A Flexible Analysis Method and System for Performance Parameters of a Combustion Chamber Tester

Abstract

A flexible analysis method and system for the performance parameters of a combustion chamber tester, belonging to the field of complex flow field tests. The present invention includes a field layout parameter input module, a combustion chamber geometric modeling module, a simulation calculation module, and a performance parameter fitting module. By means of simulation and fitting, the present invention calculates performance parameters such as combustion efficiency and total pressure loss coefficient. Users can input parameter values matching the actual situation at the site or in the design on the operation interface, so as to conveniently and quickly obtain the combustion chamber performance parameters, providing initial values for the combustion chamber performance test and the comprehensive calibration of performance parameters. The present invention can avoid the computational complexity and uncertainty of estimating the blockage effect in traditional test methods, facilitate the acquisition of combustion chamber performance parameters, and provide a theoretical basis for the comprehensive calibration of combustion chamber performance parameters. The present invention can guide on-site tests, optimize on-site test layouts, and is widely applied to the design, test, and operation and maintenance fields of aeroengine combustion chamber components.

Description

Technical Field

[0001] A flexible analysis method and system for performance parameters of a combustion chamber tester based on numerical simulation and data fitting disclosed by the present invention are applicable to the acquisition and analysis of performance parameters of a combustion chamber tester and belong to the field of complex flow field tests. Background Art

[0002] In aeroengine tests, the combustion chamber component test is one of the key tests for determining the engine performance parameters. The main purpose of the combustion chamber component test is to obtain the combustion chamber performance parameters. The combustion chamber performance parameters mainly include combustion efficiency, total pressure loss coefficient, stability, ignition range, and outlet temperature distribution, etc. However, the parameters closely related to the engine operating conditions are mainly combustion efficiency and pressure loss. The former directly relates to the fuel consumption of the engine (affecting the engine efficiency) and also affects the gas flow rate through the turbine; while the latter directly affects the expansion ratio of the turbine. During actual measurement, due to the intervention of external structures such as sensors and probes, the outlet flow field of the combustion chamber will be disturbed, causing blockage effects and flow field changes, which will affect the accurate acquisition of combustion chamber performance parameters. The blockage effect is caused by the temperature probe and pressure probe extending into the flow channel, and the size of the blockage effect depends on the blockage area, blockage ratio, and gas flow Mach number. To increase the strength of the test probe, the blockage area needs to be increased; to improve the accuracy of the test parameters, the number and blockage ratio of the test probes need to be increased. Therefore, the blockage of the probe has a great impact on the measurement results of combustion chamber performance parameters.

[0003] With the related applications and developments of digital and computer technologies, the processing capabilities and application scopes of numerical simulation and data fitting are also becoming more and more extensive. Applying the related functions of numerical simulation and data fitting to the research of complex parameters such as combustion chamber performance parameters can significantly improve the calculation efficiency and enhance the accuracy and research efficiency of complex parameters such as combustion chamber performance parameters.

[0004] At present, due to the complexity of the combustion process inside the combustion chamber, the research on the performance parameters of the combustion chamber at home and abroad cannot fully give the relationship between the combustion chamber efficiency and pressure loss and the operating conditions by theoretical calculation methods. These relationships are mainly empirical formulas based on experiments. The acquisition of the performance parameters of the combustion chamber and the decoupling of the probe blockage effect are mainly achieved through experimental means. It needs to be further calculated by formulas based on the actually measured single parameters such as temperature and pressure. And the measurement results of the gas flow temperature and gas flow pressure have an important impact on the performance parameters of the combustion chamber. Since the measurement of the gas flow pressure is mainly obtained through various forms of total pressure probes, and the measurement of the gas flow temperature is mainly obtained through various forms of total temperature probes. Therefore, it is necessary to conduct a large number of experiments to study the probe blockage effect under different operating conditions, different sensors, and probe layouts, including axial and circumferential layouts. Due to too many uncertain factors in the experimental process and the inability to ensure sufficient test volume, the calculation process is relatively cumbersome, the uncertainty of the blockage effect estimation is relatively high, and it is difficult to obtain accurate values of the combustion chamber performance parameters. Summary of the Invention

[0005] A flexible analysis method and system for the performance parameters of a combustion chamber tester disclosed by the present invention calculate performance parameters such as combustion efficiency and total pressure loss coefficient through simulation and fitting means. Users can input parameter values that match the actual situation, the site or the design at the operation interface, so as to conveniently and quickly obtain the combustion chamber performance parameters, and provide initial values for the combustion chamber performance test and the comprehensive calibration of performance parameters. The present invention can avoid the cumbersome calculation and uncertainty of the traditional test method for estimating the blockage effect, facilitate the acquisition of the combustion chamber performance parameters, and provide a theoretical basis for the comprehensive calibration of the combustion chamber performance parameters. The present invention can guide on-site tests, optimize the on-site test layout, and is widely applied to the design, test and operation and maintenance fields of aero-engine combustion chamber components.

