Numerical simulation batch processing calculation method and system for turbomachinery

Abstract

The invention relates to the technical field of simulation calculation, and discloses an impeller machine numerical simulation batch processing calculation method and system, and the method comprises the steps: carrying out the numerical simulation calculation of a single state of an impeller machine, obtaining a numerical simulation result, and carrying out the post-processing analysis of the numerical simulation result; according to the numerical simulation calculation setting and the post-processing analysis process of the numerical simulation result, making a numerical simulation calculation and post-processing macro file; and batch processing is performed on the macro files subjected to numerical simulation calculation and post-processing, operation based on the macro files is executed circularly, and a numerical simulation analysis report is automatically written. The method automatically completes complex simulation calculation tasks of multiple schemes, multiple rotating speeds and multiple states, has a high automation degree, replaces manual operation, reduces time cost, improves simulation calculation efficiency, avoids errors easily caused by manual numerical simulation calculation, automatically writes a numerical simulation analysis report, and improves simulation calculation efficiency. And data support is provided for subsequent complex tasks such as multi-scheme optimization.

Description

Technical Field

[0001] The present invention relates to the technical field of simulation calculation, and in particular to a batch processing calculation method and system for numerical simulation of turbomachinery. Background Art

[0002] In aircraft engines, the compressor and turbine are two core components whose aerodynamic performance has a crucial impact on the overall performance of the engine, directly affecting its success or failure. Therefore, during engine development, it is often necessary to perform aerodynamic performance simulations on these two core components across multiple scenarios, speeds, and states. This allows for a comprehensive evaluation of the performance of different design options under various operating conditions, and allows for the generation of full-speed characteristic curves for each design. By carefully interpreting and comparing the simulation results, the optimal solution can be selected based on the analysis.

[0003] In existing technologies, numerical simulation calculations must be performed manually, which involves a significant amount of inefficient and repetitive work. This is especially true for simulations involving multiple scenarios and states, where repeated similar settings and operations are required, significantly increasing the time and effort required for manual operation. Furthermore, manual operations are prone to errors due to human oversight, impacting the accuracy and reliability of the simulation. Summary of the Invention

[0004] In view of this, the present invention provides a batch processing calculation method and system for numerical simulation of impeller machinery to solve the problems of manual numerical simulation calculation in the prior art, which is time-consuming and error-prone.

[0005] In a first aspect, the present invention provides a batch processing calculation method for numerical simulation of turbomachinery, the method comprising:

[0006] Perform numerical simulation calculations on a single state of the impeller machinery to obtain numerical simulation results, and perform post-processing analysis on the numerical simulation results;

[0007] According to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results, create macro files for numerical simulation calculation and post-processing;

[0008] Batch process macro files for numerical simulation calculations and post-processing, loop through operations based on macro files, and automatically write numerical simulation analysis reports.

[0009] The present invention performs numerical simulation calculation and post-processing on a single state of the impeller machinery to produce a macro file. By batch processing the macro file and cyclically executing the operations in the macro file, the complex simulation calculation tasks of multiple schemes, multiple speeds, and multiple states are automatically completed. It has a high degree of automation, replaces manual operations, reduces time costs, improves simulation calculation efficiency, avoids the problem of easy errors in manual numerical simulation calculations, automatically writes numerical simulation analysis reports, integrates simulation results into analysis reports, and provides data support for subsequent complex tasks such as multi-scheme optimization.

[0010] In an optional embodiment, numerical simulation calculation is performed on a single state of the impeller machinery to obtain numerical simulation results, and post-processing analysis is performed on the numerical simulation results, including:

[0011] Blade profile data preparation, which includes blade profile geometry data and flow channel data, and the fluid domain is calculated based on the blade profile geometry data and flow channel data;

[0012] Meshing of turbomachinery;

[0013] Perform pre-processing settings for numerical simulation calculations of different working conditions of turbomachinery;

[0014] Start the simulation solver, perform numerical simulation calculations, and obtain numerical simulation results;

[0015] According to the preset convergence criteria, determine whether the numerical simulation results meet the convergence conditions;

[0016] If the numerical simulation results meet the convergence conditions, the numerical simulation results are post-processed and analyzed.

[0017] The present invention provides data support for subsequent aerodynamic performance analysis and optimization by preparing blade profile data, performs grid division to facilitate the analysis of the geometric periodicity of the impeller machinery, performs numerical simulation calculation pre-processing settings for different working states of the impeller machinery, comprehensively evaluates the performance of the impeller machinery under various working conditions, performs numerical simulation calculations and post-processing, and provides data support for the design optimization of the impeller machinery.

[0018] In an optional embodiment, post-processing analysis of the numerical simulation results includes:

[0019] Create and output cloud maps of aerodynamic parameters, which are used to represent the distribution of various parameters in the flow field;

[0020] Draw streamline diagrams, which are used to show the direction and path of fluid flow;

[0021] Calculate and extract key aerodynamic performance parameters, which are used to evaluate the mechanical performance of the impeller;

[0022] Output cloud maps, streamline diagrams and key aerodynamic performance parameters.

[0023] The present invention performs post-processing analysis on the numerical simulation results, outputs cloud maps, streamline diagrams and key aerodynamic performance parameters to facilitate further analysis and report writing, and realizes comprehensive analysis and evaluation of the numerical simulation results, providing data support for the design optimization of impeller machinery.

[0024] In an optional embodiment, the macro file for numerical simulation calculation and post-processing is prepared, including:

[0025] Create macro files to extract blade geometry data files from different modeling schemes;

[0026] Create a macro file for rotating the geometric data of the adjustable guide vane blade profile;

[0027] Create macro files for automatic grid division;

[0028] Create numerical simulation pre-processing setting macro files;

[0029] Create multi-state numerical simulation calculation macro files;

[0030] Create numerical simulation post-processing macro files.

