A method for modeling starting performance of marine gas turbines

Abstract

This invention provides a method for modeling the starting performance of a marine gas turbine. First, a gas turbine aero-thermodynamic performance calculation model is established using C++, and a heat transfer model, temperature sensor model, and control law model for the gas turbine's high-temperature components are established using the M language. Then, based on test data from the gas turbine startup process, the method analyzes how the pressure ratio and efficiency of typical gas turbine components change with the physical speed of the gas generator during startup. The corresponding low-speed characteristics of the gas turbine's rotating components are generated and corrected, enabling high-precision, real-time simulation of the gas turbine's starting performance. This method considers the heat exchange between the high-temperature fuel gas and the ambient atmosphere and the gas turbine itself, improving the accuracy of the gas turbine startup performance simulation. The method can provide a simulation testing tool for the design and optimization of gas turbine startup control laws.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine performance simulation, and mainly relates to a method for modeling a starting performance model of a marine gas turbine. Background Art

[0002] Marine gas turbines offer advantages such as high power, compact size, light weight, rapid startup, excellent acceleration, and maneuverability. They can effectively improve a ship's tactical and technical performance, significantly increasing its speed and maneuverability. Sea-level startup is the first stage of a gas turbine's operation and a prerequisite for its smooth and normal operation.

[0003] High-precision simulation methods for the start-up process of marine gas turbines, particularly those investigating the effects of varying atmospheric temperatures and initial wall temperatures on start-up performance, are still underdeveloped. These methods fail to consider the heat exchange between the high-temperature fuel gas and the turbine itself, as well as the heat exchange between the turbine itself and the external environment, which reduces the simulation accuracy of the gas turbine start-up performance model. However, the mathematical modeling of gas turbine start-up should be supplemented with heat transfer models, temperature sensor models, and control law models. This can significantly improve the accuracy of gas turbine start-up performance simulations and optimize the gas turbine start-up control laws for different atmospheric conditions and initial wall temperatures, shortening start-up time and improving start-up performance.

[0004] Based on the present invention, researchers can establish a high-precision dynamic real-time model and control law model of the gas turbine starting process, and conduct comprehensive analysis and evaluation of different starting control laws of the gas turbine. This can shorten the gas turbine development cycle to a certain extent, saving development funds and risks. Summary of the Invention

[0005] Purpose of the Invention: Based on the principles of aero-thermodynamics, taking into account the heat exchange between high-temperature combustion gas and the turbine itself during startup, as well as the dynamic characteristics of sensors, a model for the starting performance of a marine gas turbine is established. First, a gas turbine aero-thermodynamic model is established using C++, and a heat transfer model for the gas turbine's high-temperature components, a temperature sensor model, and a control law model are established using the M language. Then, based on test data from the gas turbine startup process, the variation of the pressure ratio and efficiency of typical gas turbine components with the physical speed of the gas generator during startup is analyzed. The corresponding low-speed starting characteristics of the gas turbine's rotating components are generated and corrected, achieving high-precision dynamic real-time simulation of the gas turbine's starting performance.

[0006] Technical solution: To achieve the above purpose, the technical solution adopted by the present invention is:

[0007] A method for modeling a starting performance model of a marine gas turbine comprises the following steps:

[0008] Step S1: Obtaining gas turbine startup performance measurement parameters, including the inlet and outlet total temperatures, inlet and outlet total pressures, and fuel flow rate of the compressor and power turbine, the output power of the power turbine, the speeds of the gas turbine and power turbine rotors, and the time required for the speed of the gas turbine rotor to reach a preset value, i.e., the startup time; analyzing the inlet and outlet total temperatures and inlet and outlet total pressures of the compressor and power turbine; and generating low-speed characteristics of rotating components of the gas turbine startup process using a characteristic identification method, wherein the rotating components include the compressor, the gas turbine, and the power turbine;

[0009] Step S2: Establishing a component-level starting mathematical model for the gas turbine, wherein the components include the starter, intake device, compressor, combustion chamber, gas turbine, power turbine, and exhaust device of the gas turbine; constructing the power and torque characteristics of the starter based on the existing design parameters of the starter, and calculating the compressor power consumption and gas turbine output power during the gas turbine starting process;

[0010] Step S3: constructing a heat transfer model and a temperature sensor model for high-temperature components of a gas turbine to evaluate the effect of heat exchange between high-temperature gas and high-temperature components on the starting performance of the gas turbine, wherein the high-temperature components include the combustion chamber, the gas turbine, and the power turbine;

