A fine modeling method for a single-shaft gas turbine gas path system
By employing stepwise compression and refined modeling of the differential equations of the combustion chamber module, the problem of dynamic changes in specific heat capacity and fluid composition in the gas turbine gas path system was solved, achieving high-precision simulation and real-time response, and supporting gas turbine performance optimization.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SHANGHAI JIAOTONG UNIV
- Filing Date
- 2026-01-27
- Publication Date
- 2026-06-05
AI Technical Summary
Existing gas turbine gas path system modeling methods fail to fully consider the changes in gas specific heat capacity with temperature and the dynamic changes in fluid composition in the combustion chamber, resulting in low simulation accuracy and difficulty in meeting the requirements for high accuracy and real-time response.
By employing stepwise compression, combustion chamber module differential equations, and stepwise expansion methods, combined with a Python simulation platform, the thermodynamic processes of the compressor, combustion chamber, and turbine are modeled in detail. Considering variable specific heat capacity and component differential equations, dynamic calculation of gas temperature and composition is achieved.
It significantly improves simulation accuracy and reliability, accurately predicts combustion chamber outlet parameters, enhances the model's predictive capabilities, and provides a scientific basis for gas turbine performance optimization.
Smart Images
Figure CN122154084A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of gas turbine technology, and in particular to a refined modeling method for gas path systems of single-shaft gas turbines. Background Technology
[0002] Gas turbines, as a core component of modern energy and power technology, play a crucial role in fields such as shipbuilding, power generation, and aviation. Their working principle relies on the coordinated operation of the compressor, combustion chamber, and turbine to achieve efficient energy conversion through a gas path system. Accurate mathematical models of gas turbines are fundamental for performance optimization, operational control, and fault diagnosis.
[0003] However, most existing gas turbine gas path system modeling methods have significant technical limitations, mainly in two aspects. First, when modeling the physical characteristics of the compressor and turbine, many traditional methods fail to fully consider the actual changes in the gas's thermodynamic parameters (specific heat capacity) with temperature. As air and gas experience significant temperature fluctuations in the compressor and turbine, the non-constant nature of their specific heat capacity will cause cumulative errors in the calculation of compression work, expansion work, and the overall energy balance of the system. This error is especially pronounced under high-temperature conditions, thus reducing the model's predictive accuracy.
[0004] Secondly, the modeling of the combustion chamber suffers from simplification, failing to effectively reflect the dynamic changes in actual fluid composition. The combustion chamber is not a simple energy injection unit; its internal chemical reaction processes are complex and influenced by multiple factors, including the uniformity of fuel-air mixing, the degree of combustion, and the dynamic equilibrium of the chemical reactions. Traditional models often neglect the dynamic evolution of the composition of the combustion chamber outlet products caused by the combustion process. This simplification leads to inaccurate predictions of combustion chamber outlet temperature and fuel composition, consequently affecting subsequent turbine performance analysis and overall system efficiency calculations.
[0005] These simplifications in the models directly lead to low simulation accuracy of existing gas turbine theoretical mathematical models, making it difficult to realistically reflect the complex dynamic characteristics of the gas turbine gas path system during actual operation. The limitations of traditional models become increasingly apparent, especially in scenarios requiring high-precision simulation and real-time response. For example, document CN115169048A discloses a heavy-duty gas turbine modeling method based on multi-domain component modeling. However, this method does not consider the change in specific heat capacity with temperature and directly solves for the changes in fluid composition within the combustion chamber module using both static and dynamic models. This modeling approach fails to effectively reflect the real dynamic changes in fluid composition within the gas turbine gas path system and also ignores the dynamic evolution of the combustion chamber outlet product composition caused by the combustion process, significantly reducing prediction accuracy. Therefore, there is an urgent need for a gas turbine gas path system modeling method that can overcome existing bottlenecks, more accurately simulate the energy conversion of the compressor and turbine, and comprehensively characterize the dynamic processes of chemical reactions within the combustion chamber, to meet the demands of modern gas turbine technology for high-precision and high-real-time modeling. Summary of the Invention
[0006] To address the aforementioned problems in the existing technology, this invention provides a refined modeling method for a single-shaft gas turbine gas path system, comprising the following steps: S1. Establish a step-by-step compression compressor module for a single-shaft gas turbine gas circuit system. Discretize the continuous compression process inside the compressor in terms of the spatial distance from the inlet to the outlet to obtain refined compressor module outlet temperature and power consumption. S2. Establish the combustion chamber module of the gas circuit system of a single-shaft gas turbine, use the differential equation of gas medium composition to solve the changes in fluid composition within the combustion chamber module, and combine the variable specific heat capacity integral to calculate the mass and temperature of each component at the outlet; S3, establish a step-expansion turbine module for a single-shaft gas turbine gas circuit system, and discretize the continuous expansion process inside the turbine in terms of the spatial distance from the inlet to the outlet to obtain the refined turbine module outlet temperature and power. S4, based on the calculation methods of compressor module outlet temperature and power consumption in S1, the calculation methods of mass and temperature of each component at the outlet of combustion chamber module in S2, and the calculation methods of turbine module outlet temperature and power in S3, a single-shaft gas turbine gas circuit system model is established using the Python simulation platform; S5: Obtain rated operating condition and actual operating data, input the rated operating condition data into the single-shaft gas turbine gas circuit system model built in S4, and analyze the dynamic characteristics of the gas turbine.
