SU591024A1 - Gas turbine drive control system - Google Patents

Description

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FIELD OF THE INVENTION The invention relates to the field of a & tomobile regulation of driven gas turbine plants.

A gas turbine drive control system is known, comprising a process variable control, a non-linear link, a main speed controller of the output drive shaft, and a gas temperature controller Jlj.

However, it does not provide a high accuracy of stabilization of the rotational speed, since the control is performed by acting on the setters of the temperature regulators.

The purpose of the invention is to improve accuracy.

This is achieved by the fact that the system is equipped with an additional rotational frequency regulator and a selector, successively installed through a non-linear link at the output of the technological parameter controller, and a feedback sensor on the position of the regulating laser is connected to the selector The last and main frequency regulator of the frequency is the adder to which the feedback sensor is connected.

The drawing shows a schematic diagram of a gas turbine drive control system.

The contour of the first stage of gas turbine drive control 1 consists of a rotation speed sensor 2, a main rotation speed regulator 3, a servo drive 4 of a fuel regulating valve, a main regulator 3 setting device 5. controller 7, setpoint adjuster 8 of the limit temperature, and from the rotational speed control loop, containing the rotational speed sensor 9 and the additional speed regulator 1O, as well as from a process parameter controller 11 connected to the controller 10 by a nonlinear link 12. The matching elements of the first and second stages of the control are the selector 13, the adder 14, and the feedback sensor 15 for the position of the fuel regulating valve.

Sutema works as follows

The nonlinear link 12 s is limited by the characteristic of any known method, for example by connecting the technological parameter controller 11 to the selector and the on-voltage source with a signal corresponding to the required level of rotation limitation of the gas turbine drive. The minimum selector 13, if the positive output of the regulators 7 and 10 corresponds to the opening of the fuel control valve, is used to select the control channel through which the signal passes, which corresponds to the smallest opening of the fuel control valve. The system provides stabilization of one of the three parameters of a gas turbine engine: a technological parameter, a maximum rotation frequency, or a maximum gas temperature in front of the turbine.

When stabilizing the technological parameter, the output signal of the regulator

11passes through a non-linear link

12 (since the temperature limit is not reached) and as a setpoint is fed to the input of the additional controller 10 rotational frequency. The output of the regulator 1O, which is the difference between the output signal of the nonlinear link 12 and the signal of the rotational speed sensor 9, passes through the selector 13 (the output signal of the regulator 7 exceeds the controller s regulator Yu, since the limit value of the gas temperature is not reached ), goes to the adder 14 and together with the signal of the sensor 15 feedback

on the position of the fuel regulating valve is fed to the input of the setting device 5

of the main regulator 3 of the frequency of the gadget.

 drive. When reaching the maximum gas temperature in front of the turbine ,; corresponding to the setpoint of the setting device 8, the signal of the regulator 7 becomes less than the output signal of the regulator and, passing through the selector 13, is processed by the elements of the contour of the first cascade of regulation. This achieves a stabilization of the limiting gas temperature.

Such a gas turbine drive control system improves the accuracy of the stabilization of parameters.

Claims (1)

1. USSR author's certificate N9 455327, cl. G 05 D 16/20, 1972.