Method of controlling aircraft bypass turbojet engine

FIELD: aviation. SUBSTANCE: invention relates to methods of controlling aircraft jet turbine engines, specifically bypass turbojet engine with a variable area of output device. Method comprises preliminary testing of several samples of engines with different areas of output device, adjusted to a surge in range of operating rotor speeds low pressure by means of spoiler, and then determining frequencies of rotor rotation low pressure with minimal inventory dynamic stability of engine and determined to have a minimum possible area of output device, which provides required stability margins, then turns with a minimum size of output device is fixed air flow through engine Gv and pressure ratio in low-pressure compressor π knd and determining amount of π knd /Gv, which was taken as maximum permissible value, and making adjustment of output area of device to ensure value for debugging a particular engine π knd /Gv does not exceed maximum allowable value. EFFECT: method provides required safety margins of stable operation of engine in entire range of operating speed. 1 cl, 1 dwg