[0007] Furthermore, the specific calculation method for the step-by-step compression compressor module of the single-shaft gas turbine gas circuit system in step S1 is as follows: the continuous compression process inside the compressor is discretized along the spatial distance from the inlet to the outlet, and discretized into... Step 1; Based on the ideal isentropic process, utilize stepwise compression of the first... Temperature value at step Iterative calculation and step-by-step compression of the first Step temperature The final compressor module outlet temperature was obtained as follows: .
[0008] Furthermore, the gas temperature change during the stepwise compression process in step S1 satisfies the isentropic integral relationship as follows: In the formula, To compress the first step Pressure value at the step, To compress the first step Pressure value at the step, This represents the equivalent specific heat ratio of the gas at the corresponding temperature. The pressure value is continuous. Simultaneously, an equivalent multi-party index is introduced at each compression step. This is used to provide an equivalent characterization of the isentropic integral term under varying specific heat conditions: Considering the variable specific heat characteristics and the multivariable efficiency correction of the compressor, the step compression... Step temperature Represented as: In the formula, the equivalent multi-party index Represented as: in, For the first The specific heat capacity at step [of point] increases with [the following]. Updated in accordance with changes; For compressor variable efficiency. Let be the gas constant with respect to the gas components, and take . .
[0009] Furthermore, the specific calculation method for the combustion chamber module of the single-shaft gas turbine gas path system in step S2 is as follows: establish and solve the dynamic evolution differential equation of component mass to obtain the mass fraction of each component at the combustion chamber outlet. The differential equation can be expressed as: In the formula, For the first Mass of each gas component Burning time This indicates the rate of mass change produced or consumed by chemical reactions in the combustion chamber. The total mass flow rate into the combustion chamber inlet. For the combustion chamber inlet Mass fraction of the components The total mass flow rate exiting the combustion chamber is [missing information]. For the combustion chamber inlet Mass fraction of the components; Calculating composition using variable specific heat capacity integral enthalpy : In the formula, Components At temperature The specific heat capacity at constant pressure is For the first Specific enthalpy of the components at a reference temperature For reference temperature, The outlet temperature; For each component of the outlet mixed gas at the outlet temperature The enthalpy of the outlet mixed gas is obtained by taking the weighted average of the specific enthalpy. : In the formula, The outlet mixed gas The proportion and weight of each component; enthalpy of the outlet mixed gas Substituting into the energy conservation equation of the combustion chamber: In the formula, For gas energy, For combustion efficiency, The lower heating value of fuel, The mass flow rate of the air medium. The enthalpy of air. The mass flow rate of the gas medium. The enthalpy of the gaseous medium. The mass flow rate of the exhaust medium; Under steady-state conditions, let The combustion chamber outlet temperature is determined by iteratively solving the energy conservation equation. .
[0010] Furthermore, the specific calculation method for the step-by-step expansion turbine module of the single-shaft gas turbine gas path system in step S3 is as follows: the continuous expansion process inside the turbine is discretized along the spatial distance from the inlet to the outlet, and discretized into... Step 1; Based on an ideal isentropic process, utilizing stepwise expansion of the first... Temperature value at step Iterative calculation of step-by-step expansion Step temperature The final turbine module outlet temperature was obtained as follows: .
