Gas turbine online simulation system

Abstract

The invention belongs to the technical field of gas turbine simulation control, and particularly relates to a gas turbine online simulation system. Comprising a gas turbine mathematical model generation module and a gas turbine online simulation module. The gas turbine mathematical model generation module is used for generating a mathematical model of each component in a gas turbine circulating system, establishing an access channel of input parameters and the mathematical model, and giving preset mathematical model parameters or environmental parameters according to the model and simulation content of a gas turbine selected during online simulation; the data acquisition assembly is used for acquiring simulation body data; the gas turbine simulation unit is used for creating simulation action parameters and environment parameters of different operations of the gas turbine; the system is used for realizing parameterized expression and simulation of the controllable gas turbine, realizes customization and practical training of dynamic practical training contents by using the gas turbine online simulation module, and can be used for meeting the requirements of online debugging simulation of various types of gas turbines and college training teaching.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine simulation control, and in particular relates to an online simulation system for a gas turbine. Background Art

[0002] Gas turbines are an important part of modern ship power systems. They burn compressed air and fuel at high temperatures in the combustion chamber, and drive turbines and other devices through high pressure to complete power output. They can be used as the main output of various large and medium-sized ships' power systems. The design and manufacture of gas turbines involve all aspects of the manufacturing industry. After each gas turbine is produced, it is necessary to carry out necessary simulation, debugging and testing, which involves a lot of debugging and simulation content. At present, there is a lack of sufficiently reliable practical teaching measures to meet the needs of gas turbine training and teaching. Summary of the invention

[0003] The object of the present invention is to provide a gas turbine online simulation system which can be used for training and teaching of gas turbine commissioning and the like.

[0004] To achieve the above purpose, the present invention adopts the following technical solution.

[0005] A gas turbine online simulation system comprises a gas turbine mathematical model generation module and a gas turbine online simulation module;

[0006] The gas turbine mathematical model generation module is used to generate mathematical models of various components in the gas turbine cycle system, establish access channels between input parameters and mathematical models, and set preset mathematical model parameters or environmental parameters according to the gas turbine model and simulation content selected during online simulation; the mathematical models include compressor mathematical models, combustion chamber mathematical models, turbine characteristic mathematical models, inertia mathematical models, circulation supply system mathematical models, and circulation control system mathematical models;

[0007] The gas turbine online simulation module includes a gas turbine simulation body, a data acquisition component, and a simulation setting component;

[0008] The gas turbine simulation body is used to create a gas turbine simulation unit including the cycle system, compressor and turbine;

[0009] The data acquisition component is used to collect simulation volume data, including: a sensor for collecting the temperature and pressure of the inlet and outlet sides of the gas turbine regenerator, a sensor for collecting the outlet pressure, outlet temperature and output power of the compressor, a sensor for collecting the inlet temperature, flow rate, combustion temperature and pressure of the gas turbine, and a controller for collecting control data of the gas turbine control system;

[0010] The gas turbine simulation unit is used to create simulation action parameters and environmental parameters of different operations of the gas turbine; the different operations include gas turbine startup operation, gas turbine shutdown operation, and gas turbine load adjustment operation.

[0011] A further improvement or preferred implementation of the above-mentioned gas turbine online simulation system is that in the gas turbine mathematical model generation module, the compressor mathematical model is composed of a compressor power mathematical model and a compressor characteristic mathematical model;

[0012] Compressor dynamic mathematical model including compressor speed prediction model Compressor flow prediction model Compressor Pressure Ratio Prediction Model Compressor Efficiency Prediction Model

[0013] Compressor speed prediction model It can be expressed as:

[0014] Where r represents the rotation speed, represents the predicted speed, r d represents the design speed, R refers to the fuel gas constant, T refers to the fuel combustion temperature, R d Refers to the compressor design gas constant, T d It refers to the compressor design combustion temperature;

[0015] Compressor flow prediction model It can be expressed as:

[0016] where q m is the mass flow rate, is the predicted mass flow rate, p is the compressor pressure, and p d It refers to the compressor design pressure;

[0017] Compressor Pressure Ratio Prediction Model It can be expressed as:

[0018] Where π is the compressor subratio, Refers to the predicted compressor pressure ratio, π d It refers to the compressor design pressure ratio;

[0019] Compressor Efficiency Prediction Model It can be expressed as:

[0020] Where η represents the compressor efficiency, represents the predicted compressor efficiency, η d It refers to the compressor design efficiency;

[0021] The mathematical model of compressor characteristics can be expressed as:

[0022]

[0023] Where m(p line ) represents the compressor flow inlet and outlet pressure characteristic curve, where m(p tran ) represents the compressor efficiency and speed characteristic model, T a is the air temperature, where η c Refers to the compressor cold side efficiency, η max The maximum efficiency of the compressor. It refers to the predicted speed at which the compressor reaches maximum efficiency.

