FIELD: motors and pumps.
SUBSTANCE: invention relates to controlling an aircraft engine. Method of controlling a twin-rotor gas turbine engine of aircraft at shutdown comprises reducing rotational speed of the high-pressure rotor shaft and the low-pressure rotor shaft. Rotational speed of the high-pressure rotor shaft and the low-pressure rotor shaft is reduced until the rotors achieve the same rotational speed. Rotors engage with each other by a freewheel located between the shafts, after which the rotor speed is reduced to a stop.
EFFECT: invention provides stable supply of oil to the engine mounts at stoppage before the complete stoppage of all the motor rotors, and also reduces the "sticking" effect of the high-pressure rotor shaft during shutdown.
1 cl, 1 dwg
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