Post-processing Method and Device for Combustion Flow Field Based on Parallel Computation of Multi-block Structured Grids

Abstract

The present invention provides a combustion flow field post-processing method and device based on parallel calculation of multiple structural grids, comprising: performing spatial structural modeling and re-gridding on a combustion chamber to be numerically simulated to obtain a structural grid of a three-dimensional configuration of the combustion chamber, and performing rectangular partitioning processing on the structural grid; performing parallel partitioning numerical simulation processing on the partitioned structural grid using a numerical simulation method to obtain original combustion flow field parameter data; confirming the main direction of the partitioned structural grid, and performing equidistant discretization along the main direction of the partitioned structural grid; solving and summing the coordinates of each discrete point in the main direction in each partition based on a method of linear interpolation of adjacent grid points to obtain the integral value of the combustion flow field parameter data of each partition; calculating the integral value of the combustion flow field parameters of all partitions; and using a simulation performance parameter calculation formula to solve and obtain the post-processed combustion flow field parameter data.

Description

Technical Field

[0001] The present invention relates to the fields of computational fluid dynamics and computational combustion, and particularly to a post-processing method and device for a combustion flow field based on parallel computing of a multi-block structured grid. Background Art

[0002] With the rapid development of computer technology, numerical simulation has become one of the three major means of scientific research, alongside theoretical analysis and experimental research. It is widely applied and has contributed to the progress of science, technology, and engineering. Computational fluid dynamics and computational combustion, as numerical simulation means in fluid dynamics and combustion, have achieved good results in many disciplinary fields such as aerospace and energy power.

[0003] A grid is the basis for carrying out parallel computing. Grids are generally divided into structured grids and unstructured grids. A structured grid is defined as all internal points within the grid region having the same adjacent cells. From the perspective of grid node storage, the grid nodes of a structured grid can be stored in the form of a two-dimensional or three-dimensional array. For large eddy simulation, which is widely used currently, to match its requirements for high-precision numerical formats, mostly structured grids are adopted. To accelerate the calculation, it is usually based on a multi-block structured grid and processed through parallel computing methods such as MPI.

[0004] For practical applications with an obvious main direction (the characteristic length in this direction is generally greater than that in other directions, or physical characteristics such as flow and combustion mainly vary along this direction) (such as ramjet engines, high-speed aircraft, etc.), post-processing usually needs to be carried out for the main direction. For example, the variation of some performance parameters or characteristic variables (such as parameters like mixing efficiency, total pressure loss, pressure coefficient, combustibility efficiency, combustion efficiency, average Mach number, etc.) along the main direction. These performance parameters or characteristic variables often need to be subjected to planar integration, weighted average, etc. along the main direction. The results can not only reveal the flow and combustion mechanism but also provide a reference for the optimization of engines and aircraft.

[0005] Currently, there is no widely applied post-processing method for the main direction for the large-scale parallel computing results of multi-block structured grids.

[0006] Tecplot software can perform post-processing display for multi-block structured grids, but when performing operations such as integration, it can only be carried out separately in different partitions and cannot effectively integrate the results of different partitions to form post-processing results along the main direction.

[0007] In some other solutions, all partitions are first integrated into an overall computational domain, and then post-processing is performed on this overall computational domain to obtain physical quantity parameters along the main direction. Its main deficiencies are as follows: First, it has high requirements for the computational configuration and grid topology structure, and is generally only applicable to relatively simple configurations, with poor adaptability to complex configurations; second, its real-time computability is poor, and it is difficult to utilize the advantages of parallel computing, and generally post-processing is performed after the calculation is completed; third, it has a strong dependence on the grid, and it is no longer applicable after the grid changes. Summary of the Invention

[0008] In view of the deficiencies of the prior art, the present invention provides a post-processing method and device for a combustion flow field based on parallel computing of a multi-block structured grid.

