FIELD: engine building.
SUBSTANCE: invention relates to gas turbine engines operation control and can be used for gas turbine engine (GTE) guide vanes position adjustment. In gas turbine engine compressor guide vanes position control system, comprising guide vanes position adjustment actuator, control unit connected to the gas turbine engine operating parameters measurement sensors unit, the first and the second switches controlled by the actuators connected to the control unit, the new one is that the system is equipped with the third switch controlled from the logic unit, connected to the first and second switches, drive for guiding devices position adjustment is made in the form of two hydraulic cylinders, which movable elements are equipped with sensors of their position, connected to control unit, and are kinematically connected to annular drive of blades of guide vanes of compressor. Besides, the system is also equipped with two electrohydraulic amplifiers connected to the control unit, each of which through switches is configured to control one or two hydraulic cylinders, at that inputs of the logic unit are connected to outputs of actuating mechanisms of the first and second switches.
EFFECT: technical result of present invention is development of GTE compressor guide vanes position control system providing improved reliability of guiding devices control, as well as high accuracy of control in wide range of control due to higher accuracy of positioning of guiding devices.
1 cl, 1 dwg
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