[0031] The present invention creates a macro file for extracting blade geometry data files from different modeling schemes to efficiently complete file extraction, naming and placement, reducing the tediousness of manual operations; creates a macro file for rotating adjustable guide vane blade geometry data to efficiently calculate and generate the geometry data of the rotated adjustable guide vane blades, providing an accurate geometric model basis for data simulation calculations; creates a macro file for automatic grid division to achieve automatic grid division of new blade geometry shapes and flow channels, thereby improving the efficiency and automation of grid division; creates a numerical simulation pre-processing setting macro file to improve pre-processing efficiency; creates a multi-state numerical simulation calculation macro file to efficiently complete multi-state numerical simulation calculation tasks; creates a numerical simulation post-processing macro file to efficiently complete numerical simulation post-processing tasks, providing data support for performance analysis and optimization of impeller machinery.

[0032] In an optional embodiment, creating a macro file for extracting blade profile geometry data files from different modeling schemes includes:

[0033] Extract the blade geometry data file and flow channel data file of each blade row from different modeling scheme folders based on standardized naming rules;

[0034] Rename the extracted blade geometry data file and flow channel data file according to the preset naming rules;

[0035] Place the renamed blade geometry data file and runner data file in the specified folder.

[0036] The present invention creates a macro file that extracts blade geometry data files from different modeling schemes and runs the file to efficiently complete the file extraction, naming and placement tasks, reducing the tediousness of manual operations, improving work efficiency, and ensuring the standardization and accuracy of file management, laying the foundation for subsequent automatic meshing.

[0037] In an optional embodiment, creating a numerical simulation pre-processing setting macro file includes:

[0038] Recording macro commands for grid replacement;

[0039] Edit the macro command and modify the default file path;

[0040] The boundary condition information of each blade is exported and integrated into the pre-processing setting file to generate the pre-processing setting macro file for numerical simulation.

[0041] The present invention creates a numerical simulation pre-processing setting macro file to run the file, thereby improving the efficiency of pre-processing, ensuring the consistency and accuracy of the settings, and providing a basis for subsequent numerical simulation analysis.

[0042] In an optional embodiment, creating a multi-state numerical simulation calculation macro file includes:

[0043] Select a multi-state simulation benchmark working state and use the multi-state benchmark working state as the starting point for all multi-state simulations;

[0044] Write an automatic loading calculation file, call the numerical simulation software to run the calculation, and rename the calculation results according to the preset naming rules to obtain a macro file;

[0045] Set up parameterized interfaces in macro files and automatically update them. The parameterized interfaces are used to adjust key parameters.

[0046] The loop is executed until the simulation calculation of all states is completed.

[0047] The present invention creates a multi-state numerical simulation calculation macro file and runs the file to efficiently complete the multi-state numerical simulation calculation task, providing data support for the performance analysis and optimization of the impeller machinery.

[0048] In an optional embodiment, creating a numerical simulation post-processing macro file includes:

[0049] Select the post-processing baseline working state and use it as the starting point for all post-processing tasks;

[0050] According to the preset parameter list, extract key aerodynamic parameters from the data simulation result file, save them, and generate visualization images;

[0051] According to the preset naming rules, the output aerodynamic parameters and visualization images are renamed to obtain the macro file;

[0052] Set up parameterized interfaces in macro files and automatically update them. The parameterized interfaces are used to adjust key parameters.

[0053] The loop is executed until the post-processing calculations of all states are completed.

[0054] The present invention creates a numerical simulation post-processing macro file and runs the file to efficiently complete the numerical simulation post-processing task, improve the degree of automation, and provide data support for the performance analysis and optimization of the impeller machinery.

[0055] In a second aspect, the present invention provides a batch processing computing system for numerical simulation of turbomachinery, the system comprising:

[0056] The simulation calculation module is used to perform numerical simulation calculations on a single state of the impeller machinery, obtain numerical simulation results, and perform post-processing analysis on the numerical simulation results;

[0057] A macro file making module is used to make macro files for numerical simulation calculation and post-processing according to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results;

[0058] The batch processing module is used to batch process the macro files of numerical simulation calculations and post-processing, cyclically execute operations based on macro files, perform batch processing, and automatically write numerical simulation analysis reports.

[0059] In a third aspect, the present invention provides a computer device comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the batch processing calculation method for numerical simulation of turbomachinery according to the first aspect or any corresponding embodiment thereof by executing the computer instructions.

[0060] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the batch processing calculation method for numerical simulation of turbomachinery according to the first aspect or any corresponding embodiment thereof.

[0061] In a fifth aspect, the present invention provides a computer program product comprising computer instructions for enabling a computer to execute the batch processing calculation method for numerical simulation of turbomachinery according to the first aspect or any corresponding embodiment thereof. BRIEF DESCRIPTION OF THE DRAWINGS

[0062] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0063] Figure 1 is a schematic diagram of a flow chart of a numerical simulation calculation according to an embodiment of the present invention;

[0064] Figure 2 1 is a flow chart of a batch processing calculation method for numerical simulation of turbomachinery according to an embodiment of the present invention;

[0065] Figure 3 is a structural block diagram of a batch processing computing system for numerical simulation of turbomachinery according to an embodiment of the present invention;

[0066] Figure 4 1 is a flow chart of numerical simulation batch processing calculation using a turbomachinery numerical simulation batch processing calculation system according to an embodiment of the present invention;

[0067] Figure 5 Schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0068] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0069] Turbomachinery simulation calculations usually use a single state and multiple calculations to meet the needs of multi-state simulation. The numerical simulation analysis process is as follows: Figure 1 As shown, it mainly includes: blade data preparation, grid division, numerical calculation pre-processing settings, numerical simulation calculation and post-processing, and judges whether all the predetermined multi-scheme, multi-speed, and multi-state simulation calculations are completed. If all calculation states are not completed, the blade data preparation-grid division-numerical calculation pre-processing settings-numerical simulation calculation and post-processing are repeated until the calculation of all states is completed.