[0006] The purpose of the present invention is achieved through the following technical solutions:

[0007] A flexible analysis method and system for the performance parameters of a combustion chamber tester disclosed by the present invention include the following steps:

[0008] Step 1: Input the layout parameters of the combustion chamber inlet and outlet. Respectively establish a combustion chamber inlet calculation model and a combustion chamber outlet calculation model, and perform numerical simulation calculations;

[0009] Step 2: Simulate the aerodynamic parameters of the combustion chamber inlet and outlet. Use the existing experimental data to check the accuracy and reliability of the simulation method. On this basis, perform simulation calculations to obtain the total temperature and total pressure values at the inlet and outlet of the combustion chamber under different conditions.

[0010] Step 3: Data fitting of the combustion chamber performance parameter calculation formula. The fitting formulas for each performance parameter of the combustion chamber tester are obtained by using the method of multivariate non-linear function fitting, and then the list values of the combustion chamber performance parameters under different conditions are obtained.

[0011] Step 4: Calculation of each performance parameter of the combustion chamber tester. The numerical calculation process and the data fitting process are encapsulated into a comprehensive simulation calculation system. The user inputs the parameter values matching the site or design according to the actual situation on the operation interface, so as to conveniently and quickly obtain the combustion chamber performance parameters, providing initial values for the combustion chamber performance test and the comprehensive calibration of performance parameters.

[0012] It also includes Step 5: Guiding the on-site test and optimizing the on-site test layout according to the performance parameters of the combustion chamber tester obtained in Step 4.

[0013] The simulation of the pneumatic parameters at the inlet and outlet of the combustion chamber includes different probe numbers under the same probe insertion depth and flow conditions, different probe insertion depths under the same probe number and flow conditions, and different incoming flow Mach numbers under the same probe number and probe insertion depth; the probe types are single-point or multi-point total pressure probes and total temperature probes respectively, which are used to obtain the total temperature and total pressure at the inlet of the combustion chamber under different conditions.

[0014] The calculation of the performance parameters at the outlet of the combustion chamber includes 3 types of different probe numbers under the same probe insertion depth, measurement section position, and rotation speed, 3 types of different probe insertion depths under the same probe number, measurement section position, and rotation speed, 3 types of different measurement section positions under the same probe number, probe insertion depth, and rotation speed, and 3 types of different rotation speeds under the same probe number, probe insertion depth, and measurement section position. The probe types are four-point total pressure probes and five-point total temperature probes respectively, which are used to obtain the total temperature and total pressure at the outlet of the combustion chamber under different conditions, with a total of 48 groups of inlet pressure values and 60 groups of inlet temperature values.

[0015] The fitting formula for the main performance parameters of the combustion chamber tester is a relational expression between a set of performance parameters obtained by numerical analysis of the design values, test values, and numerical simulation results and the probe number, insertion depth, measurement section position, and airflow Mach number.

[0016] The performance parameters of the combustion chamber tester include the total pressure loss coefficient and the combustion efficiency. The performance parameters of the combustion chamber tester under a single state condition are all calculated from the total temperature and total pressure at the inlet and outlet of the combustion chamber under this condition.

[0017] The probe blockage effect is the blockage of the flow channel caused by the temperature probe and the pressure probe extending into the flow channel. The magnitude of the blockage effect depends on the blockage area, blockage ratio, and airflow Mach number.

[0018] A flexible analysis system for the performance parameters of a combustion chamber tester disclosed by the present invention is used to implement the flexible analysis method and system for the performance parameters of the combustion chamber tester, and includes a field layout parameter input module, a combustion chamber geometric modeling module, a simulation calculation module, and a performance parameter fitting module.