[0011] Furthermore, the gas temperature change during the stepwise expansion process in step S3 satisfies an isentropic integral relationship, which can be expressed as: In the formula, For step-by-step expansion Pressure value at the step, For step-by-step expansion Pressure value at the step, This represents the equivalent specific heat ratio of the gas at the corresponding temperature. Each expansion step introduces an equivalent multi-party index. This is used to provide an equivalent characterization of the isentropic integral term under varying specific heat conditions: Considering the variable specific heat characteristics and the correction for the variable turbine efficiency, the stepwise compression of the first stage... Step temperature It can be represented as: In the formula, the equivalent multi-party index Represented as: in, For the first The specific heat capacity at step [of point] increases with [the following]. Updated in accordance with changes; For turbine variable efficiency; Let be the gas constant with respect to the gas components, and take . .
[0012] Furthermore, in step S4, based on the Python simulation platform, the compressor, combustion chamber and turbine component models are encapsulated as independent Python classes, and the parameters passed between the modules are defined using the interface module to realize the calculation of the thermodynamic properties of each component of the gas path system.
[0013] Furthermore, in step S5, the air mass flow rate under ISO operating conditions is used. Compressor pressure ratio Fuel mass flow rate As input to the simulation model, it is input into the single-shaft gas turbine gas path system model built by S4 to calculate the compressor outlet temperature of the simulation model. Combustion chamber outlet temperature Turbine exhaust temperature Output power ,efficiency Thermal efficiency ratio The calculation results were compared and analyzed with the actual operating data of the gas circuit system.
[0014] Compared with the prior art, the significant advantages of this invention are as follows: 1) Accurate simulation of aerodynamic processes, significantly improving simulation accuracy and reliability. When modeling the compressor and turbine modules, this invention no longer uses the simplified assumption of a fixed specific heat capacity, but innovatively considers the dynamic changes in specific heat capacity with temperature. By discretizing the continuous compression / expansion process into n stages and calculating the specific heat capacity in real time at each stage, the simulation of the aerodynamic process is more accurate, effectively improving the accuracy and reliability of the simulation model. 2) Deeply revealing the combustion process mechanism and accurately predicting combustion chamber outlet parameters. For the combustion chamber module, this invention introduces component differential equations to accurately solve the dynamic evolution of fluid composition, building upon traditional methods that only consider macroscopic energy balance. This detailed characterization of the internal chemical kinetics of the combustion reaction enables more accurate prediction of key parameters such as combustion products, instantaneous reaction rate, and combustion chamber outlet temperature, providing strong support for a deeper understanding and optimization of the combustion process. 3) Enhance model predictive capabilities to provide a scientific basis for gas turbine performance optimization. By performing more refined and physically accurate modeling of the aerodynamic and combustion processes, the modeling results show good agreement with actual operating data, meeting simulation requirements and greatly enhancing the predictive capabilities of the simulation model. This means that the model can not only more accurately describe the transient behavior of the gas turbine, but also provide more scientific and reliable data support for further performance optimization and control strategy development. Attached Figure Description
[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0016] Figure 1 This is a flowchart of the object-oriented modeling method for calculating the thermodynamic response of a gas turbine gas path system according to the present invention.
[0017] Figure 2 This is a schematic diagram of the gas path system for the M701F4 gas turbine according to the present invention.
[0018] The attached figures are labeled as follows: Gas turbine ambient temperature; , Compressor inlet pressure; Air mass flow rate at the compressor inlet; Fuel mass flow rate at the combustion chamber inlet; Compressor outlet temperature; Compressor outlet pressure; Temperature at the combustion chamber outlet; Pressure at the combustion chamber outlet; Turbine outlet temperature; Pressure at the turbine outlet. Detailed Implementation
[0019] Please see Figure 1-2 The present invention provides a refined modeling method for a single-shaft gas turbine gas path system, comprising the following specific steps: S1, Establish the step-compression compressor module of the single-shaft gas turbine gas circuit system; The continuous compression process inside the compressor is discretized, specifically its spatial distance from the inlet to the outlet, resulting in the following discretization method: Step 1: Measure the temperature value at step 1 using a temperature sensor. Calculate the number of iterations in sequence. Temperature value at step According to the Temperature value at step Calculate the first Specific heat capacity at step (The specific calculation method for the specific heat capacity is based on existing technology and is omitted here.)