[0070] While this single-state, multiple-calculation approach can meet the needs of multi-state simulation, it has many drawbacks in practice, such as heavy repetitive workload, prone to errors, and low efficiency. Therefore, developing more efficient and automated simulation calculation methods is crucial for improving the efficiency of aircraft engine development.

[0071] According to an embodiment of the present invention, an embodiment of a batch processing calculation method for numerical simulation of impeller machinery is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0072] In this embodiment, a batch processing calculation method for numerical simulation of turbomachinery is provided, which can be used in mobile terminals. Figure 2 FIG. 1 is a flow chart of a batch processing calculation method for numerical simulation of turbomachinery according to an embodiment of the present invention. Figure 2 As shown, the process includes the following steps:

[0073] Step S201 : performing numerical simulation calculation on a single state of the impeller machinery to obtain numerical simulation results, and performing post-processing analysis on the numerical simulation results.

[0074] In the embodiments of the present invention, single-state numerical simulation and post-processing refers to the numerical simulation and subsequent result analysis performed for a specific operating state of the turbomachinery (e.g., the design operating point, the rated operating point, or other specific operating state). This step aims to conduct in-depth research on the internal flow characteristics, performance, and related physical phenomena of the turbomachinery under this specific operating condition through numerical simulation, and to extract valuable information through post-processing analysis of the simulation results to guide design optimization or performance evaluation.

[0075] Step S202 , creating a macro file for numerical simulation calculation and post-processing according to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results.

[0076] In an embodiment of the present invention, a macro file for numerical simulation calculation and post-processing is produced to avoid a large amount of inefficient repetitive work caused by manual calculation under multiple schemes, multiple speeds, and multiple states, and the problems of extremely high time cost and easy error of manual operation, so as to facilitate subsequent multi-scheme optimization, guide vane law optimization, air release law optimization, calculation of full-speed characteristics, etc.

[0077] Step S203 , batch processing the macro files of numerical simulation calculation and post-processing, cyclically executing the operations based on the macro files, and automatically writing the numerical simulation analysis report.

[0078] In an embodiment of the present invention, in order to realize complex simulation calculations with multiple schemes, multiple speeds, and multiple states, an automated calculation process is designed. This process, through a loop structure, sequentially executes the following macro-file-based operations: blade geometry data preparation, meshing, numerical simulation calculation pre-processing settings, numerical simulation calculations, and numerical simulation post-processing. By looping through the above macro-file-based operations, complex simulation calculation tasks with multiple schemes, multiple speeds, and multiple states are automatically completed and batch processed. The automated process system not only improves calculation efficiency and reduces manual intervention, but also reduces the risk of errors introduced by repeated operations, providing a solid foundation for performance optimization, design improvement, and the establishment of an optimization platform for impeller machinery.

[0079] After completing numerical simulation and post-processing analysis, a numerical simulation analysis report is automatically written. This step aims to automatically integrate simulation results and transform them into a structured, standardized analysis report, thereby improving work efficiency and reducing human error. The report content typically includes the following aspects: project overview, simulation settings (including grid settings and simulation calculation settings), results presentation, results analysis, conclusions and recommendations, and appendices (simulation input files, output files, references, and other additional information).

[0080] By automatically writing analysis reports based on numerical simulation calculation results, the summary and reporting of simulation projects can be completed efficiently, providing strong support for the design optimization of impeller machinery.

[0081] The batch processing calculation method for numerical simulation of impeller machinery provided in this embodiment performs numerical simulation calculation and post-processing on a single state of the impeller machinery to produce a macro file. By batch processing the macro file, the operations in the macro file are cyclically executed to automatically complete complex simulation calculation tasks with multiple schemes, multiple speeds, and multiple states. It has a high degree of automation, replaces manual operations, reduces time costs, improves simulation calculation efficiency, avoids the error-prone problems of manual numerical simulation calculations, automatically writes numerical simulation analysis reports, integrates simulation results into analysis reports, and provides data support for subsequent complex tasks such as multi-scheme optimization.

[0082] In this embodiment, a batch processing calculation method for numerical simulation of turbomachinery is provided, and the process includes the following steps:

[0083] Step S301 : performing numerical simulation calculation on a single state of the turbomachinery to obtain numerical simulation results, and performing post-processing analysis on the numerical simulation results.

[0084] Specifically, the above step S301 includes:

[0085] Step S3011: prepare blade profile data, and calculate the fluid domain based on the blade profile geometry data and flow channel data.

[0086] In the embodiments of the present invention, blade profile data includes blade geometry data and flow channel data. Blade profile data preparation is a fundamental step in turbomachinery numerical simulation, primarily involving blade profile data preparation and flow channel data preparation. Blade geometry data describes the shape and dimensions of the blades, while flow channel data defines the paths and boundaries of fluid flow. Together, these two types of data form the foundation of the computational fluid domain.

[0087] When performing numerical simulation of turbomachinery, specialized numerical simulation software (such as ANSYS CFX and Fluent) is typically used. By importing blade geometry and flow path data, the numerical simulation software can construct a complete computational fluid domain for subsequent meshing and numerical calculations. Blade geometry and flow path data can be obtained through specialized 3D blade modeling software, dedicated programs, or scripts.