[0019] The field layout parameter input module is used to input the number, size, installation layout of the combustion chamber probes, and the environmental parameters of the combustion chamber tester into the simulation calculation interface. The installation layout includes axial and circumferential layouts.

[0020] The combustion chamber geometric modeling module is used to convert the input layout parameters into a geometric model and a calculation model for simulation calculation in software.

[0021] The simulation calculation module is used to perform numerical simulations of pressure, temperature, and flow velocity on the geometric model with specific layout parameters, and output the aerodynamic parameters at the inlet and outlet of the combustion chamber through simulation calculation. The aerodynamic parameters include average temperature and average pressure.

[0022] The performance parameter fitting module is used to fit the obtained aerodynamic parameters at the inlet and outlet of the combustion chamber in the form of a multivariate nonlinear function, and output the values of the combustion chamber performance parameters and their fitting formulas through simulation calculation.

[0023] Beneficial effects:

[0024] 1. For the flexible analysis method and system of the performance parameters of the combustion chamber tester of the present invention, performance parameters such as combustion efficiency and total pressure loss coefficient are calculated through simulation and fitting means. Designers or on-site testers only need to input probe quantity, layout, installation parameters, environmental parameters, etc. in the simulation calculation interface to obtain the combustion chamber performance parameters they care about. The present invention can avoid the cumbersome calculation and uncertainty of estimating the blockage effect in traditional test methods, facilitate the acquisition of combustion chamber performance parameters, and provide a theoretical basis for the comprehensive calibration of combustion chamber performance parameters.

[0025] 2. For the flexible analysis method and system of the performance parameters of the combustion chamber tester of the present invention, it is proposed to combine the numerical simulation results with the data fitting method to obtain a practical and usable fitting formula for the combustion chamber performance parameters, which can calculate the performance parameters of a multi-probe combustion chamber tester, reduce the test volume; and directly obtain the results from the formula in the calculation of the combustion chamber performance parameters with different probe quantities, probe insertion depths, and probe layouts in the future, without the need for numerical simulation again. The present invention has the advantages of time-saving, labor-saving, practicality, good applicability, high efficiency, and multiple functions.

[0026] 3. A flexible analysis method and system for the performance parameters of a combustion chamber tester according to the present invention adopt an existing test data verification simulation method, which has high credibility, can guide on-site tests, optimize on-site test layouts, and can be widely applied to the design, test, and operation and maintenance fields of aero-engine combustion chamber components. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the working process of a flexible analysis method and system for the performance parameters of a combustion chamber tester according to the present invention;

[0028] Figure 2 It is a structural composition diagram of a flexible analysis method and system for the performance parameters of a combustion chamber tester according to the present invention;

[0029] Figure 3 It is a user-friendly interface of a flexible analysis method and system for the performance parameters of a combustion chamber tester according to the present invention;

[0030] Figure 4 It is a layout diagram of temperature and pressure measurement points at the inlet of the combustion chamber of a flexible analysis method and system for the performance parameters of a combustion chamber tester according to the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0031] In order to better illustrate the purpose and advantages of the present invention, the content of the invention will be further described below with reference to the drawings and examples.

[0032] Example 1:

[0033] This example discloses

[0034] Taking a certain combustion chamber tester as an example, a flexible analysis method and system for the performance parameters of a combustion chamber tester are used to illustrate the calculation of combustion efficiency.

[0035] As Figure 1 shown, a flexible analysis method and system for the performance parameters of a combustion chamber tester disclosed in this example mainly include input, simulation, fitting, calculation, and storage in terms of steps. As Figure 2 shown, the system includes input of on-site layout parameters, geometric modeling of the combustion chamber, simulation calculation, and performance parameter fitting. And the entire operation process of performance parameter fitting and calculation of the combustion chamber tester can be realized on the operation interface, and the schematic diagram of the operation interface is as Figure 3 shown.

[0036] In a flexible analysis system for the performance parameters of a combustion chamber tester disclosed in this example:

[0037] The on-site layout parameter input module is used to import the number, size, and installation layout of the combustion chamber probes, including the axial and circumferential layouts, as well as the environmental parameters of the combustion chamber tester, into the simulation calculation system. Among them, the combustion chamber inlet layout parameters include the number and insertion depth of the pressure and temperature probes; the combustion chamber outlet layout parameters include the number, insertion depth, distance from the outlet, and rotational speed of the pressure and temperature probes.