[0020] Stepwise compression takes into account the drastic temperature changes inside the compressor, and the specific heat ratio of the compressed air changes with temperature. Considering the variable specific heat condition, the temperature change during stepwise compression of the gas satisfies the isentropic integral relationship, which can be expressed as: In the formula, To compress the first step Pressure value at the step, To compress the first step Pressure value at the step, This represents the equivalent specific heat ratio of the gas at the corresponding temperature. This is a continuous pressure value.
[0021] Furthermore, to better meet engineering applications, an equivalent multi-factor index is introduced at each compression step. This is used to provide an equivalent characterization of the isentropic integral term under varying specific heat conditions: Considering the variable specific heat characteristics and the multivariable efficiency correction of the compressor, the step compression... Step temperature Represented as: In the formula, the equivalent multi-party index Represented as: in, For the first The specific heat capacity at step [of point] increases with [the following]. Updated in accordance with changes; For compressor variable efficiency. Let be the gas constant with respect to the gas components, and take . .
[0022] Assuming the pressure changes uniformly, then the first... Pressure value at step and the first The pressure values at each step are as follows: in, This refers to the compressor inlet pressure. This refers to the compressor outlet pressure. To compress the discrete number of steps.
[0023] In addition, compressor power consumption is calculated based on a single step size. : In the formula, The reduced flow rate of the compressor is obtained by fitting the compressor characteristic curve using a two-dimensional table interpolation method. ,in The compressor compression ratio. This refers to the compressor speed.
[0024] S2, Establish the combustion chamber module of the single-shaft gas turbine gas circuit system; The changes in fluid composition within the combustion chamber module are solved using the differential equation of the gas medium composition, and the mass and temperature of each component at the outlet are calculated by combining the variable specific heat capacity integral. Specifically, the steps include the following: S2.1 Establish the dynamic evolution differential equation of the mass of the gas medium components: Components in the combustion chamber quality rate of change over time The net production / consumption rate of the chemical reaction and the net input / output rate of mass flow are determined by the following formula: In the formula, For the first Mass of each gas component Burning time This indicates the rate of mass change produced or consumed by chemical reactions in the combustion chamber. The total mass flow rate into the combustion chamber inlet. For the combustion chamber inlet Mass fraction of the components The total mass flow rate exiting the combustion chamber is [missing information]. For the combustion chamber inlet Mass fraction of the components; By solving the above-mentioned mass The differential equation yields the mass fraction of each component at the combustion chamber outlet. .
[0025] S2.2 Calculate the outlet temperature using energy conservation and variable specific heat capacity: enthalpy of the outlet mixed gas The components of the outlet mixed gas at the outlet temperature Weighted average of lower enthalpy: Among them, each component enthalpy By reference temperature to outlet temperature isobaric specific heat capacity Integral calculation: In the formula, Components At temperature The specific heat capacity at constant pressure is For the first The specific enthalpy of the component at the reference temperature.
[0026] enthalpy of the outlet mixed gas Substituting into the energy conservation equation of the combustion chamber: In the formula, For gas energy, For combustion efficiency, The lower heating value of fuel, The mass flow rate of the air medium. The enthalpy of air. The mass flow rate of the gas medium. The enthalpy of the gaseous medium. This represents the mass flow rate of the exhaust medium.
[0027] Gas energy Represented as: in, For reference to ambient temperature, Let be the gas constant with respect to the gas components, and be the gas constant with respect to the gas components. Related .
[0028] Combining the energy conservation equation and the formula for calculating variable specific heat capacity, under steady-state conditions, let The combustion chamber outlet temperature is determined by iteratively solving the energy conservation equation. .
[0029] The iterative solution process is as follows: Determine an initial outlet temperature. ; Based on the initial outlet temperature Calculate the enthalpy of the outlet mixed gas ; The enthalpy obtained Substitute the energy conservation equation for the combustion chamber and determine whether the energy conservation equation holds true; If the energy conservation equation does not hold, then adjust the outlet temperature. Continue iterating; if the equation holds true, output the result. .
[0030] S3, Establish a step-expansion turbine module for a single-shaft gas turbine gas circuit system; The continuous expansion process inside the turbine is discretized along the spatial distance from the inlet to the outlet, resulting in the following discretization steps: Step 1; The first step is to set the outlet temperature of the combustion chamber module. Initial temperature at the turbine module inlet Calculate the number of iterations in sequence. Temperature value at step The specific heat capacity is calculated in real time based on the current temperature at each step. (The specific calculation method for the specific heat capacity is based on existing technology and is omitted here.)