[0024] In a further improvement or preferred embodiment of the above-mentioned gas turbine online simulation system, in the gas turbine mathematical model generation module, the turbine characteristic mathematical model can be expressed as:

[0025]

[0026] Where TP1 represents the characteristic equation when the turbine expansion ratio is greater than the critical expansion ratio; Where TP2 represents the characteristic equation when the turbine expansion ratio is less than the critical expansion ratio; Where the critical expansion ratio CER can be expressed as

[0027]

[0028] where q m.in is the mass flow rate at the turbine inlet, T in refers to the gas temperature at the turbine inlet side, p in refers to the gas pressure at the turbine inlet side, p out Refers to the gas pressure at the turbine outlet, S in It refers to the cross-sectional area of ​​the flow passage at the turbine inlet side; γ is the specific heat ratio of the gas;

[0029] The mathematical model of the combustion chamber can be expressed as:

[0030]

[0031] RS p Refers to the combustion chamber pressure characteristic model, where RS en refers to the combustion chamber energy characteristic model; Δp represents the pressure difference before and after the combustion chamber; q m.out Refers to the mass flow rate at the combustion chamber outlet; m cc refers to the molar heat of fuel; where q a Refers to the air flow rate; h a refers to the specific enthalpy of air; q f Refers to the gas flow rate; h f Q is the specific enthalpy of the gas;f Refers to the heat transfer of gas; η com Refers to the combustion efficiency of the combustion chamber; h out Refers to the specific enthalpy of the gas at the combustion chamber outlet; c p.out It refers to the specific heat capacity at the outlet side of the combustion chamber; t refers to time.

[0032] A further improvement or preferred implementation of the above-mentioned gas turbine online simulation system, in the gas turbine mathematical model generation module, the inertia mathematical model includes a volumetric inertia mathematical model and a thermal inertia mathematical model;

[0033] The volumetric inertia mathematical model is used to establish the overall volumetric inertia model caused by the volume effect of the compressor and combustion chamber and the flow resistance effect, which can be expressed as V' refers to the volume of the compressor or combustion chamber, p i ' n Refers to the intake pressure of the compressor or combustion chamber, q′ m.in Refers to the mass flow rate at the inlet side of the compressor or combustion chamber, q′ m.out It refers to the mass flow rate at the outlet of the compressor or combustion chamber;

[0034] The thermal inertia mathematical model is used to establish the thermal inertia mathematical model of the compressor and combustion chamber due to their own structural heat dissipation and energy transfer, which can be expressed as

[0035] Where α represents the heat transfer coefficient, T in ' refers to the intake side temperature of the compressor or combustion chamber, T o ' ut Refers to the temperature of the exhaust side of the compressor or combustion chamber, T m ' etal refers to the given inertial control temperature; c′ p It refers to the specific heat capacity of the compressor or combustion chamber;

[0036] The mathematical model of shaft rotation inertia is used to establish the overall shaft rotation inertia of the gas turbine rotor, compressor and turbine, which can be expressed as Where J is the moment of inertia, ω is the angular velocity, M0 is the torque of the drive motor, and M T is the turbine torque, M C It refers to the compressor torque.

[0037] A further improvement or preferred embodiment of the above-mentioned gas turbine online simulation system, in the gas turbine mathematical model generation module, the circulating supply system mathematical model is used to establish a mathematical model of the dynamic delay characteristics of the fuel supply system, which can be expressed as Where ψ refers to the valve opening index, ψ set Refers to the valve opening index setting value, tlate It refers to the valve delay time;

[0038] The mathematical model of the cyclic control system is used to establish the calculated value y of the speed controller, temperature controller and acceleration controller calc With the output value y output The relationship between can be expressed as:

[0039]

[0040] y P The proportional term is used to process the effect of the error signal on the controller calculation value and

[0041]

[0042] y I represents the integral term and y D represents the derivative control term, where θ refers to the controller bias, φ represents the controller gain value, and y max refers to the maximum output of the controller, y min Refers to the minimum output of the controller; y man It refers to the maximum output of the controller given manually; v is the controlled quantity, v set is the target value of the controlled variable, v max Indicates the maximum value of the controlled quantity, v min It refers to the minimum value of the controlled quantity.