[0009] To achieve the above object, the technical solution adopted by the present invention is as follows:

[0010] On the one hand, the present invention provides a post-processing method for a combustion flow field based on parallel computing of a multi-block structured grid, including:

[0011] S1. Perform spatial structure modeling on the combustion chamber to be numerically simulated to obtain a three-dimensional configuration of the combustion chamber, mesh the three-dimensional configuration of the combustion chamber to obtain a structured grid of the three-dimensional configuration of the combustion chamber, and perform rectangular partition processing on the structured grid;

[0012] S2. Use a numerical simulation method to perform parallel partition numerical simulation processing on the partitioned structured grid to obtain original combustion flow field parameter data for post-processing; the original combustion flow field parameters include the density, velocity, pressure, temperature, and mass fractions of each component at each grid node;

[0013] S3. Confirm the main direction of the partitioned structured grid, perform equally spaced discretization along the main direction of the partitioned structured grid to obtain the number of discrete points along the main direction and the coordinates of the discrete points along the main direction;

[0014] S4. Based on the method of linear interpolation of adjacent grid points, solve the coordinates of each discrete point along the main direction in each partition, and sum the solution results of the coordinates of the discrete points along the main direction in each partition to obtain the integral value of the combustion flow field parameter data corresponding to each partition;

[0015] S5. Sum the integral values of the combustion flow field parameters of each partition to obtain the integral value of the combustion flow field parameters of all partitions;

[0016] S6. Based on the integral values of the combustion flow field parameters of all partitions, use the simulation performance parameter calculation formula to solve and obtain the post-processed combustion flow field parameter data.

[0017] Further, in step S1, the combustion chamber is a ramjet combustion chamber, including fuel injection holes for injecting fuel, a cavity for promoting mixing and improving flame stability, a combustion chamber inlet, a combustion chamber outlet, an upper wall surface, a lower wall surface, and side wall surfaces.

[0018] Further, in step S1, the structured grid is a rectangular grid; the partitioning method ensures that the number of grids contained in each partition is equal or the difference in the number of grids in each partition is within a set range, so that the computational load of each partition is balanced.

[0019] Further, in step S4, solving the coordinates of each discrete point in the main direction within each partition includes:

[0020] For the th partition, being the number of partitions, ; the number of nodes of the structured grid of the i c th partition along the x, y, and z directions are respectively , , , and the X, Y, and Z coordinates of the structured grid are all three-dimensional arrays, , , ;

[0021] Within each partition, for the discrete point coordinates along the main direction, traverse all grid nodes in the y and z directions of the structured grid to determine the range of the main direction line segment when the y and z directions are given ,

[0022] ;

[0023] ;

[0024] Among them, , being the number of discrete points along the main direction; j being the y-direction coordinate of the grid node, ; k being the z-direction coordinate of the grid node, ; being the i c th partition's number of grid nodes in the x direction, and the x direction is the main direction; being the i c th partition's number of grid nodes in the y direction; being the i c th partition's number of grid nodes in the z direction;

[0025] Determine whether the coordinates of the th discrete point along the main direction are located inside. If it is located inside, obtain the combustion flow field parameter data of the discrete point coordinates by linear interpolation of adjacent grid points; if it is located outside, the combustion flow field parameter data of the discrete point coordinates is 0.

[0026] Furthermore, in step S4, the method of linear interpolation of adjacent grid points includes:

[0027] Determine the interpolation interval and the corresponding grid point identifier i such that the discrete point coordinates are located in the i th grid, that is, satisfy ;

[0028] Based on the interpolation interval, obtain the combustion flow field parameter data of the discrete point coordinates by linear interpolation,

[0029] ;

[0030] ;

[0031] where A ( x ) is the cross-sectional area at the position of the main direction coordinate x , Y is the mass fraction of the fuel component, Y r is the mass fraction of the fuel component that can undergo chemical reactions; is the density of the mixed gas in the combustion chamber; is the x-direction velocity of the mixed gas in the combustion chamber; is the cross-sectional area at the grid node ; is the cross-sectional area at the grid node .

[0032] Furthermore, in step S4, the integral value of the combustion flow field parameter data corresponding to each partition includes:

[0033] Traverse all grid nodes in the y-direction and z-direction of the structured grid, and accumulate and sum the combustion flow field parameter data of the discrete point coordinates of each partition,

[0034] ;

[0035] ;

[0036] Obtain the integral value of the combustion flow field parameter data corresponding to each partition.