[0011] Step S4: constructing an open-loop control law model and a closed-loop control law model for the gas turbine startup process; the open-loop startup control law includes the relationship between the gas turbine converted speed and the oil supply amount, and the relationship between the gas turbine converted speed and the oil-gas ratio; the closed-loop startup control law includes the relationship between the gas turbine converted speed and the gas turbine rotor acceleration;

[0012] Step S5: Perform performance simulation on the gas turbine startup process under various initial atmospheric conditions; the various initial conditions include different atmospheric temperatures, different atmospheric pressures, and different initial wall temperatures.

[0013] Preferably, in step S1, it is known that when a sea level start-up test is performed on a certain type of ship-borne gas turbine, the rotor acceleration of the gas turbine is calculated based on the speed of the gas turbine rotor during the start-up process, and then the rotor residual power of the gas turbine rotor at different times of the start-up process is estimated in combination with the rotor dynamics equation. Then, the inlet and outlet total temperatures and inlet and outlet total pressures of the compressor and power turbine during the start-up process are identified to obtain the pressure ratio and efficiency working characteristic lines of the rotating parts corresponding to different converted speeds.

[0014] Preferably, the rotor dynamics equation is as follows:

[0015] Phase 1:

[0016]

[0017] Phase 2:

[0018]

[0019] Phase 3:

[0020]

[0021] Where n g is the speed of the gas turbine rotor, J g is the moment of inertia of the gas turbine rotor, N st is the output power of the starter, N GT is the output power of the gas turbine, N C is the power consumption of the compressor.

[0022] Preferably, the implementation of step S2 is as follows: during the startup of the gas turbine, the rotor acceleration of the gas turbine needs to be obtained by calculating the residual power of the gas turbine rotor, and then the compressor power consumption N needs to be calculated separately. c And the gas turbine output power N GT :

[0023] Δh c =h c,out -h c,in

[0024] Δh gt =h gt,in -h gt,out

[0025] N c =W C Δh c

[0026] N GT =W GT Δh gt

[0027] Where Δh c is the enthalpy difference between the inlet and outlet air of the compressor, h c,in is the specific enthalpy of the air at the compressor inlet, h c,out is the specific enthalpy of the air at the compressor outlet, W c Compressor inlet air mass flow rate; Δh gt is the enthalpy difference between the inlet and outlet gas of the gas turbine, h gt,in is the specific enthalpy of gas at the gas turbine inlet, h gt,out is the specific enthalpy of gas at the gas turbine outlet, W GT is the gas turbine inlet gas mass flow rate;

[0028] The calculation formula for compressor and gas turbine torque is as follows:

[0029]

[0030] Where, T qt is the gas turbine output torque, T qc is the compressor drag torque.

[0031] Preferably, the implementation process of step S3 is:

[0032] The energy transfer from the high-temperature gas to the turbine is divided into two parts: one part, q1, is transferred to the turbine casing, and the other part, q2, is transferred to the turbine blades. At the same time, as the temperature of the turbine casing rises, there is a temperature difference with the external environment and heat is transferred to the outside world, with a heat transfer amount of q3.

[0033] The formula for calculating the average temperature of high-temperature gas after heat exchange is as follows:

[0034]

[0035] Where, is the mass flow rate of gas, C p,gas is the constant pressure specific heat capacity of the gas, calculated using the variable specific heat method, T gas is the average temperature of the gas before heat exchange, T' gas is the average temperature of the gas after heat exchange;

[0036] The average temperature of the gas turbine blades after heat exchange is calculated as follows:

[0037]

[0038] Where m bld is the mass of the gas turbine blades involved in heat exchange, C bld is the average specific heat of the gas turbine blade material. T bld is the average temperature of the gas turbine blades before heat exchange, T' bld is the average temperature of the gas turbine blades after heat exchange;

[0039] The average temperature of the gas turbine casing after heat exchange is calculated as follows:

[0040]

[0041] Where m cas is the mass of the gas turbine casing involved in heat exchange, C cas is the average specific heat of the gas turbine casing material; T cas is the average temperature of the gas turbine casing before heat exchange, T' cas is the average temperature of the gas turbine casing after heat exchange.

