METHOD FOR EMERGENCY PROTECTION OF TURBOJET DOUBLE-CIRCUIT TWIN-SHAFT ENGINE FROM SPINNING OF ITS ROTORS Russian patent published in 2023 - IPC F02C9/28 F01D21/02 

FIELD: gas turbine engine construction.

SUBSTANCE: invention can be used in control systems for aviation dual-circuit twin-shaft engines, as well as in gas turbine units for power plants, superchargers for main gas pipelines, power gas turbine units for sea and river vessels, etc. A method has been proposed for emergency protection of a turbojet twin-shaft bypass engine from spin-up of its rotors, which consists of measuring the position of the engine control lever and engine parameters in the electronic engine governor using electronic governor sensors, depending on the position of the engine control lever and the value of engine parameters according to control programs implemented in the electronic regulator, forming the control actions of the electronic regulator and control the engine. In the autonomous electronic engine protection unit, the rotation speed n_f the engine fan rotor is measured using a sensor, and the rotation speed n_f the fan rotor is compared with the first preset calculated limit value n_f^1set. By calculation, the second preset design value n_f^2set is determined in advance, as well as the first value of the rotation speed of the high-pressure rotor n_hp^1set and the second value of the rotation speed of the high-pressure rotor n_hp2^set , the frequency values n_f^2set, n_hp^1set, n_hp2^set are additionally entered in the autonomous electronic engine protection unit, a high-pressure rotor speed n_hp sensor is also introduced into the engine design, the high-pressure rotor speed n_hp is measured in the autonomous electronic engine protection unit using a sensor, n_f is also additionally compared with n_f^2set and n_hp with n_hp^1set, n_hp^2set, and if at the same time the speed of rotation n_f exceeds n_f^1set and the speed of rotation n_hp exceeds n_hp^1set or at the same time the speed of rotation n_f exceeds the preset limit value n_hp^2set and the rotation speed n_f exceeds the preset limit valuen_f^2set, then using an autonomous electronic engine protection unit, the fuel supply to the combustion chamber is stopped and the engine is turned off.

EFFECT: increased functional reliability and fault tolerance of emergency protection of a turbojet twin-shaft bypass engine from spin-up of its rotors during an uncontrolled increase in fuel consumption G_t into the engine combustion chamber, eliminating false alarms of the autonomous engine protection unit.

4 cl, 1 dwg