FIELD: gas turbine engine building.
SUBSTANCE: invention is related to aviation gas turbine engine building and can be used in electronic automatic control systems with hydromechanical redundancy. The method of controlling a gas turbine engine with an electronic hydromechanical system consists of the fact that in the electronic controller, using sensors of the electronic controller, the position of the engine control lever and the parameters of the gas turbine engine are measured, depending on the position of the engine control lever and the value of the parameters of the gas turbine engine according to the control laws implemented in the electronic controller, control actions of the electronic controller are formed for its actuators in the hydromechanical controller using sensors of the hydromechanical controller, depending on the position of the engine control lever and the value of the parameters of the gas turbine engine and according to the laws of control of the hydromechanical controller, control actions of the hydromechanical controller are formed for its actuators, and if the electronic regulator is in good condition, the control actions of the hydromechanical regulator are blocked using a selector and the gas turbine engine is controlled from the electronic regulator through its actuators, and if the electronic regulator fails, the control actions of the electronic regulator are blocked using the selector and the gas turbine engine is controlled from the hydromechanical regulator, in case of failure of the electronic regulator, its control signal to the executing element for fuel consumption is stored for a period of time τ after issuing a control signal to the selector, where τ is the maximum allowable value of the selector spool shifting time, determined by calculation and experiment for each type of gas turbine engine and equal to 3-7 s.
EFFECT: gas turbine engine control method is provided.
2 cl, 1 dwg
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