FIELD: engines.
SUBSTANCE: invention relates to aircraft engineering, particularly, to control over gas turbine engine at aborted takeoff. Technical task of the invention is to increase the level of flight safety by highly reliable determination of the aircraft interrupted take-off mode and automatic elimination of high engine thrust in aborted take-off conditions without switching on the reverser at non-localized failure of the engine fuel supply system, due to increased reliability (validity) of aircraft aborted takeoff identification by application of information signal from aircraft system, characterizing aircraft critical flight stage/aborted takeoff, as well as automatic identification of engine fuel supply system failure, leading to its high thrust in conditions of aborted takeoff, timely and reliable parry of high thrust of gas turbine engine in conditions of aborted takeoff by automatic termination (cutoff) of fuel supply to combustion chamber of gas turbine engine.
EFFECT: higher flight safety.
6 cl, 3 dwg
