ELECTROMECHANICAL CONTROL SYSTEM FOR THE REVERSING DEVICE OF A GAS TURBINE ENGINE WITH HIGHLY RELIABLE POWER SUPPLY

摘要

FIELD: aircraft engineering. ;SUBSTANCE: invention relates to the field of control of a gas turbine engine (GTE) of the FADEC type. An electromechanical control system for a reversible device (RD) of the GTE with a highly reliable power supply, which contains an electronic motor controller from a digital engine control system having at least two electronic channels with the possibility of issuing control commands to open or close the RD by each channel, an electronic control unit of the RC having at least two electronic control channels with the possibility of exchanging information between these channels, three electromechanical drives, each of which includes an electric motor; two separate power sources, with each separate power source connected to the corresponding channel of the electronic motor controller and the electronic control unit of the RD. Additionally, it contains a power supply unit for GTE units with the possibility of powering each channel of the electronic controller and/or each channel of the electronic control unit of the RD, as well as with the possibility of automatic control of the power supply coming to the input of the power supply unit of the GTE devices; an autonomous electric generator of the motor, including two channels for generating electricity and mechanically connected to the rotor of the gas turbine engine, while both channels for generating an autonomous electric generator are connected to the power supply unit of the devices; each separate power supply contains an independent direct current supply channel, rated voltage +28 V, while at least one separate power supply contains three channels of alternating three-phase current; the output voltage of +28 V of each individual power supply source is connected to the input of the power supply unit of the motor units and to the input of the electronic control unit; the output voltage of three channels of alternating three-phase current from at least one separate power source is connected to separate inputs of the electronic control unit of the RD; the electronic control unit of the RD. Additionally, it contains a power supply monitoring module with the possibility of automatic control of the power supply coming to the input of the electronic control unit of the RD. ;EFFECT: invention makes it possible to increase the reliability and fault safety of the electromechanical system and the engine, to improve flight safety in general. ;16 cl, 1 dwg