A gas turbine online simulation system

Abstract

The present invention belongs to the field of gas turbine simulation and control technology, and in particular relates to a gas turbine online simulation system. The system comprises a gas turbine mathematical model generation module and a gas turbine online simulation module. The gas turbine mathematical model generation module is used to generate mathematical models of various components within the gas turbine cycle system, establish access channels between input parameters and the mathematical model, and assign preset mathematical model parameters or environmental parameters based on the gas turbine model and simulation content selected during online simulation. The data acquisition component is used to collect simulation volume data. The gas turbine simulation unit is used to create simulation action parameters and environmental parameters for different gas turbine operations. The present application is used to achieve controllable gas turbine parameterized expression and simulation, and utilizes the gas turbine online simulation module to achieve customization and training of dynamic training content. This system can be used to meet the needs of online commissioning simulation and college training for various types of gas turbines.

Description

Technical Field

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

[0002] Gas turbines are a vital component of modern marine propulsion systems. They generate power through the high-temperature combustion of compressed air and fuel within a combustion chamber, driving turbines and other components through high pressure. They serve as the primary power source for various large and medium-sized vessels. The design and manufacture of gas turbines touches every aspect of the manufacturing industry. Each gas turbine undergoes necessary simulation, commissioning, and testing after production. This involves extensive debugging and simulation work, and currently, there is a lack of reliable practical training methods to meet the needs of gas turbine training. Summary of the Invention

[0003] The object of the present invention is to provide a gas turbine online simulation system that can be used to meet the training and teaching requirements of gas turbine commissioning and other contents.

[0004] To achieve the above objectives, the present invention adopts the following technical solutions.

[0005] A gas turbine online simulation system includes 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 based on the gas turbine model and simulation content selected during online simulation; the mathematical models include 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;

[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: sensors for collecting temperature and pressure on the inlet and outlet sides of the gas turbine regenerator, sensors for collecting compressor outlet pressure, outlet temperature, and output power, sensors for collecting gas turbine inlet temperature, flow, combustion temperature, and pressure, 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 gas turbine operations; the different operations include gas turbine startup operation, gas turbine shutdown operation, and gas turbine load adjustment operation.

[0011] A further improvement or preferred embodiment of the aforementioned gas turbine online simulation system is that in the gas turbine mathematical model generation module, the compressor mathematical model is composed of a compressor dynamic 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 cold side efficiency of the compressor, η max It refers to 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 aforementioned 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; TP2 represents the characteristic equation when the turbine expansion ratio is less than the critical expansion ratio; the critical expansion ratio CER can be expressed as

[0027]

[0028] where q m.in Refers to the mass flow rate at the turbine inlet side, 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 channel on the turbine inlet side; γ is the gas specific heat ratio;

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

[0030]

[0031] Among them, 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 Refers to the specific enthalpy of gas; Qf 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 refers to the specific heat capacity at the outlet side of the combustion chamber; t refers to time.

[0032] A further improvement or preferred embodiment of the aforementioned gas turbine online simulation system is 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;

[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 rotational inertia is used to establish the overall shaft rotational 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 driving motor, and M T Refers to the turbine torque, M C It refers to the compressor torque.

[0037] A further improvement or preferred embodiment of the aforementioned 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 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 and the output value y output The relationship between them 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 differential 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 Refers to the maximum output of the controller given manually; where 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 Refers to the minimum value of the controlled quantity.

[0043] A further improvement or preferred embodiment of the aforementioned gas turbine online simulation system, wherein 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 increase test, performing a preset speed step-by-step decrease test, completing an ignition simulation and performing a preset maximum speed step-by-step increase test, and completing a continuous operation test at a preset power generation speed;

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

[0045] The gas turbine load adjustment operation specifically includes: completing different power generation adjustment tests and completing various parameter recording tests during the adjustment 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 controllable gas turbine parametric expression and simulation, 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 and college training and teaching of various types of gas turbines. 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 with reference to specific embodiments.

[0050] The gas turbine online simulation system of the present invention is mainly used for simulation analysis and simulation debugging test of gas turbine structure, operating status and operating process during gas turbine training and teaching as well as 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] 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.

[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. During the training and debugging process, it serves as the data output terminal and interactive window to establish a simulation expression with the actual data acquisition system. Its necessary contents include: sensors for collecting the temperature and pressure on 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 a controller 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 gas turbine operations; 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 consists 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 cold side efficiency of the compressor, η max It refers to 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; TP2 represents the characteristic equation when the turbine expansion ratio is less than the critical expansion ratio; the critical expansion ratio CER can be expressed as

[0074]

[0075] where q m.in Refers to the mass flow rate at the turbine inlet side, 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 channel on the turbine inlet side; γ is the gas specific heat ratio;

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

[0077]

[0078] Among them, 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 Refers to the specific enthalpy of gas; Q 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 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 rotational inertia is used to establish the overall shaft rotational 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 driving motor, and M T Refers to 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 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 and the output value y output The relationship between them 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 differential 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 Refers to the maximum output of the controller given manually; where v is the controlled quantity, v set is the target value of the controlled quantity, v max Indicates the maximum value of the controlled quantity, v min Refers to the minimum value of the controlled quantity.

