METHOD FOR CONTROLLING A GAS TURBINE ENGINE IN CASE OF SPONTANEOUS OPENING OF A REVERSING DEVICE Russian patent published in 2022 - IPC F02K1/76 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, in particular to methods for automatic control of a gas turbine engine (GTE). The method for controlling a gas turbine engine lies in the fact that with an electronic controller the operating modes of the gas turbine engine are regulated and, at the same time, when the aircraft is in the air, the output of a control signal to turn on the reversing device of the gas turbine engine is blocked; by means of a sensor, the position A^cur of the moving part of the reversing device is determined and the absence of spontaneous movement of the reversing device is also diagnosed (monitored); after the aircraft touches the runway, the engine control lever is moved to the minimum reverse thrust area and the reverser lock is opened, the information signal “Reverser lock is not closed” is generated, and also after the engine control lever is moved to the minimum reverse thrust area from the electronic engine controller in automatic mode, according to the given operation algorithms, a control action is issued to transfer the reversing device from the “Forward thrust” position to the “Reverse thrust” position, after the reversing device is switched to the “Reverse thrust” position, based on the position sensor data of the movable part of the reversing device, an information signal “Reversing device is on” is generated, then the engine control lever is moved to the position necessary to achieve the required reverse thrust value, and the engine operation mode is automatically set, corresponding to the position of the engine control lever, additionally, in the electronic regulator, a preset parameter A^set is formed, which characterizes the value of the maximum allowable (setting) value of the spontaneous partial opening of the reversing device, the A^cur parameter and the Aust parameter are compared, in the event that the A^set parameter exceeds the A^set parameter in the electronic regulator, when the engine control lever is in a position above the direct thrust idle gas, a control action is formed to reduce the engine operating mode to idle by reducing the fuel consumption supplied to the GTE combustion chamber in the shortest time possible.

EFFECT: present invention makes it possible to increase the fault tolerance and reliability of the gas turbine engine, to increase flight safety due to the timely detection of a partial opening of the reverser and counter this failure with the required high speed.

4 cl, 2 dwg