[0038] The combustion chamber geometry modeling module is used to convert the input layout parameters into a geometric model for simulation calculation in the software. By establishing a model and meshing it in Fluent according to the combustion chamber geometry layout parameters, it prepares for the simulation calculation of the average pressure, average temperature at the inlet and outlet of the combustion chamber, the incoming flow Mach number at the inlet, and the highest temperature pneumatic parameter at the outlet.

[0039] The simulation calculation module is used to perform numerical simulations of parameters such as pressure, temperature, and flow velocity on the geometric model with specific layout parameters, simulate and compare the combustion chamber performance parameters under several typical working conditions with the existing test data for verification, use the verified simulation method to simulate the temperature field and flow field at the inlet and outlet of the combustion chamber components, calculate and obtain the performance parameter values such as combustion efficiency and total pressure recovery coefficient under various state layouts, and output them through the simulation calculation interface.

[0040] The performance parameter module fitting is used to fit the obtained pneumatic parameters at the inlet and outlet of the combustion chamber in the form of a multivariate non-linear function to obtain the three performance parameters of the total pressure recovery coefficient, combustion efficiency, and temperature distribution coefficient of the combustion chamber, and encapsulate the numerical calculation process and the data fitting process to form a flexible analysis method for the performance parameters of the combustion chamber tester.

[0041] As Figure 1 shown, a flexible analysis method and system for the performance parameters of a combustion chamber tester disclosed in this embodiment includes the following steps:

[0042] Step 1: Input the layout parameters at the inlet and outlet of the combustion chamber.

[0043] Separate calculation models for the combustion chamber inlet and outlet are established to prepare for numerical simulation calculations. A number of total temperature and total pressure probes arranged axially symmetrically are evenly arranged at the inlet and outlet of the combustion chamber, as Figure 4 shown.

[0044] The numerical calculation model of the combustion chamber inlet includes different numbers of probes under the same probe insertion depth and incoming flow conditions. For the calculation, 2 to 4 values are selected within the range of 2 to 5 pressure and temperature probes each. Different probe insertion depths are considered under the same number of probes and incoming flow conditions. For the calculation, 2 to 4 values are selected within the range of 16 mm to 20 mm from the outer wall surface. Different incoming flow Mach numbers are considered under the same number of probes and probe insertion depth conditions. For the calculation, 2 to 4 values are selected within the range of 0.15 to 0.3. The probe types are single-point or multi-point total pressure probes and total temperature probes respectively, which are used to obtain the total temperature and total pressure at the combustion chamber inlet under different conditions. There are a total of (different numbers of probes × different probe insertion depths × different incoming flow Mach numbers × number of pressure probe measurement points) groups of inlet pressure values and (different numbers of probes × different probe insertion depths × different incoming flow Mach numbers × number of temperature probe measurement points) groups of inlet temperature values.

[0045] The numerical calculation model of the combustion chamber outlet includes 3 types of different numbers of probes under the same probe insertion depth, measurement section position, and rotational speed conditions, 3 types of different probe insertion depths under the same number of probes, measurement section position, and rotational speed conditions, 3 types of different measurement section positions under the same number of probes, probe insertion depth, and rotational speed conditions, and 3 types of different rotational speeds under the same number of probes, probe insertion depth, and measurement section position conditions. The probe types are four-point total pressure probes and five-point total temperature probes respectively, which are used to obtain the total temperature and total pressure at the combustion chamber outlet under different conditions. There are a total of 48 groups of inlet pressure values and 60 groups of inlet temperature values.

[0046] Step 2: Simulation calculation of the aerodynamic parameters at the inlet and outlet of the combustion chamber.

[0047] The simulation calculation is carried out in turn according to the five typical steps of geometric modeling → mesh generation → boundary condition and calculation format setting → numerical solution → result processing. First, a group of typical probe layouts and blockage numerical simulation calculations are carried out, and the accuracy and reliability of the simulation method are verified with existing experimental data. On this basis, other calculations are carried out, including changing the number, size, and installation layout of the probes at the inlet and outlet of the combustion chamber, including axial and circumferential layouts, as well as the environmental parameters of the combustion chamber tester. The temperature field and flow field at the inlet and outlet of the combustion chamber components are simulated to obtain the total temperature and total pressure values at the inlet and outlet of the combustion chamber under different conditions, and the performance parameter values such as combustion efficiency and total pressure recovery coefficient under various state layouts are calculated and obtained.