[0043] A further improvement or preferred implementation of the above-mentioned gas turbine online simulation system, wherein the gas turbine startup operation specifically includes: setting a preset power generation power, completing startup simulation and performing a preset speed step-by-step speed increase test, performing a preset speed step-by-step speed reduction test, completing ignition simulation and performing a preset maximum speed step-by-step speed increase test, and completing a continuous operation test at a preset power generation speed;

[0044] The gas turbine shutdown operation specifically includes: completing shutdown simulation, confirming shutdown and performing fuel system automatic reduction test, completing gas turbine load automatic degradation test, and completing gas turbine inertia off-grid shutdown test;

[0045] The gas turbine load regulation operation specifically includes: completing different power generation regulation tests and completing various parameter recording tests during the regulation process.

[0046] Its beneficial effects are:

[0047] This application uses a mathematical model generation module to construct mathematical models of various components in the gas turbine cycle system to achieve parametric expression and simulation of controllable gas turbines, and uses a gas turbine online simulation module to achieve customization and training of dynamic training content, which can be used to meet the needs of online debugging simulation of various types of gas turbines and college training and teaching. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 It is a schematic diagram of the composition of the gas turbine online simulation system. DETAILED DESCRIPTION

[0049] The present invention is described in detail below in conjunction with specific embodiments.

[0050] The gas turbine online simulation system of the present invention is mainly used for gas turbine training and teaching as well as for simulation analysis and simulation debugging test of gas turbine structure, operation status and operation process during debugging and testing, so as to improve the knowledge reserve of trainees before actual operation and simplify the complexity of practical training and debugging and testing work.

[0051] like Figure 1 As shown, a gas turbine online simulation system of the present invention mainly includes two main parts: a gas turbine mathematical model generation module and a gas turbine online simulation module;

[0052] Among them, the gas turbine mathematical model generation module is used to generate mathematical models of various components in the gas turbine cycle system, establish access channels between input parameters and mathematical models, and give preset mathematical model parameters or environmental parameters according to the gas turbine model and simulation content selected during online simulation;

[0053] In this embodiment, the mathematical model used to establish a complete gas turbine includes a compressor mathematical model, a combustion chamber mathematical model, a turbine characteristic mathematical model, an inertia mathematical model, a circulation supply system mathematical model, and a circulation control system mathematical model;

[0054] The gas turbine online simulation module includes a gas turbine simulation body, a data acquisition component, and a simulation setting component;

[0055] The gas turbine simulation body is used to create a gas turbine simulation unit including the cycle system, compressor and turbine;

[0056] The data acquisition component is used to collect simulation data and build a simulation of the gas turbine data acquisition system. It serves as a data output terminal and an interactive window to establish a simulation expression with the actual data acquisition system during the training and debugging process. Its necessary contents include: sensors for collecting the temperature and pressure of the inlet and outlet sides of the gas turbine regenerator, sensors for collecting the compressor outlet pressure, outlet temperature, and output power, sensors for collecting the gas turbine inlet temperature, flow, combustion temperature, and pressure, and controllers for collecting control data of the gas turbine control system;

[0057] The gas turbine simulation unit is used to create simulation action parameters and environmental parameters of different operations of the gas turbine; the different operations include gas turbine startup operation, gas turbine shutdown operation, and gas turbine load adjustment operation.

[0058] In the gas turbine mathematical model generation module, the compressor mathematical model is composed of the compressor dynamic mathematical model and the compressor characteristic mathematical model;

[0059] Compressor dynamic mathematical model including compressor speed prediction model Compressor flow prediction model Compressor Pressure Ratio Prediction Model Compressor Efficiency Prediction Model

[0060] Compressor speed prediction model It can be expressed as:

[0061] Where r represents the rotation speed, represents the predicted speed, r d represents the design speed, R refers to the fuel gas constant, T refers to the fuel combustion temperature, R d Refers to the compressor design gas constant, T d It refers to the compressor design combustion temperature;

[0062] Compressor flow prediction model It can be expressed as:

[0063] where q m is the mass flow rate, is the predicted mass flow rate, p is the compressor pressure, and p d It refers to the compressor design pressure;