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

[0091] Gas turbine shutdown operations specifically include: completing shutdown simulation, confirming shutdown and conducting fuel system automatic reduction test, completing gas turbine load automatic degradation test, and completing 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 solutions 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 solutions of the present invention may be modified or replaced by equivalents without departing from the essence and scope of the technical solutions of the present invention.

Claims

1. A gas turbine online simulation system, characterized in that: Including 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 based on the gas turbine model and simulation content selected during online simulation; the mathematical models include a compressor mathematical model, a combustion chamber mathematical model, a turbine characteristic mathematical model, an aftercooler mathematical model, a cycle supply system mathematical model, and a cycle control system mathematical model; 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: sensors for collecting temperature and pressure on the inlet and outlet sides of the gas turbine regenerator, sensors for collecting compressor outlet pressure, outlet temperature, and output power, sensors for collecting gas turbine inlet temperature, flow, combustion temperature, and pressure, 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 for different gas turbine operations; the different operations include gas turbine startup operation, gas turbine shutdown operation, and gas turbine load adjustment operation; In the gas turbine mathematical model generation module, the compressor mathematical model is composed of a compressor dynamic 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: ; in Indicates the speed, represents the predicted speed, Indicates the design speed, is the fuel gas constant, The fuel combustion temperature, It refers to the compressor design gas constant, It refers to the compressor design combustion temperature; Compressor flow prediction model It can be expressed as: ; in is the mass flow rate, is the predicted mass flow rate, is the compressor pressure, It refers to the compressor design pressure; Compressor pressure ratio prediction model It can be expressed as: ; in is the compressor pressure ratio, It refers to the predicted compressor pressure ratio, It refers to the compressor design pressure ratio; Compressor Efficiency Prediction Model It can be expressed as: ; in represents the compressor efficiency, represents the predicted compressor efficiency, It refers to the compressor design efficiency; The mathematical model of compressor characteristics can be expressed as: ； in Represents the compressor flow inlet and outlet pressure characteristic curve, where represents the compressor efficiency and speed characteristic model, is the air temperature, where It refers to the cold side efficiency of the compressor. It refers to the maximum efficiency of the compressor. It refers to the predicted speed at which the compressor reaches maximum efficiency.

2. 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: ； in The characteristic equation when the turbine expansion ratio is greater than the critical expansion ratio is represented by: The characteristic equation when the turbine expansion ratio is less than the critical expansion ratio is expressed as It can be expressed as ; in is the mass flow rate at the turbine inlet side, is the gas temperature at the turbine inlet side, It refers to the gas pressure at the turbine inlet side, Refers to the gas pressure at the turbine outlet side, It refers to the cross-sectional area of ​​the flow passage on the turbine inlet side; is the ratio of specific heats of gases; The mathematical model of the combustion chamber can be expressed as: ； in Refers to the combustion chamber pressure characteristic model, where It refers to the combustion chamber energy characteristic model; Indicates the pressure difference before and after the combustion chamber; Refers to the mass flow rate at the combustion chamber outlet; is the molar heat of fuel; It refers to the air flow rate; is the specific enthalpy of air; Refers to the gas flow rate; It refers to the specific enthalpy of gas; Refers to the heat transfer of gas; Refers to the combustion efficiency of the combustion chamber; It refers to the specific enthalpy of the gas at the combustion chamber outlet; It refers to the specific heat capacity at the combustion chamber outlet side; It refers to time.

3. 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 ; It refers to the volume of the compressor or combustion chamber. It refers to the intake pressure of the compressor or combustion chamber. Refers to the mass flow rate at the inlet side of the compressor or combustion chamber, 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 ; in represents the heat transfer coefficient, It refers to the temperature on the intake side of the compressor or combustion chamber. It refers to the temperature at the outlet side of the compressor or combustion chamber. is the given inertial control temperature; It refers to the specific heat capacity of the compressor or combustion chamber; The mathematical model of shaft rotational inertia is used to establish the overall shaft rotational inertia of the gas turbine rotor, compressor, and turbine, which can be expressed as ;in is the moment of inertia, is the angular velocity, Refers to the torque of the driving motor, is the turbine torque, It refers to the compressor torque.

4. 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 ;in Refers to the valve opening index, Refers to the valve opening index setting value, Refers to the valve delay time; The mathematical model of the cyclic control system is used to establish the calculated values ​​of the speed controller, temperature controller and acceleration controller With the output value The relationship between them can be expressed as: ； The proportional term is used to process the effect of the error signal on the controller calculation value and ； represents the integral term and ; represents the differential control term, where is the controller bias, represents the controller gain value, Refers to the maximum output of the controller, Refers to the minimum output of the controller; Refers to the maximum output of the controller given manually; For the amount of charge, is the target value of the controlled quantity, Indicates the maximum value of the controlled quantity. Refers to the minimum value of the controlled quantity.

5. 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 increase test, performing a preset speed step-by-step decrease test, completing an ignition simulation and performing a preset maximum speed step-by-step increase test, and completing a continuous operation test at a preset power generation speed; The gas turbine shutdown operation specifically includes: completing a shutdown simulation, confirming the shutdown and performing a fuel system automatic reduction test, completing a gas turbine load automatic degradation test, and completing a gas turbine inertia off-grid shutdown test; The gas turbine load adjustment operation specifically includes: completing different power generation adjustment tests and completing various parameter recording tests during the adjustment process.

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