CN-122014427-A - Heavy gas turbine active disturbance rejection control method, electronic equipment and storage medium

CN122014427ACN 122014427 ACN122014427 ACN 122014427ACN-122014427-A

Abstract

The invention provides an active disturbance rejection control method of a heavy gas turbine, electronic equipment and a storage medium. The method comprises the steps of establishing a two-input and multi-output state space model of the heavy-duty gas turbine, performing high-order full-drive system model conversion on the two-input and multi-output state space model to decouple the two-input and multi-output state space model into an exhaust temperature subsystem model and a power generation subsystem model, establishing an exhaust temperature ideal control law and a power generation power ideal control law according to the exhaust temperature subsystem model and the power generation subsystem model respectively, and controlling the heavy-duty gas turbine at least by using the exhaust temperature ideal control law and the power generation power ideal control law. The method can improve the operation stability of the heavy-duty gas turbine.

Inventors

HUANG CONGZHI
LIU REN
HOU GUOLIAN
Tan Xiangshuai

Assignees

华北电力大学

Dates

Publication Date: 20260512
Application Date: 20260330

Claims (10)

1. A heavy gas turbine auto-disturbance rejection control method, comprising: establishing a two-input multi-output state space model of the heavy-duty gas turbine; performing high-order full-drive system model conversion on the two-input multi-output state space model to decouple the two-input multi-output state space model into an exhaust temperature subsystem model and a power generation subsystem model; Establishing an ideal exhaust temperature control law and an ideal power generation power control law according to the exhaust temperature subsystem model and the power generation power subsystem model respectively; the heavy duty gas turbine is controlled using at least the exhaust gas temperature ideal control law and the generated power ideal control law.
2. The method of claim 1, wherein the building a two-input, multiple-output state space model of a heavy gas turbine comprises: deducing a compressor, a combustion chamber and a turbine of the heavy-duty gas turbine to obtain the two-input-multiple-output state space model; wherein the two-input multiple-output state space model is represented by the following expression: ; ; ; ; ; Wherein the state variables , Is the pressure in the combustion chamber and, Is the temperature of the combustion chamber and, Is the air flow rate, and the air flow rate, Is the flow rate of the fuel and, Is the exhaust temperature, input variable , Is the opening degree of the inlet guide vane, Is a fuel flow rate adjustment value; Is the combustion chamber volume; is the nominal combustion chamber pressure; is the rated combustion chamber temperature; Is the exhaust gas constant; Is the specific heat capacity of exhaust gas under constant pressure; Is the specific heat capacity of air at constant pressure; Is the low heating value of the fuel; Is an air constant; is ambient temperature; Is ambient pressure; is compressor efficiency; Is the adiabatic efficiency of the compressor; And The time constants of the inlet guide vanes and the fuel intake system respectively, And Is the gain; And Is a constant coefficient; Is the time constant of the exhaust gas temperature sensor; is the rated air flow rate of the compressor.
3. The method of claim 2, wherein the exhaust temperature subsystem model and the generated power subsystem model are represented by the following expressions: , ; Wherein, the , , , , And Representing the non-linear portions of the generated power subsystem and the exhaust temperature subsystem respectively, ; Representing generator efficiency; Wherein, the 。
4. A method according to any one of claims 1-3, wherein said establishing an exhaust temperature ideal control law and a generated power ideal control law from said exhaust temperature subsystem model and said generated power subsystem model, respectively, comprises: Based on the exhaust temperature subsystem model and the power generation subsystem model, respectively establishing a full-drive state model of the exhaust temperature subsystem and a full-drive state model of the power generation subsystem; Combining non-linearities and uncertain disturbances in the exhaust temperature subsystem and the generated power subsystem into a total disturbance; Rewriting a full drive state model of the exhaust temperature subsystem and the generated power subsystem based on the total disturbance; and respectively establishing control laws based on the rewritten full-driving state models of the exhaust temperature subsystem and the generating power subsystem.
5. The method of claim 4, wherein the full drive state model of the exhaust gas temperature subsystem and the full drive state model of the generation power subsystem may be represented by the following expressions: ; Wherein, the , , ; The rewritten full drive state model of the generation power subsystem and the exhaust temperature subsystem can be represented by the following expression: ; Wherein, the , ; The ideal control law of the electric power generation subsystem and the exhaust gas temperature subsystem is represented by the following expression: ; Wherein, the And Respectively representing a generated power tracking error and an exhaust gas temperature tracking error; And Preset values of the generated power and the exhaust temperature are respectively set; And Observations respectively representing the generated power and the exhaust temperature tracking error; And Respectively representing observed values of a second derivative and a third derivative of the exhaust temperature tracking error; And Respectively representing observed values of the total disturbance of the generating power subsystem and the total disturbance of the exhaust temperature subsystem; presetting a first derivative of a value for the generated power; the third derivative of the preset value is the exhaust temperature.
6. The method according to claim 4, wherein the method further comprises: Deducing the generated power tracking error and the exhaust temperature tracking error in the control law respectively to obtain the tracking error dynamic characteristics of the generated power subsystem and the exhaust temperature subsystem; Constructing linear expansion state observers of the power generation subsystem and the exhaust temperature subsystem according to the control laws and the tracking error dynamic characteristics of the power generation subsystem and the exhaust temperature subsystem respectively; Said controlling said heavy duty gas turbine using at least said exhaust gas temperature ideal control law and said generated power ideal control law, comprising: And carrying out real-time disturbance observation and compensation control on the power generation subsystem and the exhaust temperature subsystem of the heavy gas turbine by using the exhaust temperature ideal control law, the power generation power ideal control law and the linear expansion state observers of the power generation subsystem and the exhaust temperature subsystem.
7. The method of claim 6, wherein the tracking error dynamics of the generated power subsystem are represented by the following expression: ; The linear extended state observer of the generated power subsystem is represented by the following expression: ; Wherein, the Representing an estimate of the state variable s 1 , A gain vector representing a linear extended state observer of the generated power subsystem.
8. The method of claim 6, wherein the tracking error dynamics of the exhaust temperature subsystem are represented by the following expression: ; the linear extended state observer of the exhaust temperature subsystem is represented by the expression: ; Wherein, the Representing an estimate of the state variable s 2 , A gain vector representing a linear extended state observer of the exhaust temperature subsystem.
9. An electronic device comprising a processor and a memory, the memory having stored therein a computer program for executing the computer program to implement the method of any of claims 1-8.
10. A computer readable storage medium, characterized in that a computer program/instruction is stored, which, when executed by a processor, implements the method according to any of claims 1-8.