[0064] Compressor Pressure Ratio Prediction Model It can be expressed as:

[0065] Where π is the compressor subratio, Refers to the predicted compressor pressure ratio, πd It refers to the compressor design pressure ratio;

[0066] Compressor Efficiency Prediction Model It can be expressed as:

[0067] Where η represents the compressor efficiency, represents the predicted compressor efficiency, η d It refers to the compressor design efficiency;

[0068] The mathematical model of compressor characteristics can be expressed as:

[0069]

[0070] Where m(p line ) represents the compressor flow inlet and outlet pressure characteristic curve, where m(p tran ) represents the compressor efficiency and speed characteristic model, T a is the air temperature, where η c Refers to the compressor cold side efficiency, η max The maximum efficiency of the compressor. It refers to the predicted speed at which the compressor reaches maximum efficiency.

[0071] In the gas turbine mathematical model generation module, the turbine characteristic mathematical model can be expressed as:

[0072]

[0073] Where TP1 represents the characteristic equation when the turbine expansion ratio is greater than the critical expansion ratio; Where TP2 represents the characteristic equation when the turbine expansion ratio is less than the critical expansion ratio; Where the critical expansion ratio CER can be expressed as

[0074]

[0075] where q m.in is the mass flow rate at the turbine inlet, T in refers to the gas temperature at the turbine inlet side, p in refers to the gas pressure at the turbine inlet side, p out Refers to the gas pressure at the turbine outlet, S in It refers to the cross-sectional area of ​​the flow passage at the turbine inlet side; γ is the specific heat ratio of the gas;

[0076] The mathematical model of the combustion chamber can be expressed as:

[0077]

[0078] RS p Refers to the combustion chamber pressure characteristic model, where RS enrefers to the combustion chamber energy characteristic model; Δp represents the pressure difference before and after the combustion chamber; q m.out Refers to the mass flow rate at the combustion chamber outlet; m cc refers to the molar heat of fuel; where q a Refers to the air flow rate; h a refers to the specific enthalpy of air; q f Refers to the gas flow rate; h f Q is the specific enthalpy of the gas; f Refers to the heat transfer of gas; η com Refers to the combustion efficiency of the combustion chamber; h out Refers to the specific enthalpy of the gas at the combustion chamber outlet; c p.out It refers to the specific heat capacity at the outlet side of the combustion chamber; t refers to time.

[0079] In the gas turbine mathematical model generation module, the inertia mathematical model includes a volumetric inertia mathematical model and a thermal inertia mathematical model;

[0080] The volumetric inertia mathematical model is used to establish the overall volumetric inertia model caused by the volume effect of the compressor and combustion chamber and the flow resistance effect, which can be expressed as V' refers to the volume of the compressor or combustion chamber, p i ' n Refers to the intake pressure of the compressor or combustion chamber, q′ m.in Refers to the mass flow rate at the inlet side of the compressor or combustion chamber, q′ m.out It refers to the mass flow rate at the outlet of the compressor or combustion chamber;

[0081] The thermal inertia mathematical model is used to establish the thermal inertia mathematical model of the compressor and combustion chamber due to their own structural heat dissipation and energy transfer, which can be expressed as

[0082] Where α represents the heat transfer coefficient, T in ' refers to the intake side temperature of the compressor or combustion chamber, T o ' ut Refers to the temperature of the exhaust side of the compressor or combustion chamber, T m ' etal refers to the given inertial control temperature; c′ p It refers to the specific heat capacity of the compressor or combustion chamber;

[0083] The mathematical model of shaft rotation inertia is used to establish the overall shaft rotation inertia of the gas turbine rotor, compressor and turbine, which can be expressed as Where J is the moment of inertia, ω is the angular velocity, M0 is the torque of the drive motor, and M T is the turbine torque, M C It refers to the compressor torque.

[0084] In the gas turbine mathematical model generation module, the cycle supply system mathematical model is used to establish the mathematical model of the dynamic delay characteristics of the fuel supply system, which can be expressed as Where ψ refers to the valve opening index, ψ set Refers to the valve opening index setting value, t late It refers to the valve delay time;

[0085] The mathematical model of the cyclic control system is used to establish the calculated value y of the speed controller, temperature controller and acceleration controller calc With the output value y output The relationship between can be expressed as:

[0086]

[0087] y P The proportional term is used to process the effect of the error signal on the controller calculation value and

[0088]

[0089] y I represents the integral term and y D represents the derivative control term, where θ refers to the controller bias, φ represents the controller gain value, and y max refers to the maximum output of the controller, y min Refers to the minimum output of the controller; y man It refers to the maximum output of the controller given manually; v is the controlled quantity, v set is the target value of the controlled variable, v max Indicates the maximum value of the controlled quantity, v min It refers to the minimum value of the controlled quantity.