[0031] Stepwise expansion takes into account the drastic temperature changes of the gas inside the turbine, where the specific heat ratio of the expanding gas changes with temperature. Considering the variable specific heat condition, the temperature change during the stepwise expansion of the gas satisfies the isentropic integral relationship, which can be expressed as: In the formula, For step-by-step expansion Pressure value at the step, For step-by-step expansion Pressure value at the step, This represents the equivalent specific heat ratio of the gas at the corresponding temperature.
[0032] Furthermore, to facilitate better engineering applications, an equivalent multi-square index is introduced for each expansion step. This is used to provide an equivalent characterization of the isentropic integral term under varying specific heat conditions: Considering the variable specific heat characteristics and the correction for the variable turbine efficiency, the stepwise compression of the first stage... Step temperature It can be represented as: In the formula, the equivalent multi-party index It can be represented as: in, For the first The specific heat capacity at step [of point] increases with [the following]. Updated in accordance with changes; To improve the variable efficiency of the turbine.
[0033] Assuming the pressure changes uniformly, then the first... Pressure value at step and the first The pressure values at each step are as follows: in, To increase turbine inlet pressure, To alleviate export pressure, The step-by-step expansion discrete number.
[0034] In addition, the turbine work is calculated cumulatively based on a single step size. : In the formula, The reduced flow rate of the turbine was obtained by fitting a turbine characteristic curve using a two-dimensional table interpolation method. ;in The compression ratio of the turbine, The rotational speed of the turbine.
[0035] S4, based on the compressor module outlet temperature in S1 Power consumption Calculation method, mass of each component at the outlet of the combustion chamber module in S2 ,temperature The calculation method and the turbine module outlet temperature obtained in S3 ,power The calculation method uses a Python simulation platform to build a model of the gas circuit system of a single-shaft gas turbine; The models S1-S3, built based on the compressor, combustion chamber, and turbine components, are encapsulated as independent Python classes. An interface module is used to define the parameters passed between these modules, including the components of the gas-phase fluid. ,temperature ,pressure and mass flow rate The interface module is responsible for implementing the components. and temperature Calculation of thermodynamic properties (specific heat capacity, enthalpy) under certain conditions.
[0036] A single-shaft gas turbine gas path system model was built on a Python simulation platform. The gas path system was built as follows: Figure 2 As shown, the air intake assembly is connected to the compressor module inlet, and the gas intake assembly is connected to the combustion chamber module inlet; the compressor module outlet is connected to the combustion chamber module inlet via an interface module; the combustion chamber module outlet is connected to the turbine module inlet via an interface module; the turbine module outlet outputs the system's final state parameters. The power consumption of the compressor module in S1, the output power of the turbine module in S3, and the composition and temperature of the combustion chamber outlet in S2 are transmitted through the interface, realizing the dynamic correlation of the single-axis system.
[0037] Using the Python libraries NumPy and SciPy, the numerical computation, interpolation, integration, and iterative solution processes for S1-S3 are implemented. During the simulation, discretization calculations are performed according to a preset step size, sequentially solving for the state updates of each module, and iterating based on coupling relationships. When configuring the model, compressor / turbine characteristic data, combustion chamber chemical reaction mechanisms and kinetic parameters, fuel properties, and component thermodynamic databases must be imported in advance. The simulation inputs specifically include ambient temperature, ambient pressure, compressor pressure ratio, air mass flow rate, and fuel mass flow rate. The simulation outputs the system's transient state parameters and overall performance indicators.
[0038] S5, acquire the rated operating conditions of the gas turbine and the actual operating data of the gas turbine gas circuit system, input the above data into the single-shaft gas turbine gas circuit system model built in S4, output the key thermodynamic parameters of the gas turbine, and then use the above output to analyze the dynamic characteristics of the gas turbine. like Figure 2 The M701F4 gas turbine is a single-shaft type, consisting of three main components: a compressor, a combustion chamber, and a turbine. Its main parameters are shown in Table 1. The compressor draws in and compresses air, the combustion chamber mixes and ignites fuel, and the turbine uses the expansion of the high-temperature gas to drive the rotor, performing work. Part of this work is used to drive the compressor, and the remaining work is output. The gas turbine control inputs include intake air flow and fuel flow. Actual operating data of the gas turbine's gas circuit system includes: air mass flow rate. Compressor pressure ratio Fuel mass flow rate Compressor inlet temperature Compressor inlet pressure Compressor outlet temperature Compressor outlet pressure Combustion chamber outlet temperature Combustion chamber outlet pressure Turbine outlet temperature Turbine export pressure and the output power of the gas system under operating conditions. ,efficiency Heat consumption rate Key thermodynamic parameters. It is assumed that the compressor inlet temperature equals the ambient temperature, the compressor outlet temperature equals the combustion chamber inlet temperature, and the combustion chamber outlet temperature equals the turbine inlet temperature.