[0037] Further, in step S5, obtaining the integral values of the combustion flow field parameters of all partitions includes:

[0038] Traverse all partitions, accumulate and sum the integral values of the combustion flow field parameter data of each partition to obtain the integral values of the combustion flow field parameters of all partitions.

[0039] ;

[0040] .

[0041] Further, in step S6, the combustion flow field parameter data after post - processing obtained by solving using the simulation performance parameter calculation formula includes:

[0042] According to the mixing efficiency Calculation formula:

[0043] ;

[0044] Substitute the integral values of the combustion flow field parameters of all partitions into the calculation to solve for the mixing efficiency after post - processing , as shown in the following formula:

[0045] .

[0046] Further, Y r Solve through the following formula:

[0047] ;

[0048] Wherein, Y st Is the mass fraction of the fuel component at complete reaction.

[0049] On the other hand, the present invention provides a combustion flow field post - processing device based on multi - block structured grid parallel computing, including:

[0050] A configuration partition processing module, used to perform spatial structure modeling on the combustion chamber to be numerically simulated, obtain the three - dimensional configuration of the combustion chamber, mesh the three - dimensional configuration of the combustion chamber to obtain the structured grid of the three - dimensional configuration of the combustion chamber, and perform rectangular partition processing on the structured grid;

[0051] A numerical simulation module, which is used to perform parallel partition numerical simulation processing on the partitioned structured grid by using numerical simulation methods, and obtain the original combustion flow field parameter data for post-processing; the original combustion flow field parameters include the density, velocity, pressure, temperature, and mass fraction of each component at each grid node;

[0052] A positioning and acquisition module, which is used to confirm the main direction of the partitioned structured grid, divide the main direction with equally spaced discrete points, and obtain the number of discrete points along the main direction and the coordinates of the discrete points along the main direction;

[0053] An integral value calculation module, which is used to solve the coordinates of each discrete point in the main direction in each partition based on the method of linear interpolation of adjacent grid points, and sum the solution results of the coordinates of the discrete points in the main direction in each partition to obtain the integral value of the combustion flow field parameter data corresponding to each partition; sum the integral values of the combustion flow field parameters of each partition to obtain the integral value of the combustion flow field parameters of all partitions;

[0054] A data solution module, which is used to solve the post-processed combustion flow field parameter data based on the integral values of the combustion flow field parameters of all partitions by using the simulation performance parameter calculation formula.

[0055] Compared with the prior art, the technical effects that the present invention can produce are:

[0056] The combustion flow field post-processing method and device based on multi-block structured grid parallel computing provided by the present invention do not need to be integrated into a complete computational domain, and can be distributedly processed during the calculation of each partition, making full use of the advantages of large-scale parallelism, and can conveniently process relatively complex regions; at the same time, the processing method has a certain generality. When the topology of the computational domain remains unchanged, even if the computational grid is adjusted, the post-processing method and the discrete grid in the main direction can remain unchanged. Therefore, the present invention has a wide range of applications.

[0057] The present invention synchronously calculates the physical quantities along the main direction during the iterative calculation of the flow field in each partition. Therefore, the present invention can be used to analyze the dynamic characteristics of the flow field, make real-time judgments on the calculation results, etc.

[0058] The present invention utilizes the partition characteristics of the computational domain itself for parallel processing, greatly improving the calculation efficiency, and is suitable for situations where post-processing is frequent and high real-time requirements are imposed. BRIEF DESCRIPTION OF THE DRAWINGS

[0059] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on the structures shown in these drawings without creative efforts.

[0060] Figure 1 Schematic diagram of the post-processing method for combustion flow field based on parallel computing of multi-block structured grids provided for an embodiment;

[0061] Figure 2 Schematic diagram of the structure of a ramjet combustor provided for an embodiment;

[0062] Figure 3 Schematic diagram of the structured grid and zoning of a ramjet combustor provided for an embodiment;

[0063] Figure 4 Schematic diagram of the discrete points in the main direction and their coordinates provided for an embodiment;

[0064] Figure 5 Schematic diagram of the number of grid points in three directions and the structured grid number of a single zone provided for an embodiment;

[0065] Figure 6 Main direction line segment interval of a single zone provided for an embodiment Schematic diagram;

[0066] Figure 7 Main direction line segment intervals of three zones A, B, and C provided for an embodiment and the calculation of physical quantity values at the discrete point coordinates Schematic diagram;

[0067] Figure 8 Interpolation interval provided for an embodiment and the corresponding grid point representation i Schematic diagram;

[0068] Figure 9 Schematic diagram of the variation of mixing efficiency along the main direction provided for an embodiment.