[0048] Step 3: Data fitting of the calculation formulas for the performance parameters of the combustion chamber.

[0049] The fitting formulas of various performance parameters of the combustor tester are obtained by using the method of multi - variable non - linear function fitting, and then the tabulated values of the combustor performance parameters under different conditions are obtained. The combustor performance parameters include total pressure recovery coefficient, combustion efficiency and temperature distribution coefficient. The fitting formulas of the performance parameters of the combustor tester are a set of relatively ideal relationships between performance parameters and the number of probes, insertion depth, measurement section position, and flow Mach number obtained through mathematical analysis of design values, test values, and numerical simulation results. It is characterized in that the combustor performance parameters under a single state condition can be calculated from aerodynamic parameters such as total temperature and total pressure at the inlet and outlet of the combustor under this condition.

[0050] Step 4: Calculation of the combustion efficiency of the combustor tester.

[0051] The numerical calculation process and data fitting process are encapsulated into a comprehensive simulation calculation system, thus forming a flexible analysis method for the performance parameters of the combustor tester. The flexible analysis method is to encapsulate the numerical calculation process and numerical fitting process to form a friendly man - machine interface for calculating and analyzing the performance parameters of the combustor tester.

[0052] Taking the combustion efficiency as an example, the final results are as follows:

[0053] Fitting formula for the combustion efficiency correction coefficient of the combustor:

[0054] θ = θ test ×Δβ

[0055]

[0056] Δβ = a·d1 b ·N1 c ·Ma d ·N2 e ·d2 f ·p2 g

[0057] Where:

[0058] a = 417.01;

[0059] b = 0.04278;

[0060] c = - 0.62424;

[0061] d = 0.13866;

[0062] e = 0.67155;

[0063] f = - 1.50787;

[0064] g = 0.02634;

[0065] Δβ——Correction coefficient of combustion efficiency in the combustion chamber;

[0066] Θ——Actual combustion efficiency of the combustion chamber;

[0067] θ test ——Combustion efficiency obtained from the test data of the combustion chamber;

[0068] T t3 ——Average temperature measured by the inlet probe of the combustion chamber, unit: K;

[0069] T t4 ——Average temperature measured by the outlet probe of the combustion chamber, unit: K;

[0070] T t4th ——Stagnation temperature at the end of the combustion process when chemical reaction equilibrium is reached, unit: K;

[0071] d1——Insertion depth of the inlet temperature probe of the combustion chamber, unit: mm;

[0072] N1——Number of inlet temperature probes of the combustion chamber;

[0073] Ma——Mach number of the inlet air flow in the combustion chamber;

[0074] N2——Number of outlet temperature probes of the combustion chamber;

[0075] d2——Insertion depth of the outlet temperature probe of the combustion chamber, unit: mm;

[0076] p2——Distance between the temperature probe and the cross-section at the outlet of the combustion chamber, unit: mm; Whether it is caused by measurement.

[0077] The obtained combustion efficiency formula can be represented by fitting through the layout parameters at the inlet and outlet of the combustion chamber on the simulation calculation interface. Designers or on-site test personnel only need to input the number of probes, layout, installation parameters, and environmental parameters, etc. on this platform. After background calculation, the performance parameters of the combustion chamber that they care about can be obtained. Therefore, this simulation calculation system can be used to guide the analysis of probe blockage effect and the prediction calculation and analysis of performance parameters in the combustion chamber test.

[0078] The performance parameters of the combustion chamber tester predicted in this embodiment can guide on-site tests and optimize the on-site test layout. It can be widely applied to the design, test, and operation and maintenance fields of aero-engine combustion chamber components.