Description

Heavy gas turbine active disturbance rejection control method, electronic equipment and storage medium Technical Field The invention relates to the technical field of intelligent control of heavy gas turbines, in particular to an active disturbance rejection control method, electronic equipment and a storage medium of a heavy gas turbine. Background Along with the continuous evolution of global energy structures and the continuous increase of the installed capacity of renewable energy sources such as wind energy, solar energy and the like, the heavy-duty gas turbine is taken as a core component of the gas-steam combined cycle unit, and the key role in power grid adjustment and renewable energy source grid connection is increasingly highlighted. The heavy gas turbine has complex dynamic characteristics in the operation process, including strong nonlinearity, parameter time-varying, strong coupling and the like, and the traditional control method is difficult to realize quick and accurate response due to performance limitation, so that the control precision and response speed of the heavy gas turbine are often unsatisfactory. In view of this, the present invention has been made. Disclosure of Invention The invention aims to provide an active disturbance rejection control method, electronic equipment and a storage medium of a heavy gas turbine, which are used for solving the problems of nonlinear characteristics and uncertainty disturbance of the heavy gas turbine in the background art, and improving the peak regulation capacity of the heavy gas turbine, so that load fluctuation caused by grid connection of renewable energy sources is effectively handled. In order to achieve the above object, the present invention provides a heavy duty gas turbine active disturbance rejection control method, comprising: establishing a two-input multi-output state space model of the heavy-duty gas turbine; performing high-order full-drive system model conversion on the two-input multi-output state space model to decouple the two-input multi-output state space model into an exhaust temperature subsystem model and a power generation subsystem model; Establishing an ideal exhaust temperature control law and an ideal power generation power control law according to the exhaust temperature subsystem model and the power generation power subsystem model respectively; the heavy duty gas turbine is controlled using at least the exhaust gas temperature ideal control law and the generated power ideal control law. According to the technical scheme, the state space model of the heavy-duty gas turbine is converted into the high-order full-drive system model, decoupling of the system structure is achieved, the system structure is decomposed into two control subsystems with full-drive system characteristics, an ideal control law is further built based on a full-drive system method, and therefore intelligent active disturbance rejection control with flexible disturbance rejection capability can be achieved. The control method is superior to the traditional control method in precision, robustness and dynamic response, the nonlinear characteristic and the response capability of uncertain disturbance in a heavy gas turbine system are obviously improved, and the control method has outstanding dynamic performance and engineering adaptability. The method meets the dual requirements of the industrial field on quick deployment and high-reliability control, shows remarkable technical innovation and wide application prospect, is particularly suitable for complex industrial environments such as energy power, automatic control and the like, and has important technical value and practical significance. Illustratively, the building a two-input, multiple-output state space model of a heavy gas turbine includes: deducing a compressor, a combustion chamber and a turbine of the heavy-duty gas turbine to obtain the two-input-multiple-output state space model; wherein the two-input multiple-output state space model is represented by the following expression: ; ; ; ; ; Wherein the state variables ,Is the pressure of the combustion chamber in real time,Is the temperature of the combustion chamber in real time,Is the air flow rate, and the air flow rate,Is the flow rate of the fuel and,Is the exhaust temperature, input variable,Is the opening degree of the inlet guide vane,Is a fuel flow rate adjustment value; Is the combustion chamber volume; is the nominal combustion chamber pressure; is the rated combustion chamber temperature; Is the exhaust gas constant; Is the specific heat capacity of exhaust gas under constant pressure; Is the specific heat capacity of air at constant pressure; Is the low heating value of the fuel; Is an air constant; is ambient temperature; Is ambient pressure; is compressor efficiency; Is the adiabatic efficiency of the compressor; And The time constants of the inlet guide vanes and the fuel intake system respectively,AndIs the g