[0039] For the ISO operating condition of the M701F4 gas turbine gas circuit system, extract the output power of the gas circuit system under actual operating conditions. ,efficiency Heat consumption rate Compressor outlet temperature Combustion chamber outlet temperature and turbine exhaust temperature Six key thermodynamic parameters are used for comparison.
[0040] In addition, the air mass flow rate under ISO operating conditions Compressor pressure ratio Fuel mass flow rate As input to the simulation model, the compressor outlet temperature of the simulation model is calculated. Combustion chamber outlet temperature Turbine exhaust temperature .
[0041] According to the work done by the turbine and compressor power consumption Calculate output power : Efficiency of the gas system during operation : In the formula, This refers to the fuel flow rate of the gas turbine.
[0042] Thermal efficiency ratio of gas circuit system under operating conditions : In the formula, The higher heating value per unit mass of fuel.
[0043] The thermodynamic parameters of the actual operating state of the gas circuit system are compared and analyzed with the thermodynamic parameters output by the model established by the method of this invention. Specific calculation results and error comparisons are shown in Table 2. The analysis results show that the stepwise compression and combustion reaction modeling method for gas turbine gas circuit systems adopted in this invention has high analytical accuracy and meets the accuracy requirements of actual machine simulation.
[0044] Table 1 Table 2 In this specification, the same or similar parts between the various embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the descriptions of the embodiments described later are relatively simple, and relevant parts can be referred to the descriptions of the foregoing embodiments.
[0045] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A refined modeling method for a single-shaft gas turbine gas path system, characterized in that, The steps include the following: S1. Establish a step-by-step compression compressor module for a single-shaft gas turbine gas circuit system. Discretize the continuous compression process inside the compressor in terms of the spatial distance from the inlet to the outlet to obtain refined compressor module outlet temperature and power consumption. S2. Establish the combustion chamber module of the gas circuit system of a single-shaft gas turbine, use the differential equation of gas medium composition to solve the changes in fluid composition within the combustion chamber module, and combine the variable specific heat capacity integral to calculate the mass and temperature of each component at the outlet; S3, establish a step-expansion turbine module for a single-shaft gas turbine gas circuit system, and discretize the continuous expansion process inside the turbine in terms of the spatial distance from the inlet to the outlet to obtain the refined turbine module outlet temperature and power. S4, based on the calculation methods of compressor module outlet temperature and power consumption in S1, the calculation methods of mass and temperature of each component at the outlet of combustion chamber module in S2, and the calculation methods of turbine module outlet temperature and power in S3, a single-shaft gas turbine gas circuit system model is established using the Python simulation platform; S5: Obtain rated operating condition and actual operating data, input the rated operating condition data into the single-shaft gas turbine gas circuit system model built in S4, and analyze the dynamic characteristics of the gas turbine.
2. The refined modeling method for a single-shaft gas turbine gas path system according to claim 1, characterized in that, The specific calculation method for the step-by-step compression compressor module of the single-shaft gas turbine gas circuit system in step S1 is as follows: the continuous compression process inside the compressor is discretized along the spatial distance from the inlet to the outlet, and discretized into... step; Based on the ideal isentropic process, stepwise compression of the first... Temperature value at step Iterative calculation and step-by-step compression of the first step Step temperature The final compressor module outlet temperature was obtained as follows: .