[0069] Appendix annotation:

[0070] 1. Ramjet combustor; 2. Ramjet combustor inlet; 3. Fuel injection hole; 4. Cavity; 5. Lower wall surface; 6. Ramjet combustor outlet; 7. Upper wall surface; 8. Side wall surface. Detailed implementation manners

[0071] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0072] Refer toFigure 1 , in one embodiment, a post-processing method for a combustion flow field based on parallel computing of multiple structured grids is provided, including:

[0073] S1. Perform a spatial structure modeling on the combustion chamber to be numerically simulated to obtain a three-dimensional configuration of the combustion chamber, mesh the three-dimensional configuration of the combustion chamber to obtain a structured grid of the three-dimensional configuration of the combustion chamber, and perform a rectangular partitioning process on the structured grid;

[0074] S2. Use a numerical simulation method to perform a parallel partition numerical simulation process on the partitioned structured grid to obtain the original combustion flow field parameter data for post-processing; the original combustion flow field parameters include the density, velocity, pressure, temperature, and mass fractions of each component at each grid node;

[0075] S3. Confirm the main direction of the partitioned structured grid, perform an equally spaced discretization along the main direction of the partitioned structured grid to obtain the number of discrete points along the main direction and the coordinates of the discrete points along the main direction;

[0076] S4. Based on the method of linear interpolation of adjacent grid points, solve the coordinates of each discrete point along the main direction in each partition, and perform a summation process on the solution results of the coordinates of the discrete points along the main direction in each partition to obtain the integral value of the combustion flow field parameter data corresponding to each partition;

[0077] S5. Perform a summation process on the integral values of the combustion flow field parameters of each partition to obtain the integral values of the combustion flow field parameters of all partitions;

[0078] S6. Based on the integral values of the combustion flow field parameters of all partitions, use the simulation performance parameter calculation formula to solve and obtain the post-processed combustion flow field parameter data.

[0079] Refer to Figure 2 , in one embodiment, in step S1, the combustion chamber is a ramjet combustion chamber 1, including a fuel injection hole 3 for injecting fuel, a cavity 4 for promoting mixing and improving flame stability, a combustion chamber inlet 2, a combustion chamber outlet 6, an upper wall surface 7, a lower wall surface 5, and a side wall surface 8.

[0080] Refer to Figure 3 , in one embodiment, in step S1, use the grid pre-processing software Pointwise to perform a spatial structure modeling on the ramjet combustion chamber to obtain a three-dimensional configuration of the combustion chamber, then mesh the three-dimensional configuration of the combustion chamber to obtain a structured grid of the three-dimensional configuration of the combustion chamber, and perform a rectangular partitioning process on the structured grid. The structured grid is a rectangular grid; the partitioning method ensures that the number of grids included in each partition is equal or the difference in the number of grids in each partition is within a set range, so that the calculation load of each partition is balanced. In this embodiment, the structured grid is divided into 30 partitions.

[0081] Refer toFigure 4 , confirm the main direction of the structured grid after zoning ( x ), perform equally spaced discretization along the main direction of the structured grid after zoning, and obtain the number of discrete points along the main direction ( is a positive integer, generally greater than 100 to ensure a smoother post-processing result) and the coordinates of the discrete points along the main direction ; In particular, the coordinates of the discrete points can be the same as the coordinates of the grid points.

[0082] In step S4, solving the coordinates of each discrete point in the main direction within each zone includes:

[0083] For the th zone, is the number of zones, ; The number of nodes of the i c th zone structured grid in the x, y, and z directions are respectively , , , and the X, Y, and Z coordinates of the structured grid are all three-dimensional arrays, , , ; In an embodiment, , the number of grid points in the three directions of a single zone and the structured grid number are as Figure 5 shown.

