METHOD OF CONTROLLING CRITICAL SECTION OF JET NOZZLE OF TWO-SHAFT BYPASS GAS TURBINE ENGINE Russian patent published in 2024 - IPC F02K1/15 F02K1/11 F02C9/28 

FIELD: aircraft engine building.

SUBSTANCE: invention can be used in electronic-hydromechanical automatic control systems multimode gas turbine bypass engines (GTE) with controlled critical section of jet nozzle. Disclosed is a method of controlling the critical section of a jet nozzle of a two-shaft bypass gas turbine engine, according to which rpm of engine rotors is measured and their ratio (S) is determined, determining the ratio of the air pressure behind the high-pressure compressor to the gas pressure behind the low-pressure turbine by two measurement channels (pi_T1 and pi_T2), determining the minimum (pi_Tmin) and maximum (pi_Tmax) values from the values pi_T1 and pi_T2, forming a given pressure ratio (pi_Tgiv), nominal ratio of engine rotor speeds (S_nom) is formed by calculation depending on high-pressure compressor rotor speed, generating the value of deviation of the current ratio of the rotation frequencies of the motor rotors from the nominal (ΔS=S−S_nom), if the value of ΔS is less than the comparator operation threshold, adjusting the critical section area of the jet nozzle of the engine depending on the deviation pi_Tmax from pi_Tgiv to counter the deviation, when the value ΔS exceeds the preselected threshold, the area of the critical section of the jet nozzle of the engine is controlled depending on the deviation of pi_Tmax from pi_Tgiv.

EFFECT: high reliability of the control system, maintaining the specified operating mode of the low pressure compressor in case of parametric failures of pressure sensors and elimination of additional reduction of thrust as the resource is depleted.

6 cl, 2 dwg, 1 tbl