FIELD: machine building.
SUBSTANCE: invention relates to aircraft turbojet engines, including engines for supersonic multimode aircraft, and relates to a method of operating a double-flow turbojet engine, which comprises an air intake, fan, two airflow circuits, two turbines, afterburner and jet nozzle. Engine is equipped with bypass ratio variation device. Device is installed on the outer side of the internal circuit in the area of the compressor and the combustion chamber and consists of hydraulic cylinders pivotally connected by rods to a cylindrical washer. Washer is pivotally connected by rods with flaps pivotally fixed on the end of the housing of the inner contour. From the outside, the device is partially covered with a fairing.
EFFECT: higher thrust and speed characteristics of supersonic flight.
1 cl, 1 dwg
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