Combustion flow field post-processing method and device based on multi-block structured grid parallel computing

Abstract

The invention provides a combustion flow field post-processing method and device based on parallel computing of multiple structured grids, and the method comprises the steps: carrying out the spatial structure modeling and gridding of a combustion chamber to be subjected to numerical simulation, obtaining the structured grids of the three-dimensional configuration of the combustion chamber, and carrying out the rectangular partitioning processing of the structured grids; performing parallel partition numerical simulation processing on the partitioned structural grids by adopting a numerical simulation method to obtain original combustion flow field parameter data; determining the main direction of the partitioned structural grid, and performing equidistant discretization along the main direction of the partitioned structural grid; based on a near grid point linear interpolation method, solving and summing each discrete point coordinate in the main direction in each partition to obtain an integral value of the combustion flow field parameter data of each partition; integral values of the combustion flow field parameters of all the partitions are calculated; and solving by using a simulation performance parameter calculation formula to obtain 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 in particular to a combustion flow field post-processing method and device based on multi-block structure network parallel computing. 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 used and has contributed to the progress of science, technology and engineering. Computational fluid dynamics and computational combustion, as numerical simulation methods used in fluid mechanics and combustion, have achieved good results in many disciplines such as aerospace, energy and power.

[0003] Grid is the basis for parallel computing. Grids are generally divided into structured grids and unstructured grids. A structured grid is defined as a grid area in which all internal points have 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 the currently widely used large eddy simulation, structured grids are mostly used to match its requirements for high-precision numerical formats. In order to speed up the calculation, it is usually based on multi-block structured grids and processed through parallel computing methods such as MPI.

[0004] For practical applications (such as ramjet engines, high-speed aircraft, etc.) with obvious main directions (the characteristic length of this direction is generally greater than that of other directions, or the physical characteristics of flow, combustion, etc. mainly change along this direction), it is usually necessary to post-process the main direction. For example, the changes of some performance parameters or characteristic variables (such as mixing efficiency, total pressure loss, pressure coefficient, flammability efficiency, combustion efficiency, average Mach number, etc.) along the main direction, these performance parameters or characteristic variables often need to be processed by plane integration, weighted average, etc. along the main direction. The results can not only reveal the flow combustion mechanism, but also provide a reference for the optimization of engines and aircraft.

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

[0006] Tecplot software can post-process and display multiple structural grids, but when performing operations such as integration, it can only be performed separately in different partitions, and the results of different partitions cannot be effectively integrated to form post-processing results along the main direction.

[0007] Some other solutions first integrate all partitions into an overall calculation domain, and then post-process the overall calculation domain to obtain the physical quantity parameters along the main direction. Its main shortcomings are: first, it has high requirements for the calculation configuration and grid topology structure, and is generally only applicable to relatively simple configurations, and has poor adaptability to complex configurations; second, it has poor real-time calculation performance and is difficult to take advantage of parallel computing. It is generally processed after the calculation is completed; third, it has a strong dependence on the grid and is no longer applicable after the grid changes. Summary of the invention

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

[0009] To achieve the above purpose, the technical solution adopted by the present invention is as follows: In one aspect, the present invention provides a combustion flow field post-processing method based on multi-block structured grid parallel computing, comprising: 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 density, velocity, pressure, temperature, and mass fraction of each component of 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.

[0010] Furthermore, 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.

[0011] Furthermore, 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 calculation load of each partition is balanced.

[0012] Furthermore, 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.

[0013] Furthermore, 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 .

[0014] Furthermore, 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 structure 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.

[0015] Furthermore, 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. ; .

[0016] Further, 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: .

[0017] Further, Y r Solve by the following formula: ; in, Y st is the mass fraction of the fuel component when the reaction is complete.

[0018] On the other hand, the present invention provides a combustion flow field post-processing device based on multi-block structured grid parallel computing, comprising: 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; The numerical simulation module is used to perform parallel partition numerical simulation processing on the partitioned structural grid using a numerical simulation method 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 fraction of each component of 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.

[0019] Compared with the prior art, the technical effects that the present invention can produce are: 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 computing domain, and can be distributedly processed in each partition calculation, making full use of the advantages of large-scale parallelism, and can facilitate processing for more complex areas; at the same time, the processing method has a certain versatility. When the computing domain topology remains unchanged, even if the computing grid is adjusted, the post-processing method and the main direction discrete grid can remain unchanged. Therefore, the present invention has a wide range of applications.

[0020] The present invention synchronously calculates the physical quantities along the main direction when iteratively calculating the flow fields of each partition, so the present invention can be used to analyze the dynamic characteristics of the flow field, make real-time judgments on the calculation results, etc.