3. The refined modeling method for a single-shaft gas turbine gas path system according to claim 2, characterized in that, The gas temperature change during the stepwise compression process in step S1 satisfies the isentropic integral relationship as follows: In the formula, To compress the first step Pressure value at the step, To compress the first step Pressure value at the step, This represents the equivalent specific heat ratio of the gas at the corresponding temperature. The pressure value is continuous. Simultaneously, an equivalent multi-party index is introduced at each compression step. This is used to provide an equivalent characterization of the isentropic integral term under varying specific heat conditions: Considering the variable specific heat characteristics and the multivariable efficiency correction of the compressor, the step compression... Step temperature Represented as: In the formula, the equivalent multi-party index Represented as: in, For the first The specific heat capacity at step [of point] increases with [the following]. Updated in accordance with changes; For compressor variable efficiency. Let be the gas constant with respect to the gas components, and take . .
4. The refined modeling method for a single-shaft gas turbine gas path system according to claim 1, characterized in that, The specific calculation method for the combustion chamber module of the single-shaft gas turbine gas path system in step S2 is as follows: establish and solve the dynamic evolution differential equation of component mass to obtain the mass fraction of each component at the combustion chamber outlet. The differential equation can be expressed as: In the formula, For the first Mass of each gas component Burning time This indicates the rate of mass change produced or consumed by chemical reactions in the combustion chamber. The total mass flow rate into the combustion chamber inlet. For the combustion chamber inlet Mass fraction of the components The total mass flow rate exiting the combustion chamber is [missing information]. For the combustion chamber inlet Mass fraction of the components; Calculating composition using variable specific heat capacity integral enthalpy : In the formula, Components At temperature The specific heat capacity at constant pressure is For the first Specific enthalpy of the components at a reference temperature For reference temperature, The outlet temperature; For each component of the outlet mixed gas at the outlet temperature The enthalpy of the outlet mixed gas is obtained by taking the weighted average of the specific enthalpy. : In the formula, The outlet mixed gas The proportion and weight of each component; enthalpy of the outlet mixed gas Substituting into the energy conservation equation of the combustion chamber: In the formula, For gas energy, For combustion efficiency, The lower heating value of fuel, The mass flow rate of the air medium. The enthalpy of air. The mass flow rate of the gas medium. The enthalpy of the gaseous medium. The mass flow rate of the exhaust medium; Under steady-state conditions, let The combustion chamber outlet temperature is determined by iteratively solving the energy conservation equation. .
5. The refined modeling method for a single-shaft gas turbine gas path system according to claim 1, characterized in that, The specific calculation method for the step-by-step expansion turbine module of the single-shaft gas turbine gas path system in step S3 is as follows: the continuous expansion process inside the turbine is discretized along the spatial distance from the inlet to the outlet, and discretized into... step; Based on the ideal isentropic process, using stepwise expansion of the first... Temperature value at step Iterative calculation of step-by-step expansion Step temperature The final turbine module outlet temperature was obtained as follows: .
6. The refined modeling method for a single-shaft gas turbine gas path system according to claim 5, characterized in that, The gas temperature change during the stepwise expansion process in step S3 satisfies an isentropic integral relationship, which can be expressed as: In the formula, For step-by-step expansion Pressure value at the step, For step-by-step expansion Pressure value at the step, This represents the equivalent specific heat ratio of the gas at the corresponding temperature. Each expansion step introduces an equivalent multi-party index. This is used to provide an equivalent characterization of the isentropic integral term under varying specific heat conditions: Considering the variable specific heat characteristics and the correction for the variable turbine efficiency, the stepwise compression of the first stage... Step temperature It can be represented as: In the formula, the equivalent multi-party index Represented as: in, For the first The specific heat capacity at step [of point] increases with [the following]. Updated in accordance with changes; For variable turbine efficiency; Let be the gas constant with respect to the gas components, and take . .
7. The refined modeling method for a single-shaft gas turbine gas path system according to claim 1, characterized in that, In step S4, based on the Python simulation platform, the compressor, combustion chamber and turbine component models are encapsulated as independent Python classes, and the parameters passed between the modules are defined using the interface module to realize the calculation of the thermodynamic properties of each component of the gas path system.
8. The refined modeling method for a single-shaft gas turbine gas path system according to claim 1, characterized in that, In step S5, the air mass flow rate under ISO operating conditions is used. Compressor pressure ratio Fuel mass flow rate As input to the simulation model, it is input into the single-shaft gas turbine gas path system model built by S4 to calculate the compressor outlet temperature of the simulation model. Combustion chamber outlet temperature Turbine exhaust temperature Output power ,efficiency Thermal efficiency ratio The calculation results were compared and analyzed with the actual operating data of the gas circuit system.