[0088] For turbomachinery with adjustable guide vanes, the guide vane angle can be adjusted to suit different operating conditions. Using specialized software or custom geometric transformation algorithms, guide vane geometry data can be rotated to generate geometric models for different guide vane angles. This adjusted geometry can then be directly used in numerical simulations to investigate the effects of different guide vane angles on aerodynamic performance.

[0089] Blade profile data preparation is crucial for ensuring the accuracy and reliability of numerical simulations. By combining precise blade geometry and flow path data with professional numerical simulation software, the computational fluid domain can be efficiently constructed, providing a solid foundation for subsequent aerodynamic performance analysis and optimization.

[0090] Step S3012: meshing the turbomachinery.

[0091] In the embodiments of the present invention, due to the geometric periodicity of the turbomachinery, professional meshing software (such as ANSYS TurboGrid) is typically used to perform structured meshing. During the meshing process, some key areas require special processing to ensure that the mesh quality meets the requirements of numerical simulation. Specifically, the following steps are included:

[0092] (1) Local grid encryption:

[0093] Local meshing is required for areas such as the leading edge, trailing edge, gap, and near-wall surfaces. The flow characteristics in these areas are complex, and local meshing can improve the mesh's ability to capture flow details, thereby increasing simulation accuracy.

[0094] (2) Setting of blade clearance:

[0095] The blade gap size should be appropriately selected based on the actual mechanical structure. For example, the gap between the rotor blade tip and the stator blade root is typically 0.25 mm. The mesh at the gap can be matched or non-matched along the center of the blade thickness to ensure optimal mesh quality and accurately predict the blade gap flow.

[0096] Step S3013: performing pre-processing settings for numerical simulation calculations of different working states of the turbomachinery.

[0097] In the embodiments of the present invention, the pre-processing setup for turbomachinery numerical simulation calculations is a key step in ensuring simulation accuracy and reliability. It primarily encompasses the following four aspects: model and physics setup, boundary condition setup, solver and discretization method setup, and initial conditions and solver control. When performing numerical simulation calculations for different operating states, the model and physics setup, solver and discretization method setup, and initial conditions and solver control in the pre-processing setup generally remain unchanged. Key parameters such as rotational speed, inlet boundary conditions, and outlet boundary conditions are adjusted to accommodate different operating states.

[0098] In this way, numerical simulation calculations of different working states can be efficiently realized while keeping other settings consistent, thereby comprehensively evaluating the performance of the impeller machinery under various working conditions.

[0099] Step S3014: start the simulation solver, perform numerical simulation calculations, and obtain numerical simulation results.

[0100] In an embodiment of the present invention, when performing a numerical simulation, a simulation solver is activated to begin the calculation process. During the calculation process, key indicators, including residuals and aerodynamic performance parameters, need to be monitored in real time to assess the convergence of the calculation. Residuals are an important indicator that measures the difference between the numerical solution and the exact solution, while aerodynamic performance parameters (such as pressure, velocity, and temperature) reflect the physical state of the simulation model.

[0101] Step S3015: judging whether the numerical simulation result meets the convergence condition according to the preset convergence criterion.

[0102] In an embodiment of the present invention, whether the numerical simulation result has converged is determined according to a preset convergence criterion (for example, the residual error drops to a certain threshold or the aerodynamic performance parameters tend to be stable).

[0103] Step S3016: If the numerical simulation results meet the convergence condition, then post-processing analysis is performed on the numerical simulation results.

[0104] In the embodiment of the present invention, if the numerical simulation results meet the convergence condition, the calculation is considered to be completed. After the numerical simulation results converge, the numerical simulation results are then post-processed and analyzed.

[0105] Specifically, the above step S3016 includes:

[0106] Step S30161, create and output a cloud map of aerodynamic parameters.

[0107] Step S30162, draw a streamline diagram.

[0108] Step S30163: Calculate and extract key aerodynamic performance parameters.

[0109] Step S30164, output cloud map, streamline map and key aerodynamic performance parameters.

[0110] In the embodiment of the present invention, first open the converged calculation result file, and then perform the following operations:

[0111] (a) Create and output cloud maps of aerodynamic parameters such as pressure, velocity, and temperature. These cloud maps can intuitively display the distribution of various parameters in the flow field;

[0112] (b) Draw streamline diagrams to clearly show the direction and path of fluid flow;

[0113] (c) Calculate and extract key aerodynamic performance parameters such as flow rate, pressure ratio, efficiency, etc., which are crucial for evaluating the performance of turbomachinery;

[0114] (d) Output the above analysis results in the form of charts, data tables, etc., and output cloud maps, streamline diagrams and key aerodynamic performance parameters to facilitate further analysis and report writing.

[0115] Through the above steps, the numerical simulation results can be comprehensively analyzed and evaluated, providing strong support for the design optimization of impeller machinery.

[0116] Step S302 : According to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results, a macro file for numerical simulation calculation and post-processing is prepared.

[0117] Specifically, the above step S302 includes:

[0118] Step S3021: Create a macro file for extracting blade geometry data files from different modeling schemes.

[0119] In an embodiment of the present invention, a command macro file can be created to automate the management and preparation of blade geometry and flow path data files. This macro file copies blade geometry and flow path data files from a modeling solution folder based on standardized naming rules, renames them, and then places them in a designated folder.

[0120] Specifically, the above step S3021 includes:

[0121] Step S30211: extract the blade geometry data file and flow channel data file of each blade row from different modeling solution folders based on the standardized naming rules.