[0042] Preferably, in step S5:

[0043] Under three atmospheric conditions, namely, -15°C and 100740Pa, 0°C and 100570Pa, and 15°C and 100020Pa, the initial wall temperatures of the combustion chamber, the gas turbine, and the power turbine were set to 15°C in cold start-up and to 60°C, 90°C, and 120°C in hot start-up, respectively, to perform performance simulation of the gas turbine startup process.

[0044] Beneficial Effects: The present invention provides a method for modeling the starting performance of a naval gas turbine. This method is based on aerodynamic thermodynamics, considers the heat exchange between high-temperature fuel gas and the turbine itself during the startup process, and takes into account the dynamic characteristics of sensors. First, a gas turbine aerodynamic thermodynamic performance model is established using C++, and a heat transfer model, temperature sensor model, and control law model for the gas turbine's high-temperature components are established using the M language. Finally, based on gas turbine startup test data, the variation of the pressure ratio and efficiency of typical gas turbine components with the physical speed of the gas generator during startup is analyzed. The corresponding low-speed characteristics of the gas turbine's rotating components are generated and corrected, achieving high-precision real-time simulation of the gas turbine's starting performance. The present invention considers the heat exchange between the high-temperature fuel gas and the ambient atmosphere and the turbine itself, establishes a heat transfer model for the gas turbine's high-temperature components, and a temperature sensor model. This improves the accuracy of the gas turbine startup performance simulation. This method can be used to establish an integrated simulation platform for naval gas turbine starting performance, enabling closed-loop control simulation of the gas turbine startup process and providing a simulation testing tool for the design and optimization of gas turbine startup control laws. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 This is a flow chart of a method for modeling a starting performance model of a marine gas turbine provided by the present invention;

[0046] Figure 2 a is a characteristic diagram of the compressor pressure ratio during the startup process obtained by the characteristic identification method provided by the present invention;

[0047] Figure 2 b is a characteristic diagram of compressor efficiency during the startup process obtained by the characteristic identification method provided by the present invention;

[0048] Figure 3 a is a characteristic diagram of the gas turbine pressure drop ratio during the startup process obtained by the characteristic identification method provided by the present invention;

[0049] Figure 3 b is a characteristic diagram of gas turbine efficiency during the startup process obtained by the characteristic identification method provided by the present invention;

[0050] Figure 4a is a characteristic diagram of the power turbine pressure drop ratio during the starting process obtained by the characteristic identification method provided by the present invention;

[0051] Figure 4 b is a characteristic diagram of the power turbine efficiency during the starting process obtained by the characteristic identification method provided by the present invention;

[0052] Figure 5 This is a torque characteristic diagram of a gas turbine starter provided by the present invention;

[0053] Figure 6 This is a power characteristic diagram of the gas turbine starter provided by the present invention;

[0054] Figure 7 It is a schematic diagram of a gas turbine heat transfer model provided by the present invention;

[0055] Figure 8 The present invention provides a simulation curve of the gas turbine speed at different atmospheric temperatures before ignition when the engine is started;

[0056] Figure 9 a is a curve of the change in the gas turbine speed at the start of the combustion engine at different atmospheric temperatures provided by the present invention;

[0057] Figure 9 b is a curve of total temperature variation of the power turbine inlet at different atmospheric temperatures provided by the present invention when the combustion engine is started;

[0058] Figure 10 The invention provides the open-loop oil-gas ratio control law for starting a combustion engine.

[0059] Figure 11 a is a gas turbine speed change curve for starting with open-loop fuel supply at different initial wall temperatures provided by the present invention;

[0060] Figure 11 b is a curve of total temperature variation of the power turbine inlet at different initial wall temperatures provided by the present invention when the combustion engine is started with open-loop fuel supply;

[0061] Figure 12 a is a gas turbine speed change curve of closed-loop fuel supply at different initial wall temperatures provided by the present invention;

[0062] Figure 12 b is the total temperature change curve of the power turbine inlet during closed-loop fuel supply starting of the combustion engine at different initial wall temperatures provided by the present invention. DETAILED DESCRIPTION

[0063] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the present invention is described more clearly and completely below with reference to the accompanying drawings. It should be understood that the embodiments described are only a portion of the embodiments of the present invention, not all of them. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without inventive effort are also within the scope of protection of the present invention.

[0064] The present invention provides a method for modeling the starting performance model of a marine gas turbine. The specific process is as follows: Figure 1 shown.

