front-end device along the axis of the engine. Reverse includes deflecting channels, each of which is equipped with a valve, communicating with the flow part of the engine, and groups of rotating blades located behind the mixer in front of the front-line device along the axis of the engine. Each group of rotating blades is gas-dynamically connected with its deflecting channel and has the possibility of independent partial overlapping of the flow-through part of the engine with simultaneous opening of the corresponding valve of the deflecting channel. Afterburner combustion chamber has a housing connected to an all-mode jet nozzle by means of a rotation mechanism of the all-mode jet nozzle. All-mode jet nozzle is made with the possibility of rotation in the same plane and simultaneous rotation around its axis through the mechanism of rotation of the jet nozzle.

EFFECT: increase in the angular velocity of the aircraft turning due to equipping a bypass turbojet engine with a low degree of bypass ratio with a deflected thrust vector in different directions around the longitudinal axis of the engine, in particular, creating a negative thrust vector of the engine.

4 cl, 2 dwg