METHOD FOR CONTROLLING A TWO-SHAFT GAS TURBINE ENGINE WITH ADJUSTABLE GUIDE DEVICES OF HIGH AND LOW-PRESSURE COMPRESSORS Russian patent published in 2022 - IPC F02C9/00 F04D27/00 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engine construction, namely to the control of a two-shaft gas turbine engine with adjustable guide devices of high and low-pressure compressors. The technical problem of the invention is to increase the reliability of the control system. The expected result is achieved in a method for controlling a two-shaft gas turbine engine with adjustable guide devices of high and low-pressure compressors, with a set nominal ratio of the reduced rotor rotation frequencies for each engine operating mode, including control of the rotation frequencies of low and high-pressure rotors by changing fuel consumption in the main combustion chamber, adjusting the position of the guide devices, affecting the speed of their movements, at the same time, a threshold is selected in advance according to the reduced rotation frequency of one of the rotors, in the range of engine operating modes below the selected threshold, the rotation frequency of the low-pressure rotor is maintained by influencing the increase in fuel consumption into the main combustion chamber, while the rotation frequency of the high-pressure rotor is maintained based on the nominal established ratio of the reduced rotation speeds of the rotors by influencing the speed of movement of the guide devices of the high-pressure compressor, and in the range of engine operating modes above or equal to the selected threshold, the rotation frequency of the high-pressure rotor is maintained by affecting the reduction of fuel consumption in the main combustion chamber, and the rotation frequency of the low-pressure rotor is maintained based on the nominal established ratio of the reduced rotational speeds of the rotors by affecting the speed of movement of the guiding devices of the low-pressure compressor.

EFFECT: ensuring the controllability of the engine in the absence of information about the position of the compressor guides.

1 cl, 2 dwg