[0084] Referring to Figure 6 , within each zone, for the coordinates of the discrete points along the main direction, traverse all the grid nodes in the y and z directions of the structured grid to determine the range of the main direction line segment when the y and z directions are given ,

[0085] ;

[0086] ;

[0087] Among them, , is the number of discrete points along the main direction; j is the y-direction coordinate of the grid node, ; k is the z-direction coordinate of the grid node, ; is the number of grid nodes in the x direction of the i c th zone, and the x direction is the main direction; is the number of grid nodes in the y direction of the i c th zone; is the number of grid nodes in the z - direction of the i c th partition;

[0088] Judge whether the coordinates of the th discrete point along the main direction are within . If it is within , obtain the data of the combustion flow - field parameters of the discrete - point coordinates by linear interpolation of adjacent grid points; if it is outside , the data of the combustion flow - field parameters of the discrete - point coordinates is 0.

[0089] Referring to Figure 7 and Figure 8 , the method of linear interpolation of adjacent grid points includes:

[0090] As shown in Figure 8 , determine the interpolation interval and the corresponding grid - point identifier i , so that the discrete - point coordinates are within the i th grid, that is, satisfy ;

[0091] Based on the interpolation interval, obtain the data of the combustion flow - field parameters of the discrete - point coordinates by linear interpolation,

[0092] ;

[0093] ;

[0094] Among them, A ( x ) is the cross - sectional area at the position of the main - direction coordinate x , Y is the mass fraction of the fuel component, Y r is the mass fraction of the fuel component that can undergo chemical reactions; is the density of the mixed gas in the combustion chamber; is the x - direction velocity of the mixed gas in the combustion chamber; is the cross - sectional area at the grid node ; is the cross - sectional area at the grid node .

[0095] As shown in Figure 7 , linear interpolation is performed on partitions A and B to obtain the discrete - point coordinates For the combustion flow field parameter data, the combustion flow field parameter data at the discrete point coordinates in Zone C is 0.

[0096] The present invention uses the method of linear interpolation of adjacent grid points to solve the coordinates of each discrete point in the main direction within each zone, so as to estimate and fill in the missing data points in the zone grid, making the data in each zone more complete and facilitating subsequent analysis and processing. Moreover, using the method of linear interpolation of adjacent grid points can ensure the progress of processing when the calculation grid is adjusted, improving the applicable range of the present invention.

[0097] In step S4, obtaining the integral value of the combustion flow field parameter data corresponding to each zone includes:

[0098] Traverse all grid nodes in the y-direction and z-direction of the structured grid, and sum up the combustion flow field parameter data of the discrete point coordinates in each zone.

[0099] ;

[0100] .

[0101] Obtain the integral value of the combustion flow field parameter data corresponding to each zone.

[0102] In step S5, obtaining the integral value of the combustion flow field parameter of all zones includes:

[0103] Traverse all zones, sum up the integral values of the combustion flow field parameter data of each zone, and obtain the integral value of the combustion flow field parameter of all zones.

[0104] ;

[0105] .

[0106] In step S6, solving the combustion flow field parameter data after post-processing by using the simulation performance parameter calculation formula includes:

[0107] According to the calculation formula of the mixing efficiency :

[0108] ;

[0109] Substitute the integral values of the combustion flow field parameter of all zones into the calculation to solve the mixing efficiency after post-processing, as shown in the following formula:

[0110] .

[0111] Y r Solve through the following formula:

[0112] ;

[0113] Among them, Y st is the mass fraction of the fuel component at complete reaction; for the reaction of a determined fuel component, Y st is a constant.

[0114] In the present invention, physical quantities along the main direction are synchronously calculated during the iterative calculation of the flow field in each partition. Therefore, the present invention can be used to analyze the dynamic characteristics of the flow field and make real-time judgments on the calculation results.

[0115] Referring to Figure 9 , Figure 9 is a schematic diagram showing the change of the mixing efficiency along the main direction provided in an embodiment.