[0065] First, a C++-based gas turbine aerodynamic and thermodynamic calculation method is established. Based on the analysis of the test data of the gas turbine startup process, the pressure ratio and efficiency characteristic diagrams of the typical gas turbine components during startup are generated. Then, a gas turbine component-level model based on the M language is built. Specifically,

[0066] Step S1: Obtain gas turbine startup performance test data and analyze the inlet and outlet parameters of typical gas turbine components. The test data is the total temperature and total pressure at the inlet and outlet of the components. Typical components include compressors and power turbines. Use the characteristic identification method to generate the low-speed characteristics of the rotating components during the gas turbine startup process, including the compressor, gas turbine, and power turbine. The results generated by the characteristic identification method are: the pressure ratio characteristics of the compressor are as follows: Figure 2 As shown in a, the efficiency characteristics of the compressor are as follows Figure 2 b; the gas turbine pressure drop ratio characteristics are as follows Figure 3 As shown in a, the gas turbine efficiency characteristics are as follows Figure 3 b; the power turbine pressure ratio characteristics are as follows Figure 4 As shown in a, the power turbine efficiency characteristics are as follows Figure 4 As shown in b.

[0067] Step S2: Establish a gas turbine component-level starting mathematical model, including the starter, intake device, compressor, combustion chamber, gas turbine, power turbine, and exhaust device; further construct the starter power and torque characteristics based on the existing design parameters of the starter, wherein the starter torque characteristics are as follows: Figure 5 As shown, the starter power characteristics are as follows Figure 6 As shown, the compressor power consumption and gas turbine output power during the gas turbine startup process are calculated.

[0068] Step S3: Build a heat transfer model and temperature sensor model for high-temperature components of a gas turbine to evaluate the effect of heat exchange between high-temperature gas and high-temperature components on the starting performance of the gas turbine. The high-temperature components here include the combustion chamber, gas turbine, and power turbine. Taking the gas turbine as an example, the heat transfer diagram of its components is as follows: Figure 7 As shown;

[0069] Step S4: Construct open-loop and closed-loop control law models for the gas turbine startup process. The open-loop startup control law includes the relationship between the gas turbine converted speed and the fuel supply, i.e., varying fuel quantities are assigned based on changes in the gas turbine converted speed during operation, and the relationship between the gas turbine converted speed and the fuel-to-gas ratio, i.e., varying fuel quantities are assigned based on changes in the ratio of the fuel quantity to the compressor outlet total pressure during operation. The closed-loop startup control law refers to the relationship between the gas turbine converted speed and the gas turbine rotor acceleration, i.e., based on a preset gas turbine acceleration command, the controller adjusts the fuel quantity at the next moment using the gas turbine rotor acceleration at the previous moment as feedback, thereby controlling the gas turbine rotor acceleration process. Performance simulations of the gas turbine startup process are performed under various initial atmospheric conditions. These various initial conditions include different atmospheric temperatures, different atmospheric pressures, and different initial wall temperatures of the gas turbine's high-temperature components. Performance simulations of the startup process are performed under various atmospheric temperatures, different atmospheric pressures, and different initial wall temperatures, based on the open-loop and closed-loop startup control laws.

[0070] In order to ensure the effectiveness of the ship gas turbine startup modeling method based on the modular simulation platform designed by the present invention, a specific embodiment is provided below to simulate the startup performance model of a certain type of ship gas turbine. Specifically,

[0071] For the gas turbine, the model is simulated to a certain gas turbine physical speed under the initial conditions of atmospheric temperature of -30℃, 0℃ and 30℃. Taking the physical ignition speed of the gas turbine as the 100% reference value of the coordinate, the gas turbine speed simulation curve at different atmospheric temperatures before ignition is obtained ( Figure 8 ).Depend on Figure 8 It can be seen that during the startup process, when the gas turbine reaches the same ignition physical speed, the higher the atmospheric temperature, the shorter the startup acceleration time. The higher the atmospheric temperature, the higher the shaft mechanical efficiency, the greater the rotor acceleration, and the shorter the time required to reach the ignition speed. Then, under the same open-loop oil supply law, given different atmospheric temperatures of -30℃, 0℃, and 30℃, the model is used to simulate the slow-run state. The key parameters such as the gas turbine speed change curve are as follows: Figure 9 As shown in a, the total temperature change curve of the power turbine inlet is as follows Figure 9 As shown in Figure b. It can be seen that when the atmospheric temperature is -30℃, the ignition time is earlier than when it is 0℃ and 30℃, and it can be seen that the lower the atmospheric temperature, the earlier the ignition time. Since the gas turbine modeled in this paper is ignited and fueled when the converted speed reaches a certain value, according to the conversion speed calculation formula, the lower the atmospheric temperature, the lower the physical speed corresponding to the converted speed at the time of ignition. Therefore, when the temperature is low, the conversion speed corresponding to the ignition can be reached in advance at a relatively low physical speed. At the same time, this simulation adopts the start-up open-loop oil-gas ratio control law ( Figure 10) Oil supply. In cold weather, the gas turbine reaches the converted speed in advance. Early oil supply will cause the gas turbine speed to increase faster when the atmospheric temperature is low.