[0021] The present invention utilizes the partition characteristics of the computational domain itself to perform parallel processing, which greatly improves the computational efficiency and is suitable for situations where post-processing is frequent and real-time requirements are high. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0023] Figure 1 A schematic flow chart of a combustion flow field post-processing method based on multi-block structured grid parallel computing provided by an embodiment; Figure 2 A schematic diagram of the structure of a ramjet combustion chamber provided by an embodiment; Figure 3 A schematic diagram of a ramjet combustion chamber structure grid and partitions provided by an embodiment; Figure 4 A schematic diagram of main direction discrete points and their coordinates provided by an embodiment; Figure 5 A schematic diagram of the number of grid points in three directions and the structural grid numbering of a single partition provided by an embodiment; Figure 6 A main direction line segment interval of a single partition provided in an embodiment Schematic diagram; Figure 7 The main direction line segment intervals of the three partitions A, B, and C provided in an embodiment And the coordinates of discrete points Schematic diagram of calculation of physical quantity value at ; Figure 8 An interpolation interval provided for an embodiment And the corresponding grid points are represented i Schematic diagram; Fig. 9 A schematic diagram of the variation of mixing efficiency along the main direction provided by an embodiment.

[0024] Figure annotation: 1. Ramjet combustion chamber; 2. Ramjet combustion chamber inlet; 3. Fuel nozzle; 4. Concave cavity; 5. Lower wall; 6. Ramjet combustion chamber outlet; 7. Upper wall; 8. Side wall. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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 ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] Reference Figure 1 In one embodiment, a combustion flow field post-processing method based on multi-block structured grid parallel computing is provided, including: 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 density, velocity, pressure, temperature, and mass fraction of each component of 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.

[0027] Reference Figure 2In one embodiment, in step S1, the combustion chamber is a ramjet combustion chamber 1, including a nozzle 3 for injecting fuel, a cavity 4 for promoting mixing and improving flame stabilization capability, a combustion chamber inlet 2, a combustion chamber outlet 6, an upper wall 7, a lower wall 5 and a side wall 8.

[0028] Reference Figure 3 In one embodiment, in step S1, the grid pre-processing software Pointwise is used to perform spatial structural modeling on the ramjet engine combustion chamber to obtain the three-dimensional configuration of the combustion chamber, and then the three-dimensional configuration of the combustion chamber is meshed to obtain the structural grid of the three-dimensional configuration of the combustion chamber, and the structural grid is subjected to rectangular partition processing, and the structural 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 of each partition is within a set range, so that the calculation load of each partition is balanced. In this embodiment, the structural grid is divided into 30 partitions.

[0029] Reference Figure 4 , confirm the main direction of the structure grid after partitioning ( x ), perform equal-interval discretization along the main direction of the partitioned structure grid, and obtain the number of discrete points along the main direction ( is a positive integer, usually greater than 100 to ensure smooth post-processing results) and the coordinates of discrete points along the main direction ; In particular, the coordinates of discrete points can be consistent with the coordinates of grid points.

[0030] 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 one embodiment, The number of grid points in three directions of a single partition and the structural grid number are as follows: Figure 5 shown.

[0031] Reference Figure 6 , in each partition, the coordinates of the discrete points along the main direction , 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.

[0032] Reference Figure 7 , Figure 8 , the method of linear interpolation of adjacent grid points includes: like Figure 8 As shown, 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 .

[0033] like Figure 7 As shown, linear interpolation is performed on the A and B partitions to obtain the coordinates of discrete points. The combustion flow field parameter data of the discrete point coordinates in partition C is 0.

[0034] 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 in each partition, thereby estimating and filling the missing data points in the partition grid, making the data of each partition more complete and convenient for subsequent analysis and processing. Moreover, the method of linear interpolation of adjacent grid points can ensure the processing when the calculation grid is adjusted, thereby improving the scope of application of the present invention.

[0035] 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 structure grid, and calculate the coordinates of the discrete points in each partition The combustion flow field parameter data are accumulated and summed. ; .

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

[0037] 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. ; .

[0038] 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: .

[0039] Y r Solve by the following formula: ; in, Y st is the mass fraction of the fuel component when the reaction is complete; for the reaction of a certain fuel component, Y st is a constant.

[0040] The present invention synchronously calculates the physical quantities along the main direction when iteratively calculating the flow fields of each partition, so the present invention can be used to analyze the dynamic characteristics of the flow field and make real-time judgments on the calculation results.

[0041] Reference Fig. 9 , Fig. 9 A schematic diagram of the variation of mixing efficiency along the main direction provided by an embodiment.

[0042] In one embodiment, a combustion flow field post-processing device based on multi-block structured grid parallel computing is provided, comprising: 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; The numerical simulation module is used to perform parallel partition numerical simulation processing on the partitioned structural grid using a numerical simulation method 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 fraction of each component of 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.

[0043] Matters not covered by the present invention are known technologies.

[0044] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, 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, they should be considered to be within the scope of this specification.

[0045] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, 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 attached claims.

[0046] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. 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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