[0116] In one embodiment, a post-processing device for a combustion flow field based on parallel calculation of multi-block structured grids is provided, including:

[0117] A configuration partition processing module for performing spatial structure modeling on a combustion chamber to be numerically simulated, obtaining a three-dimensional configuration of the combustion chamber, meshing the three-dimensional configuration of the combustion chamber to obtain a structured grid of the three-dimensional configuration of the combustion chamber, and performing rectangular partition processing on the structured grid;

[0118] A numerical simulation module for performing parallel partition numerical simulation processing on the partitioned structured grid by using a numerical simulation method to obtain original combustion flow field parameter data for post-processing; the original combustion flow field parameters include the density, velocity, pressure, temperature, and mass fraction of each component at each grid node;

[0119] A positioning and acquisition module for confirming the main direction of the partitioned structured grid, dividing the main direction with equally spaced discrete points, and obtaining the number of discrete points along the main direction and the coordinates of the discrete points along the main direction;

[0120] An integral value calculation module for solving the coordinates of each discrete point along the main direction in each partition based on the method of linear interpolation of adjacent grid points, and performing summation processing on the solution results of the coordinates of the discrete points along the main direction in each partition to obtain the integral value of the combustion flow field parameter data corresponding to each partition; performing summation processing on the integral values of the combustion flow field parameters of each partition to obtain the integral value of the combustion flow field parameters of all partitions;

[0121] A data solution module for solving the post-processed combustion flow field parameter data based on the integral values of the combustion flow field parameters of all partitions by using a simulation performance parameter calculation formula.

[0122] Matters not described in the present invention are well-known technologies.

[0123] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope recorded in this specification.

[0124] The above-described embodiments merely represent several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation on the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the appended claims.

[0125] The above is only the preferred embodiment of the present invention and is not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. 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 combustion flow field post-processing method based on multi-block structured grid parallel computing, characterized in that: include: S1. Perform spatial structural modeling on a combustion chamber to be numerically simulated to obtain a three-dimensional configuration of the combustion chamber, grid the three-dimensional configuration of the combustion chamber to obtain a structural grid of the three-dimensional configuration of the combustion chamber, and perform rectangular partitioning on the structural grid; S2. Using a numerical simulation method to perform parallel partition numerical simulation processing on the partitioned structural grid to obtain original combustion flow field parameter data for post-processing; The original combustion flow field parameters include the density, velocity, pressure, temperature, and mass fraction of each component at each grid node; S3, confirming the main direction of the structure grid after partitioning, performing equidistant discretization along the main direction of the structure grid after partitioning, and obtaining the number of discrete points along the main direction and the coordinates of the discrete points along the main direction; S4. Based on the method of linear interpolation of adjacent grid points, the coordinates of each discrete point in the main direction are solved in each partition, and the solution results of the coordinates of the discrete points in the main direction in each partition are summed to obtain the integral value of the combustion flow field parameter data corresponding to each partition; S5, summing the integral values ​​of the combustion flow field parameters of each partition to obtain the integral values ​​of the combustion flow field parameters of all partitions; S6. Based on the integral values ​​of the combustion flow field parameters of all partitions, the simulation performance parameter calculation formula is used to solve and obtain the post-processed combustion flow field parameter data.

2. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 1, characterized in that: In step S1, the combustion chamber is a ramjet combustion chamber, including a nozzle for injecting fuel, a cavity for promoting mixing and improving flame stabilization capability, a combustion chamber inlet, a combustion chamber outlet, an upper wall surface, a lower wall surface, and a side wall surface.

3. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 2 is characterized in that: In step S1, the structured grid is a rectangular grid; the partitioning process ensures that the number of grids contained in each partition is equal or the difference in the number of grids in each partition is within a set range, so that the calculation load of each partition is balanced.

4. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to any one of claims 1 to 3, characterized in that: In step S4, solving the coordinates of each discrete point in the main direction in each partition includes: For partitions, is the number of partitions, ;No. i c The number of nodes in the partition structure grid along the x, y, and z directions are , , , the X, Y, and Z coordinates of the structure grid are all three-dimensional arrays, , , ; In each partition, the coordinates of discrete points along the main direction are , traverse all grid nodes in the y and z directions of the structural grid, and determine the main direction line segment interval range when the y and z directions are given , in, , is the number of discrete points along the main direction; j is the y-coordinate of the grid node, ; k is the z-coordinate of the grid node, ; For the i c The number of grid nodes in the x direction of each partition, where the x direction is the main direction; For the i c The number of grid nodes in the y direction of each partition; For the i c The number of grid nodes in the z direction of each partition; Determine the first Discrete point coordinates Is it located in If within If the coordinates of discrete points are within , the linear interpolation method of the adjacent grid points is used to obtain the coordinates of the discrete points. Combustion flow field parameter data; if located at In addition, the coordinates of the discrete points The combustion flow field parameter data is 0.

5. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 4 is characterized in that: In step S4, the method of linear interpolation of adjacent grid points includes: Determine the interpolation interval and the corresponding grid point identifier i , so that the coordinates of the discrete points Located in i Within the grid, that is, ; Based on the interpolation interval, the coordinates of discrete points are obtained by linear interpolation. Combustion flow field parameter data, in, A ( x ) is the main direction coordinate x The cross-sectional area at the location, Y is the fuel component mass fraction, Y r is the mass fraction of the fuel component that can undergo chemical reactions; is the density of the mixed gas in the combustion chamber; is the x-direction velocity of the mixed gas in the combustion chamber; For grid nodes The cross-sectional area at For grid nodes The cross-sectional area at .

6. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 1, characterized in that: In step S4, obtaining the integral value of the combustion flow field parameter data corresponding to each partition includes: Traverse all grid nodes in the y and z directions of the structural grid, and calculate the coordinates of the discrete points in each partition The combustion flow field parameter data are accumulated and summed. The integral value of the combustion flow field parameter data corresponding to each partition is obtained.

7. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 1, characterized in that: In step S5, the integral values ​​of the combustion flow field parameters of all partitions are obtained, including: Traverse all partitions, accumulate and sum the integral values ​​of the combustion flow field parameter data of each partition, and obtain the integral values ​​of the combustion flow field parameters of all partitions. 。 8. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 1, characterized in that: In step S6, the post-processed combustion flow field parameter data is obtained by using the simulation performance parameter calculation formula, including: According to the mixing efficiency The calculation formula is: Substitute the integral values ​​of the combustion flow field parameters of all partitions into the calculation to obtain the post-processing mixing efficiency , as shown below: 。 9. The combustion flow field post-processing method based on multi-block structured grid parallel computing according to claim 8, characterized in that: Y r Solve by the following formula: in, Y st is the mass fraction of the fuel component when the reaction is complete.

10. A combustion flow field post-processing device based on multi-block structured grid parallel computing, characterized in that: include: A configuration partition processing module is used to perform spatial structural modeling on the combustion chamber to be numerically simulated, obtain a three-dimensional configuration of the combustion chamber, grid the three-dimensional configuration of the combustion chamber, obtain a structural grid of the three-dimensional configuration of the combustion chamber, and perform rectangular partition processing on the structural grid; A numerical simulation module is used to perform parallel partition numerical simulation processing on the partitioned structural grid using a numerical simulation method to obtain original combustion flow field parameter data for post-processing; The original combustion flow field parameters include the density, velocity, pressure, temperature, and mass fraction of each component at each grid node; The positioning acquisition module is used to confirm the main direction of the structure grid after partitioning, divide the main direction with discrete points at equal intervals, and obtain the number of discrete points along the main direction and the coordinates of the discrete points along the main direction; The integral value calculation module is used to solve the coordinates of each discrete point in the main direction in each partition based on the method of linear interpolation of adjacent grid points, and sum the solution results of the discrete point coordinates in the main direction in each partition to obtain the integral value of the combustion flow field parameter data corresponding to each partition; sum the integral values ​​of the combustion flow field parameters of each partition to obtain the integral values ​​of the combustion flow field parameters of all partitions; The data solving module is used to solve the post-processed combustion flow field parameter data based on the integral value of the combustion flow field parameters of all partitions using the simulation performance parameter calculation formula.

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