[0072] The cold and hot start of the gas turbine are simulated by giving the gas turbine conversion speed and oil-gas ratio. The gas turbine speed change curves during open-loop oil supply start at different initial wall temperatures are shown in the figure below. Figure 11 As shown in a, under the conditions that the initial wall temperature T0 of the gas turbine is 25℃, 50℃, and 75℃ respectively, the simulation curves of the main performance parameters of the gas turbine during open-loop oil supply start-up are as follows: Figure 11 As shown in Figure b, with other conditions remaining the same, the gas turbine speed curves vary when starting at different initial wall temperatures. When the wall temperature is higher than the ambient air temperature, the gas turbine is in a hot start state, with a faster increase in speed. When the wall temperature is equal to the ambient air temperature, the gas turbine is in a cold start state, with a relatively slow increase in speed. Therefore, when the wall temperature is higher and the engine is in a hot start state, a greater proportion of the heat generated by fuel combustion is used to accelerate the gas turbine rotor, allowing the engine to reach ignition speed more quickly, resulting in a relatively shorter start time.

[0073] Compared with the open-loop control method, the starting performance of the gas turbine is simulated under the closed-loop fuel supply method based on the relationship between the gas turbine speed and its rotor acceleration, with the initial wall temperature of 25°C, 50°C, and 75°C respectively. The simulation results show the speed change curves of the gas turbine when the closed-loop fuel supply is started at different initial wall temperatures. Figure 12 As shown in a, the total temperature change curve of the power turbine inlet at different initial wall temperatures is as follows: Figure 12 As shown in b. Figure 12 a. When the fuel is supplied according to the closed-loop control law of the gas turbine speed and its rotor acceleration, the difference between the gas turbine speed change curves under three different working conditions is not the same as when the fuel is supplied according to the open-loop starting control law ( Figure 11 a) is obvious. Although the gas turbine speed will reach the ignition speed and the idle speed faster when the initial wall temperature of the gas turbine is high, the overall difference is not very obvious. Figure 12 b. Under different initial wall temperatures, when the gas turbine adopts the closed-loop gas turbine rotor acceleration rate oil supply method, the total temperature difference of the power turbine inlet is not much, and the gas turbine obtains almost the same starting acceleration performance.