[0122] Step S30212: rename the extracted blade geometry data file and flow channel data file according to a preset naming rule.

[0123] Step S30213: placing the renamed blade geometry data file and flow channel data file into a designated folder.

[0124] In an embodiment of the present invention, a macro file is created to extract blade profile geometry data files from different modeling schemes. The macro file can accomplish the following tasks:

[0125] (a) File extraction: Accurately extract the blade geometry data files and flow channel data files of each blade row from multiple different modeling scheme folders based on standardized naming rules.

[0126] (b) Standardized naming: Rename the extracted files according to the preset naming rules to ensure the consistency and recognizability of the file names.

[0127] (c) File placement: Place the renamed file in the designated folder where the mesh is to be divided, providing the required input files for subsequent automatic mesh division.

[0128] By running this macro file, file extraction, naming, and placement can be completed efficiently, reducing the tediousness of manual operations, improving work efficiency, and ensuring the standardization and accuracy of file management, thus laying a solid foundation for the subsequent automatic meshing process.

[0129] The following is an example of a file copy command:

[0130] Copy. / source_folder / subfolder1 / subfolder2 / ... / filename.curve. / destination_fo lder / target_subfolder / ... / filename.curve

[0131] This example copies the files in the specified path to the target path.

[0132] The following are the commands:

[0133] (a) Source Path:

[0134] . / source_folder / subfolder1 / subfolder2 / ... / filename.curve represents the full path to the source file.

[0135] Where: . / indicates the relative path to the current working directory, source_folder is the name of the main folder containing the source files, subfolder1 / subfolder2 / ... indicates the subfolder path where the source files are located, which can be extended according to the actual hierarchical structure, filename.curve is the name of the file to be copied, and the extension .curve indicates the file type.

[0136] (b) Destination Path:

[0137] . / destination_folder / target_subfolder / ... / filename.curve represents the full path to the target file.

[0138] Among them: . / also represents the relative path of the current working directory, destination_folder is the name of the target folder, target_subfolder / ... represents the subfolder path where the target file is located. You can create multiple levels of subfolders as needed. filename.curve is the copied file name, which is the same as the source file name (it can also be changed to another name as needed).

[0139] (c) Command format: Copy is a command used to copy files (usually copy is used in Windows systems and cp is used in Unix-like systems).

[0140] The source and destination paths are separated by a space. Make sure the paths do not contain spaces or special characters. Otherwise, you may need to enclose the paths in quotation marks.

[0141] Step S3022: Create a macro file for rotating the geometric data of the adjustable guide vane profile.

[0142] In an embodiment of the present invention, in order to realize automatic adjustment of the geometric data of the adjustable guide vane blade profile, a special macro file can be created according to the adjustment rules of the guide vane and the coordinate information of the guide vane rotation axis.

[0143] This macro file is used to rotate each row of adjustable guide vanes around its respective rotation axis. When performing a rotation operation, the specific position of the rotation axis and the rotation angle must be specified (positive values ​​for counterclockwise rotation and negative values ​​for clockwise rotation).

[0144] By running this macro file, the geometric data of the rotated adjustable guide vane can be efficiently calculated and generated. This adjusted geometric data will serve as the input file for the subsequent automatic meshing process, providing an accurate geometric model foundation for numerical simulation calculations. This automates the process from geometry adjustment to mesh generation, improving simulation efficiency and accuracy.

[0145] Step S3023: Create a macro file for automatic grid division.

[0146] In an embodiment of the present invention, to improve efficiency and ensure consistent mesh quality, a mesh template can be saved during the meshing process. This mesh template contains the mesh topology, mesh parameters, and other relevant settings. When the meshing software is run, the software automatically re-reads the airfoil geometry and flow path data by loading the mesh template and performs meshing based on the settings in the template.

[0147] By compiling and calling meshing software commands based on mesh templates, meshes for new blade geometries and flow channels can be automatically generated, thereby improving the efficiency and automation of meshing, reducing repetitive work, and ensuring the quality and consistency of meshing for different blades and flow channels.

[0148] Step S3024: Create a numerical simulation pre-processing setting macro file.

[0149] Specifically, the above step S3024 includes:

[0150] Step S30241, recording the macro command for grid replacement.

[0151] Step S30242, edit the macro command and modify the default file path.

[0152] Step S30243: export the boundary condition information of each blade, integrate the boundary condition information into the pre-processing setting file, and generate a pre-processing setting macro file for numerical simulation.

[0153] In this embodiment of the present invention, when performing pre-processing for a single-state numerical simulation, you first need to record a macro command for mesh replacement. After recording, edit the macro command file and modify the default file path to a specified path or relative path to ensure that the mesh file can be loaded correctly.

[0154] Then, the boundary condition information for each blade is exported from the pre-processing setup function module, including key parameters such as speed, inlet and outlet boundary conditions, and interface settings. By integrating these parameters into the pre-processing setup file, a pre-processing setup macro file for numerical simulation is generated. This file then executes a series of macro commands, such as mesh replacement, speed setting, inlet and outlet boundary condition settings, and interface settings, to efficiently generate pre-processing settings suitable for numerical simulations of different states.

[0155] This macro file not only improves the efficiency of pre-processing, but also ensures the consistency and accuracy of the settings, providing a solid foundation for subsequent numerical simulation analysis.

[0156] Step S3025: Create a multi-state numerical simulation calculation macro file.

[0157] In the embodiment of the present invention, the macro file automatically completes the following tasks based on a reference working state: loading numerical simulation calculation files, running numerical simulation calculations, and normalizing the naming of result files.

