RU2006114247A - METHOD FOR GAS-TURBINE ENGINE CONTROL - Google Patents

Claims (4)

1. A method for controlling a gas turbine engine, in which the air parameters are measured: temperature and pressure at the engine inlet, engine pressure and engine rotor speed with respective temperature, pressure and speed sensors, and the engine is controlled in accordance with an algorithm using signals sensors of air inlet parameters for generating setpoints of adjustable parameters of the automatic control system, characterized in that in case of failure of any one of the sensors of the air parameters at the engine inlet, a "virtual" measurement of the signal of the failed sensor is carried out, for which a functional relationship between the pressure in the engine and the rotational speed in the given coordinates is preliminarily formed, and the ratios are used for reduction: for the pressure, the ratio P _CR = 1.033 P / P _1, where P _CR is the reduced value of the engine pressure, P is the pressure in the engine, P ₁ is the air pressure, and to bring the rotation speed, the ratio

, where n _pr is the reduced value of the rotational speed, n is the rotational speed, T ₁ is the inlet air temperature, and, when "measuring" the signal of the failed sensor, they first determine the reduced value of one of these parameters by the signal from the working inlet air parameter sensor into the engine, determine the corresponding value of the other reduced parameter according to the functional dependence and enter its value into another ratio for reduction, and then calculate the value of the signal of the failed sensor and the calculated value The rate is introduced into the automatic control system for the formation of predetermined values of the adjustable parameters. 2. The method according to claim 1, characterized in that for gas turbine engines with variable geometry of the flow part by changing the position of the regulatory body, for example, compressor guide vanes, the functional dependence in the given coordinates is formed at different positions of the regulatory bodies, in the form of a family of curves or analytical dependence, and with a "virtual" measurement of the signal of the failed sensor, the current position of the regulatory body is additionally measured and the "virtual" measurement of the response signal is determined sensor at the measured position of the regulatory body. 3. The method according to claim 1, characterized in that in case of failure of the air temperature sensor at the engine inlet, first, the reduced value is calculated by the ratio for bringing P _pr = 1,033P / P ₁ , which contains the measured air pressure parameter at the engine inlet, pressure determine the corresponding value of P _{CR the} given value of the rotational speed n _CR functional dependence and enter it into the ratio to bring

and then, from the same ratio, the signal value of the failed temperature sensor at the inlet to the engine is calculated by the formula T ₁ = 288 (n / n _pr ) ² , and the calculated value of T ₁ is entered into the automatic control system to generate the specified values of the adjustable parameters 4. The method according to claim 1, characterized in that in case of failure, the air pressure sensor at the engine inlet, first in relation to bring

, which contains the measured parameter of the air temperature at the engine inlet, calculate the value of the reduced speed. determine a reduced value corresponding to n _ave given pressure value P _ave by functional dependencies, and it is administered in relation to bring P _ave = 1,033R / P _1, and then calculating therefrom the value of the failed pressure transducer at input to the engine ₁ according to the formula P = 1.033 P / P _ol , and the calculated value of P ₁ is introduced into the automatic control system to form the set values of the adjustable parameters.