[0074] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A method for modeling a starting performance model of a marine gas turbine, characterized in that: The following steps are involved: Step S1: Obtaining gas turbine startup performance measurement parameters, including the inlet and outlet total temperatures, inlet and outlet total pressures, and fuel flow rate of the compressor and power turbine, the output power of the power turbine, the speeds of the gas turbine and power turbine rotors, and the time required for the speed of the gas turbine rotor to reach a preset value, i.e., the startup time; analyzing the inlet and outlet total temperatures and inlet and outlet total pressures of the compressor and power turbine; and generating low-speed characteristics of rotating components of the gas turbine startup process using a characteristic identification method, wherein the rotating components include the compressor, the gas turbine, and the power turbine; Step S2: Establishing a component-level starting mathematical model for the gas turbine, wherein the components include the starter, intake device, compressor, combustion chamber, gas turbine, power turbine, and exhaust device of the gas turbine; constructing the power and torque characteristics of the starter based on the existing design parameters of the starter, and calculating the compressor power consumption and gas turbine output power during the gas turbine starting process; Step S3: constructing a heat transfer model and a temperature sensor model for high-temperature components of a gas turbine to evaluate the effect of heat exchange between high-temperature gas and high-temperature components on the starting performance of the gas turbine, wherein the high-temperature components include the combustion chamber, the gas turbine, and the power turbine; Step S4: constructing an open-loop control law model and a closed-loop control law model for the gas turbine startup process; the open-loop startup control law includes the relationship between the gas turbine converted speed and the oil supply amount, and the relationship between the gas turbine converted speed and the oil-gas ratio; the closed-loop startup control law includes the relationship between the gas turbine converted speed and the gas turbine rotor acceleration; Step S5: Performing a performance simulation of the gas turbine startup process under various initial atmospheric conditions; the various initial conditions include different atmospheric temperatures, different atmospheric pressures, and different initial wall temperatures; The implementation process of step S3 is: The energy transfer from the high-temperature gas to the turbine is divided into two parts: one part, q1, is transferred to the turbine casing, and the other part, q2, is transferred to the turbine blades. At the same time, as the temperature of the turbine casing rises, there is a temperature difference with the external environment and heat is transferred to the outside world, with a heat transfer amount of q3. The formula for calculating the average temperature of high-temperature gas after heat exchange is as follows: in, is the mass flow rate of gas, C p,gas is the constant pressure specific heat capacity of the gas, calculated using the variable specific heat method, T gas is the average temperature of the gas before heat exchange, T′ gas is the average temperature of the gas after heat exchange; The average temperature of the gas turbine blades after heat exchange is calculated as follows: Among them, m bld is the mass of the gas turbine blades involved in heat exchange, C bld is the average specific heat of the gas turbine blade material, T bld is the average temperature of the gas turbine blades before heat exchange, T′ bld is the average temperature of the gas turbine blades after heat exchange; The average temperature of the gas turbine casing after heat exchange is calculated as follows: Among them, m cas is the mass of the gas turbine casing involved in heat exchange, C cas is the average specific heat of the gas turbine casing material; T cas is the average temperature of the gas turbine casing before heat exchange, T′ cas is the average temperature of the gas turbine casing after heat exchange.

2. The method for modeling a starting performance model of a marine gas turbine according to claim 1, wherein: In step S1, it is known that when a sea level start-up test is performed on a certain type of ship gas turbine, the rotor acceleration of the gas turbine is calculated based on the speed of the gas turbine rotor during the start-up process, and then the rotor residual power of the gas turbine rotor at different times of the start-up process is estimated in combination with the rotor dynamics equation. Then, the inlet and outlet total temperatures and inlet and outlet total pressures of the compressor and power turbine during the start-up process are identified to obtain the pressure ratio and efficiency working characteristic lines of the rotating parts corresponding to different converted speeds.

3. The method for modeling a starting performance model of a marine gas turbine according to claim 2, wherein: The rotor dynamics equation is as follows: Phase 1: Phase 2: Phase 3: Among them, n g is the speed of the gas turbine rotor, J g is the moment of inertia of the gas turbine rotor, N st is the output power of the starter, N GT is the output power of the gas turbine, n C is the power consumption of the compressor.

4. A method for modeling a starting performance model of a marine gas turbine according to claim 3, characterized in that: The implementation of step S2 is as follows: during the startup of the gas turbine, the residual power of the gas turbine rotor needs to be calculated to obtain the acceleration of the gas turbine rotor during the startup process, and then the compressor power consumption N needs to be calculated separately. c And the gas turbine output power N GT : Δh c =h c,out -h c,in Δh gt =h gt,in -h gt,out N c =W C Δh c N GT =W GT Δh gt Where Δh c is the enthalpy difference between the inlet and outlet air of the compressor, h c,in is the specific enthalpy of the air at the compressor inlet, h c,out is the specific enthalpy of the air at the compressor outlet, W c Compressor inlet air mass flow rate; Δh gt is the enthalpy difference between the inlet and outlet gas of the gas turbine, h gt,in is the specific enthalpy of gas at the gas turbine inlet, h gt,out is the specific enthalpy of gas at the gas turbine outlet, W GT is the gas turbine inlet gas mass flow rate; The calculation formula for compressor and gas turbine torque is as follows: Among them, T qt is the gas turbine output torque, T qc is the compressor drag torque.

5. The method for modeling a starting performance model of a marine gas turbine according to claim 1, wherein: In step S5: Under three atmospheric conditions, namely, -15°C and 100740Pa, 0°C and 100570Pa, and 15°C and 100020Pa, the initial wall temperatures of the combustion chamber, the gas turbine, and the power turbine were set to 15°C in cold start-up and to 60°C, 90°C, and 120°C in hot start-up, respectively, to perform performance simulation of the gas turbine startup process.

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