[0158] Specifically, the above step S3025 includes:

[0159] Step S30251: Select a multi-state reference operating state and use the multi-state reference operating state as the starting point of all multi-state simulations.

[0160] Step S30252, write an automatic loading calculation file, call the numerical simulation software to run the calculation, rename the calculation results according to the preset naming rules, and obtain a macro file.

[0161] Step S30253: Set a parameterized interface in the macro file and automatically update it. The parameterized interface is used to adjust key parameters.

[0162] Step S30254, execute in a loop until the simulation calculations of all states are completed.

[0163] In an embodiment of the present invention, a representative reference working state is selected as the starting point of all multi-state simulations. An automatic loading calculation file is written, and the numerical simulation software is called to run the calculation. According to the preset naming rules (such as including key parameters such as working condition number, speed, flow rate, etc.), the result file after the calculation is completed is renamed to obtain a macro file. A parameterized interface is set in the macro file to allow the user to adjust key parameters (such as speed, inlet flow, outlet pressure, etc.) according to different working states, and automatically update the corresponding settings in the input file. Through the loop structure, multiple working states are processed in turn, and the steps of loading, calculating and naming the result files are repeated until the simulation calculations of all states are completed.

[0164] By creating and running this macro file, multi-state numerical simulation calculation tasks can be completed efficiently, providing strong support for the performance analysis and optimization of impeller machinery.

[0165] Step S3026: Create a numerical simulation post-processing macro file.

[0166] In this embodiment of the present invention, the purpose of the numerical simulation post-processing macro file is to automatically process simulation results, extract key information, and output aerodynamic parameter files and visualization images in a standardized manner. This macro file can complete the following tasks: automatically loading a specified numerical simulation result file, extracting aerodynamic parameters, generating visualization images, and standardizing naming.

[0167] Specifically, the above step S3026 includes:

[0168] Step S30261: Select a post-processing benchmark working state and use the post-processing benchmark working state as the starting point of all post-processing tasks.

[0169] Step S30262: extract key aerodynamic parameters from the data simulation result file according to the preset parameter list, save them, and generate a visual image.

[0170] Step S30263: rename the output aerodynamic parameters and visualization images according to a preset naming rule to obtain a macro file.

[0171] Step S30264: Set a parameterized interface in the macro file and automatically update it. The parameterized interface is used to adjust key parameters.

[0172] Step S30265, execute in a loop until the post-processing calculations of all states are completed.

[0173] In an embodiment of the present invention, a representative benchmark working state is selected as the starting point for all post-processing tasks. Write a program to automatically load numerical simulation result files. According to the preset parameter list, key aerodynamic parameters are extracted from the result file, and these parameters are saved in the specified file (such as CSV, TXT format), and visualization images such as pressure distribution cloud map, velocity vector map, streamline map, etc. are generated and saved to the specified path. According to the preset naming rules (such as key parameters such as working condition number, speed, flow rate, etc.), the output aerodynamic parameter files and picture files are renamed. A parameterized interface is set in the macro file to allow the user to adjust key parameters (such as working condition number, speed, flow rate, etc.) according to different working states, and the name of the output file is automatically updated. Through the loop structure, the result files of multiple working states are processed in turn, and the steps of loading, extracting, generating and naming are repeated until the post-processing of all states is completed.

[0174] The main advantages of post-processing macro files are high automation, reduced errors, easy management, and strong flexibility. By creating and running such macro files, numerical simulation post-processing tasks can be completed efficiently, providing strong support for the performance analysis and optimization of turbomachinery.

[0175] Step S303 , batch processing the macro files of numerical simulation calculation and post-processing, cyclically executing the operations based on the macro files, and automatically writing the numerical simulation analysis report.

[0176] For details, please see Figure 2 Step S203 of the illustrated embodiment will not be described in detail here.

[0177] The batch processing calculation method for the numerical simulation of turbomachinery provided in this embodiment can solve many problems faced in the existing numerical simulation process of turbomachinery when facing multi-scheme, multi-speed, and multi-state simulation requirements, such as low calculation efficiency and easy errors in calculation settings.

[0178] This method offers the following features and functions: automated file extraction, blade geometry rotation, meshing, calculation setup, numerical calculations, and post-processing. Highly automated and easy to use, this method significantly improves computational efficiency and reduces human error. It provides strong support for subsequent complex tasks such as multi-scheme optimization, guide vane pattern optimization, air release pattern optimization, and full-speed characteristic calculation, significantly enhancing the efficiency and reliability of turbomachinery design and optimization.

[0179] In this embodiment, a batch processing computing system for numerical simulation of turbomachinery is also provided. The system is used to implement the above-mentioned embodiments and preferred embodiments. The details that have been described will not be repeated here. As used below, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the system described in the following embodiments is preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and contemplated.

[0180] This embodiment provides a batch processing computing system for numerical simulation of turbomachinery, such as Figure 3 Shown, including:

[0181] The simulation calculation module 301 is used to perform numerical simulation calculation on a single state of the impeller machinery, obtain numerical simulation results, and perform post-processing analysis on the numerical simulation results.

[0182] The macro file making module 302 is used to make a macro file of numerical simulation calculation and post-processing according to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results.

[0183] The batch processing module 303 is used to batch process the macro files of numerical simulation calculation and post-processing, cyclically execute the operations based on the macro files, perform batch processing, and automatically write the numerical simulation analysis report.

[0184] In some optional implementations, the simulation calculation module 301 includes:

[0185] The data preparation unit is used for preparing blade profile data, the blade profile data including blade profile geometry data and flow channel data, and calculating the fluid domain based on the blade profile geometry data and flow channel data.

