FIELD: engines.
SUBSTANCE: invention relates to aircraft engine building, specifically to methods of controlling air bypass from a compressor of a gas turbine engine (GTE) of an aircraft.
EFFECT: invention solves the problem of increasing the reliability (fault tolerance) and accuracy of the method of controlling the air bypass from the low-pressure compressor of the turbojet two-shaft engine of the aircraft by introducing an additional (backup) signal which characterizes the movement of the aircraft on the runway; higher reliability of aircraft speed Va when vortex-like air suction into engine air intake from runway surface disappears and there is no effect of tail or side wind on engine operation.
3 cl, 1 dwg