[0090] The gas turbine startup operation specifically includes: setting the preset power generation, completing the startup simulation and performing a preset speed step-by-step speed increase test, performing a preset speed step-by-step speed reduction test, completing the ignition simulation and performing a preset maximum speed step-by-step speed increase test, and completing a continuous operation test at the preset power generation speed;

[0091] The gas turbine shutdown operation specifically includes: completing the shutdown simulation, confirming the shutdown and conducting the fuel system automatic reduction test, completing the gas turbine load automatic degradation test, and completing the gas turbine inertia off-grid shutdown test;

[0092] The gas turbine load regulation operation specifically includes: completing different power generation adjustment tests and completing various parameter recording tests during the adjustment process.

[0093] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention, rather than to limit the scope of protection of the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the essence and scope of the technical solution of the present invention.

Claims

1. A gas turbine online simulation system, characterized in that: It includes gas turbine mathematical model generation module and gas turbine online simulation module; The gas turbine mathematical model generation module is used to generate mathematical models of various components in the gas turbine cycle system, establish access channels between input parameters and mathematical models, and set preset mathematical model parameters or environmental parameters according to the gas turbine model and simulation content selected during online simulation; the mathematical models include compressor mathematical models, combustion chamber mathematical models, turbine characteristic mathematical models, aftercooler mathematical models, circulation supply system mathematical models, and circulation control system mathematical models; The gas turbine online simulation module includes a gas turbine simulation body, a data acquisition component, and a simulation setting component; The gas turbine simulation body is used to create a gas turbine simulation unit including the cycle system, compressor and turbine; The data acquisition component is used to collect simulation volume data, including: a sensor for collecting the temperature and pressure of the inlet and outlet sides of the gas turbine regenerator, a sensor for collecting the outlet pressure, outlet temperature and output power of the compressor, a sensor for collecting the inlet temperature, flow rate, combustion temperature and pressure of the gas turbine, and a controller for collecting control data of the gas turbine control system; The gas turbine simulation unit is used to create simulation action parameters and environmental parameters of different operations of the gas turbine; the different operations include gas turbine startup operation, gas turbine shutdown operation, and gas turbine load adjustment operation.

2. The gas turbine online simulation system according to claim 1, characterized in that: In the gas turbine mathematical model generation module, the compressor mathematical model is composed of a compressor power mathematical model and a compressor characteristic mathematical model; Compressor dynamic mathematical model including compressor speed prediction model Compressor flow prediction model Compressor Pressure Ratio Prediction Model Compressor Efficiency Prediction Model Compressor speed prediction model It can be expressed as: Where r represents the rotation speed, represents the predicted speed, r d represents the design speed, R refers to the fuel gas constant, T refers to the fuel combustion temperature, R d Refers to the compressor design gas constant, T d It refers to the compressor design combustion temperature; Compressor flow prediction model It can be expressed as: where q m is the mass flow rate, is the predicted mass flow rate, p is the compressor pressure, and p d It refers to the compressor design pressure; Compressor Pressure Ratio Prediction Model It can be expressed as: Where π is the compressor subratio, Refers to the predicted compressor pressure ratio, π d It refers to the compressor design pressure ratio; Compressor Efficiency Prediction Model It can be expressed as: Where η represents the compressor efficiency, represents the predicted compressor efficiency, η d It refers to the compressor design efficiency; The mathematical model of compressor characteristics can be expressed as: Where m(p line ) represents the compressor flow inlet and outlet pressure characteristic curve, where m(p tran ) represents the compressor efficiency and speed characteristic model, T a is the air temperature, where η c Refers to the compressor cold side efficiency, η max The maximum efficiency of the compressor. It refers to the predicted speed at which the compressor reaches maximum efficiency.