[0186] Meshing unit, used for meshing turbomachinery.

[0187] The pre-processing setting unit is used to perform pre-processing settings for numerical simulation calculations of impeller machinery in different working states.

[0188] The numerical simulation calculation unit is used to start the simulation solver, perform numerical simulation calculations, and obtain numerical simulation results.

[0189] The judgment unit is used to judge whether the numerical simulation result meets the convergence condition according to the preset convergence criterion.

[0190] The post-processing analysis unit is used to perform post-processing analysis on the numerical simulation results if the numerical simulation results meet the convergence conditions.

[0191] In some optional embodiments, the post-processing analysis unit includes:

[0192] The cloud map creation subunit is used to create and output cloud maps of aerodynamic parameters. The cloud maps are used to represent the distribution of various parameters in the flow field.

[0193] The streamline drawing subunit is used to draw streamline diagrams, which are used to represent the direction and path of fluid flow.

[0194] The calculation subunit is used to calculate and extract key aerodynamic performance parameters, which are used to evaluate the mechanical performance of the impeller.

[0195] The output subunit is used to output cloud maps, streamline maps and key aerodynamic performance parameters.

[0196] In some optional implementations, the macro file creation module 302 includes:

[0197] The first production unit is used to produce a macro file for extracting blade geometry data files from different modeling schemes.

[0198] The second production unit is used to produce a macro file for rotating the geometric data of the adjustable guide vane blade profile.

[0199] The third production unit is used to produce macro files for automatic grid division.

[0200] The fourth production unit is used to produce a numerical simulation pre-processing setting macro file.

[0201] The fifth production unit is used to produce multi-state numerical simulation calculation macro files.

[0202] The sixth production unit is used to produce numerical simulation post-processing macro files.

[0203] In some optional embodiments, the first production unit includes:

[0204] The first extraction subunit is used to extract the blade geometry data file and the flow channel data file of each blade row from different modeling scheme folders based on the standardized naming rules.

[0205] The first renaming subunit is used to rename the extracted blade geometry data file and flow channel data file according to a preset naming rule.

[0206] The file placement subunit is used to place the renamed blade geometry data file and runner data file in the specified folder.

[0207] In some optional embodiments, the fourth production unit includes:

[0208] Recording subunit, used to record macro commands for grid replacement.

[0209] The Edit subunit is used to edit macro commands and modify the default file path.

[0210] The export subunit is used to export the boundary condition information of each blade, integrate the boundary condition information into the pre-processing setting file, and generate the pre-processing setting macro file for numerical simulation.

[0211] In some optional embodiments, the fifth production unit includes:

[0212] The first selection subunit is used to select a multi-state simulation reference working state and use the multi-state reference working state as a starting point for all multi-state simulations.

[0213] The second renaming subunit is used to write an automatic loading calculation file, call the numerical simulation software to run the calculation, and rename the calculation results according to the preset naming rules to obtain a macro file.

[0214] The first updating subunit is used to set a parameterized interface in the macro file and perform automatic updating, wherein the parameterized interface is used to adjust key parameters.

[0215] The first loop subunit is used for loop execution until the simulation calculation of all states is completed.

[0216] In some optional embodiments, the sixth production unit includes:

[0217] The second selection subunit is used to select a post-processing reference working state and use the post-processing reference working state as the starting point of all post-processing tasks.

[0218] The second extraction subunit is used to extract key aerodynamic parameters from the data simulation result file according to a preset parameter list, save them, and generate a visual image.

[0219] The third renaming subunit is used to rename the output aerodynamic parameters and visualization images according to a preset naming rule to obtain a macro file.

[0220] The second updating subunit is used to set a parameterized interface in the macro file and perform automatic updating. The parameterized interface is used to adjust key parameters.

[0221] The second loop subunit is used for loop execution until the post-processing calculations of all states are completed.

[0222] The further functional description of each of the above modules and units is the same as that of the above corresponding embodiments and will not be repeated here.

[0223] The impeller machinery numerical simulation batch processing computing system in this embodiment is presented in the form of functional units, where the units refer to ASIC (Application Specific Integrated Circuit) circuits, processors and memories that execute one or more software or fixed programs, and / or other devices that can provide the above functions.

[0224] like Figure 4 As shown, Figure 4 This is a flow chart for batch processing of turbomachinery simulations using a batch processing system for numerical simulations of turbomachinery. The flow begins with geometric modeling of the turbomachinery blades, followed by automatic preparation of blade profile data based on macro files, automatic meshing based on macro files, numerical simulation pre-processing settings based on macro files, numerical simulation calculations and post-processing based on macro files, and automatic writing of numerical simulation analysis reports. The batch processing system for numerical simulations of turbomachinery can automatically connect the aforementioned single-state numerical simulation macro files, enabling automated loading and operation of blade profile data preparation, meshing, numerical simulation pre-processing settings, numerical simulation calculations, and post-processing, ultimately completing multi-scheme, full-speed aerodynamic performance simulation calculations.

[0225] The embodiment of the present invention also provides a computer device having the above Figure 3 The impeller machinery numerical simulation batch computing system shown.

[0226] See also Figure 5 , Figure 5 is a structural diagram of a computer device provided by an optional embodiment of the present invention, such as Figure 5 As shown, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components utilize different buses to communicate with each other and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in the memory or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Equally, multiple computer devices can be connected, and each device provides part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 5 A processor 10 is taken as an example.

[0227] The processor 10 may be a central processing unit, a network processor, or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic, or any combination thereof.

[0228] The memory 20 stores instructions that can be executed by at least one processor 10, so as to enable at least one processor 10 to execute the method shown in the above embodiment.