[0079] The above specific description further details the purpose, technical solution, and beneficial effects of the invention. It should be understood that the above is only a specific embodiment of the present invention and is not used to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A flexible analysis method for the performance parameters of a combustion chamber tester, characterized in that: It includes the following steps: Step 1: Input the layout parameters of the combustion chamber inlet and outlet; Respectively establish the calculation models for the combustion chamber inlet and outlet, and conduct numerical simulation calculations; Step 2: Simulate the aerodynamic parameters of the combustion chamber inlet and outlet; Use the existing test data to verify the accuracy and reliability of the simulation method. On this basis, conduct simulation calculations to obtain the total temperature and total pressure values at the inlet and outlet of the combustion chamber under different conditions; Step 3: Fit the data of the calculation formulas for the performance parameters of the combustion chamber tester; Use the method of multi-variable non-linear function fitting to obtain the fitting formulas for the performance parameters of each combustion chamber tester, and then obtain the list values of the performance parameters of the combustion chamber tester under different conditions; The fitting formulas for the performance parameters of each combustion chamber tester are a set of relationships between the performance parameters obtained through numerical analysis of the design values, test values, and numerical simulation results and the number of probes, insertion depth, measurement cross-section position, and flow Mach number; The performance parameters of the combustion chamber tester include the total pressure loss coefficient and combustion efficiency. The performance parameters of the combustion chamber tester under a single state condition are all calculated from the total temperature and total pressure at the inlet and outlet of the combustion chamber under this condition; Step 4: Calculate the performance parameters of each combustion chamber tester; Package the numerical calculation process and data fitting process into a comprehensive simulation calculation system. The user inputs the parameter values matching the site or design according to the actual situation on the operation interface, so as to conveniently and quickly obtain the performance parameters of the combustion chamber, providing initial values for the combustion chamber performance test and comprehensive calibration of performance parameters.

2. The flexible analysis method for the performance parameters of a combustion chamber tester as described in claim 1, characterized in that: It also includes Step 5: Guide the on-site test and optimize the on-site test layout according to the performance parameters of each combustion chamber tester obtained in Step 4.

3. A flexible analysis method for the performance parameters of a combustion chamber tester according to claim 2, characterized in that: The simulation of the aerodynamic parameters of the combustion chamber inlet and outlet includes different numbers of probes under the same probe insertion depth and incoming flow conditions, different probe insertion depths under the same number of probes and incoming flow conditions, and different incoming flow Mach numbers under the same number of probes and probe insertion depth; The probe types are single-point or multi-point total pressure probes and total temperature probes respectively, which are used to obtain the total temperature and total pressure at the inlet of the combustion chamber under different conditions.

4. The flexible analysis method for the performance parameters of a combustion chamber tester according to claim 3, wherein: The calculation of the performance parameters at the outlet of the combustion chamber includes 3 types of different numbers of probes under the same probe insertion depth, measurement cross-section position, and rotational speed conditions, 3 types of different probe insertion depths under the same number of probes, measurement cross-section position, and rotational speed conditions, 3 types of different measurement cross-section positions under the same number of probes, probe insertion depth, and rotational speed conditions, and 3 types of different rotational speeds under the same number of probes, probe insertion depth, and measurement cross-section position conditions. The probe types are four-point total pressure probes and five-point total temperature probes respectively, which are used to obtain the total temperature and total pressure at the outlet of the combustion chamber under different conditions, totaling 48 sets of inlet pressure values and 60 sets of inlet temperature values.

5. The flexible analysis method for the performance parameters of a combustion chamber tester according to claim 4, characterized in that: The probe blockage effect is the flow channel blockage caused by the temperature probe and pressure probe extending into the flow channel. The magnitude of the blockage effect depends on the blockage area, blockage ratio, and flow Mach number.

6. A flexible analysis system for the performance parameters of a combustion chamber tester, which is used to implement a flexible analysis method for the performance parameters of a combustion chamber tester as described in claims 1, 2, 3, 4, or 5, characterized in that: It includes a field layout parameter input module, a combustion chamber geometry modeling module, a simulation calculation module, and a performance parameter fitting module; The on-site layout parameter input module is used to input the number, size, installation layout of the combustion chamber probes, and the environmental parameters of the combustion chamber tester into the simulation calculation interface; the installation layout includes axial and circumferential layouts; The combustion chamber geometric modeling module is used to convert the input layout parameters into geometric models and calculation models for simulation calculation in the software; The simulation calculation module is used to perform numerical simulations of pressure, temperature, and flow velocity on the geometric model with specific layout parameters, and obtain the aerodynamic parameters at the inlet and outlet of the combustion chamber through simulation calculation output. The aerodynamic parameters include average temperature and average pressure; The performance parameter fitting module is used to fit the obtained aerodynamic parameters at the inlet and outlet of the combustion chamber in the form of a multivariate non-linear function, and obtain the values of the combustion chamber performance parameters and their fitting formulas through simulation calculation output.

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