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 invention solves the technical problem associated with the lack of a differentiated approach to identifying and solving possible malfunctions of the channel for controlling the position of the GTE compressor blades.
EFFECT: technical result of the claimed method of controlling the inlet guide vane of the compressor of a gas turbine engine is increase of controllability of the circuit controlling position of the GTE compressor blades using an electronic controller of a two-channel design by introducing internal feedback to control the electrical control signal of the electronic controller. This ensures timely detection of a malfunction of the control channel and prevention of deviation of the compressor guide vanes to critical values that are characteristic of the prototype.
6 cl, 1 dwg
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