METHOD FOR AUTOMATICALLY CONTROLLING AIRCRAFT POWER PLANT WHEN THRUST OF ONE OF ENGINES IS REDUCED DURING TAKE-OFF Russian patent published in 2024 - IPC F02C9/42 F04D27/02 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to methods for automatically controlling an aircraft power plant, consisting of two gas turbine engines (GTE), in the event of failure or partial loss of thrust of one of the engines. The effect is achieved by the fact that additionally, during the take-off mode of the aircraft, in the main and backup channels of the electronic regulator of each engine, the thrust parameter R of this engine is measured and its thrust parameter R is compared with predetermined value R^set, in the event of a spontaneous decrease in thrust parameter R of the faulty engine below R^set detected in each channel of the electronic regulator of the faulty engine, failure sign I_fault is generated in each channel of the electronic regulator of the faulty engine. Based on simultaneous presence of the failure sign I_fault in each channel of the electronic regulator of the faulty engine, the electronic regulator of the faulty engine transmits discrete information signal I “Engine failure. Turn on HPM”, and in the event of a failure of one of the channels of the electronic regulator of a serviceable engine or failure of one channel of the electronic regulator of a serviceable engine to detect a decrease in the thrust parameter R < R^set of the faulty engine, activation of the electronic regulator of the faulty engine in the high-power mode of the faulty engine is carried out only when a spontaneous decrease in the thrust parameter R of the faulty engine is detected by the working channel of the electronic regulator of the faulty engine and the information discrete signal I “Engine failure” is received at the input of the electronic regulator of the faulty engine. Turn on HPM" from the electronic regulator of the faulty engine; and if any channel of the electronic regulator of a serviceable engine fails to detect a decrease in the thrust parameter R< R^set and absence of discrete information signal I “Engine failure. Turn on the RPT" from the second engine, the high-power mode of the serviceable engine is not activated.

EFFECT: improved functional reliability and fault tolerance of the power plant control method in the event of failure of one of the channels of the electronic engine governor; blocking false activations of the high-power mode.

6 cl, 1 dwg