3. The gas turbine online simulation system according to claim 1, characterized in that: In the gas turbine mathematical model generation module, the turbine characteristic mathematical model can be expressed as: Where TP1 represents the characteristic equation when the turbine expansion ratio is greater than the critical expansion ratio; Where TP2 represents the characteristic equation when the turbine expansion ratio is less than the critical expansion ratio; Where the critical expansion ratio CER can be expressed as where q m.in is the mass flow rate at the turbine inlet, T in refers to the gas temperature at the turbine inlet side, p in refers to the gas pressure at the turbine inlet side, p out Refers to the gas pressure at the turbine outlet, S in It refers to the cross-sectional area of ​​the flow passage at the turbine inlet side; γ is the specific heat ratio of the gas; The mathematical model of the combustion chamber can be expressed as: RS p Refers to the combustion chamber pressure characteristic model, where RS en It refers to the combustion chamber energy characteristic model; Δp represents the pressure difference before and after the combustion chamber; q m.out Refers to the mass flow rate at the combustion chamber outlet; m cc refers to the molar heat of fuel; where q a Refers to the air flow rate; h a refers to the specific enthalpy of air; q f Refers to the gas flow rate; h f Q is the specific enthalpy of the gas; f Refers to the heat transfer of gas; η com Refers to the combustion efficiency of the combustion chamber; h out Refers to the specific enthalpy of the gas at the combustion chamber outlet; c p.out It refers to the specific heat capacity at the outlet side of the combustion chamber; t refers to time.

4. The gas turbine online simulation system according to claim 1, characterized in that: In the gas turbine mathematical model generation module, the inertia mathematical model includes a volumetric inertia mathematical model and a thermal inertia mathematical model; The volumetric inertia mathematical model is used to establish the overall volumetric inertia model caused by the volume effect of the compressor and combustion chamber and the flow resistance effect, which can be expressed as V' refers to the volume of the compressor or combustion chamber, p i ' n Refers to the intake pressure of the compressor or combustion chamber, q′ m.in Refers to the mass flow rate at the inlet side of the compressor or combustion chamber, q′ m.out It refers to the mass flow rate at the outlet of the compressor or combustion chamber; The thermal inertia mathematical model is used to establish the thermal inertia mathematical model of the compressor and combustion chamber due to their own structural heat dissipation and energy transfer, which can be expressed as Where α represents the heat transfer coefficient, T in ' refers to the intake side temperature of the compressor or combustion chamber, T o ' ut Refers to the temperature of the exhaust side of the compressor or combustion chamber, T m ' etal refers to the given inertial control temperature; c′ p It refers to the specific heat capacity of the compressor or combustion chamber; The mathematical model of shaft rotation inertia is used to establish the overall shaft rotation inertia of the gas turbine rotor, compressor and turbine, which can be expressed as Where J is the moment of inertia, ω is the angular velocity, M0 is the torque of the drive motor, and M T is the turbine torque, M C It refers to the compressor torque.

5. The gas turbine online simulation system according to claim 1, characterized in that: In the gas turbine mathematical model generation module, the circulating supply system mathematical model is used to establish a mathematical model of the dynamic delay characteristics of the fuel supply system, which can be expressed as Where ψ refers to the valve opening index, ψ set Refers to the valve opening index setting value, t late It refers to the valve delay time; The mathematical model of the cyclic control system is used to establish the calculated value y of the speed controller, temperature controller and acceleration controller calc With the output value y output The relationship between them can be expressed as: y P The proportional term is used to process the effect of the error signal on the controller calculation value and y I represents the integral term and y D represents the derivative control term, where θ refers to the controller bias, φ represents the controller gain value, and y max refers to the maximum output of the controller, y min Refers to the minimum output of the controller; y man It refers to the maximum output of the controller given manually; v is the controlled quantity, v set is the target value of the controlled variable, v max Indicates the maximum value of the controlled quantity, v min It refers to the minimum value of the controlled quantity.

6. The gas turbine online simulation system according to claim 1, characterized in that: The gas turbine startup operation specifically includes: setting a preset power generation power, completing a startup simulation and performing a preset speed step-by-step speed increase test, performing a preset speed step-by-step speed reduction test, completing an ignition simulation and performing a preset maximum speed step-by-step speed increase test, and completing a continuous operation test at a preset power generation speed; The gas turbine shutdown operation specifically includes: completing shutdown simulation, confirming shutdown and performing fuel system automatic reduction test, completing gas turbine load automatic degradation test, and completing gas turbine inertia off-grid shutdown test; The gas turbine load regulation operation specifically includes: completing different power generation regulation tests and completing various parameter recording tests during the regulation process.

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