[0229] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created based on the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0230] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0231] The computer device further includes an input device 30 and an output device 40. The processor 10, the memory 20, the input device 30 and the output device 40 may be connected via a bus or other means. Figure 5 The bus connection is taken as an example.

[0232] The input device 30 can receive input digital or character information and generate key signal input related to user settings and function control of the computer device, such as a touch screen, etc. The output device 40 can include a display device, etc.

[0233] The embodiment of the present invention also provides a computer-readable storage medium. The above-mentioned method according to the embodiment of the present invention can be implemented in hardware, firmware, or implemented as a computer code that can be recorded in a storage medium, or implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and downloaded through a network and will be stored in a local storage medium, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state drive, etc.; further, the storage medium can also include a combination of the above-mentioned types of memory. It can be understood that a computer, a processor, a microprocessor controller or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor or hardware, the method shown in the above embodiment is implemented.

[0234] A portion of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the form in which the computer program instruction exists in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc. Accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium that can be accessed by the computer.

[0235] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are intended to fall within the scope of this application.

Claims

1. A batch processing calculation method for numerical simulation of turbomachinery, characterized in that: The method comprises: Performing numerical simulation calculation on a single state of the impeller machinery to obtain numerical simulation results, and performing post-processing analysis on the numerical simulation results; According to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results, create macro files for numerical simulation calculation and post-processing; Batch processing is performed on the macro files of the numerical simulation calculation and post-processing, and the operations based on the macro files are executed cyclically to automatically write a numerical simulation analysis report.

2. The method according to claim 1, characterized in that The performing of numerical simulation calculation on a single state of the impeller machinery to obtain numerical simulation results, and performing post-processing analysis on the numerical simulation results, includes: Preparing blade profile data, wherein the blade profile data includes blade profile geometry data and flow channel data, and calculating the fluid domain based on the blade profile geometry data and flow channel data; Meshing of turbomachinery; Perform pre-processing settings for numerical simulation calculations of different working conditions of turbomachinery; Start the simulation solver, perform numerical simulation calculations, and obtain numerical simulation results; According to a preset convergence criterion, determining whether the numerical simulation result meets the convergence condition; If the numerical simulation results meet the convergence condition, the numerical simulation results are post-processed and analyzed.

3. The method according to claim 2, characterized in that The post-processing analysis of the numerical simulation results includes: Creating and outputting a cloud map of aerodynamic parameters, wherein the cloud map is used to represent the distribution of various parameters in the flow field; Draw a streamline diagram, wherein the streamline diagram is used to represent the direction and path of fluid flow; Calculating and extracting key aerodynamic performance parameters, which are used to evaluate the performance of the impeller machinery; The cloud map, the streamline map and the key aerodynamic performance parameters are output.

4. The method according to claim 1, wherein The macro file for producing numerical simulation calculation and post-processing includes: Create macro files to extract blade geometry data files from different modeling schemes; Create a macro file for rotating the geometric data of the adjustable guide vane blade profile; Create macro files for automatic grid division; Create numerical simulation pre-processing setting macro files; Create multi-state numerical simulation calculation macro files; Create numerical simulation post-processing macro files.

5. The method according to claim 4, characterized in that The method of producing a macro file for extracting blade geometry data files from different modeling schemes includes: Extract the blade geometry data file and flow channel data file of each blade row from different modeling scheme folders based on standardized naming rules; Rename the extracted blade geometry data file and flow channel data file according to the preset naming rules; Place the renamed blade geometry data file and runner data file in the specified folder.

6. The method according to claim 4, characterized in that The method of making a numerical simulation pre-processing setting macro file includes: Recording macro commands for grid replacement; Edit the macro command and modify the default file path; The boundary condition information of each blade is exported and integrated into a pre-processing setting file to generate a pre-processing setting macro file for numerical simulation.

7. The method according to claim 4, characterized in that The method of making a multi-state numerical simulation calculation macro file includes: Selecting a multi-state simulation reference operating state, and using the multi-state reference operating state as a starting point for all multi-state simulations; Write an automatic loading calculation file, call the numerical simulation software to run the calculation, and rename the calculation results according to the preset naming rules to obtain a macro file; Setting a parameterized interface in a macro file and automatically updating it, wherein the parameterized interface is used to adjust key parameters; The loop is executed until the simulation calculation of all states is completed.

8. The method according to claim 4, characterized in that The method of making a numerical simulation post-processing macro file includes: Selecting a post-processing baseline working state and using the post-processing baseline working state as a starting point for all post-processing tasks; According to the preset parameter list, extract key aerodynamic parameters from the data simulation result file, save them, and generate visualization images; According to the preset naming rules, the output aerodynamic parameters and visualization images are renamed to obtain the macro file; Setting a parameterized interface in a macro file and automatically updating it, wherein the parameterized interface is used to adjust key parameters; The loop is executed until the post-processing calculations of all states are completed.

9. A batch processing computing system for numerical simulation of turbomachinery, characterized in that: The system comprises: A simulation calculation module is used to perform numerical simulation calculation on a single state of the impeller machinery, obtain numerical simulation results, and perform post-processing analysis on the numerical simulation results; A macro file making module is used to make macro files for numerical simulation calculation and post-processing according to the numerical simulation calculation settings and the post-processing analysis process of the numerical simulation results; The batch processing module is used to batch process the macro files of the numerical simulation calculation and post-processing, cyclically execute the operations based on the macro files, perform batch processing, and automatically write the numerical simulation analysis report.

10. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the batch processing calculation method for numerical simulation of an impeller machinery according to any one of claims 1 to 8 by executing the computer instructions.

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