CN110009746A - The hexahedral mesh automatic generation method with boundary layer of reactor fuel assemblies - Google Patents
The hexahedral mesh automatic generation method with boundary layer of reactor fuel assemblies Download PDFInfo
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Abstract
The invention discloses a kind of hexahedral mesh automatic generation method with boundary layer of reactor fuel assemblies, the thickness space of fuel rod surface body fitted anisotropic mesh is reserved in 1, geometry pretreatment；2, fluid mass is divided into the complex geometry region and simple geometry region for mixing the wing by the subregion of fluid mass；3, using tetrahedral grid division methods, the grid dividing with the complex geometry region for mixing the wing obtained in step 2 is completed；4, the tetrahedral grid generated in step 3 is converted into HEX8 hexahedral mesh；5, HEX20 hexahedral mesh is converted by the HEX8 hexahedral mesh generated in step 4；6, simple geometry area grid generates；7, the generation of the neighbouring body fitted anisotropic mesh of fuel rod surface；The present invention solves the Fluid Mechanics Computation software for calculation based on spectral element method and establishes difficulty to complex geometric models, can not generate the problems such as hexahedral mesh of the complex geometry with boundary layer.
Description
Technical field
The invention belongs to geometry hexahedral mesh generation method technical fields, and in particular to arrive a kind of reactor fuel assemblies
The hexahedral mesh automatic generation method with boundary layer.
Background technique
Currently, Fluid Mechanics Computation analysis is as a kind of important analysis method, in engineering calculation and field of scientific study
It occupies an important position.Fluid Mechanics Computation analysis tool type is more at present, and the numerical discretization schemes of use are also not quite similar.
Currently used calculation method is mostly the calculation method that geometry applicability is good and computational accuracy is low: more wide in terms of grid dividing
Hold, spatial spreading can be completed using tetrahedral grid, complete the simulation calculation for the fluid domain that complex geometry surrounds.But due to meter
The build-in attribute of calculation method makes computational accuracy low, cannot effectively identify Flow details, while being difficult to through secondary development
Mode promotes computational accuracy.Therefore completing high precision computation task has sizable difficulty.
Spectral element method is a kind of spatial spreading method.In discrete solution partial differential equation, this method uses high order polynomial
Formula can increase substantially computational solution precision as basic function.When use high-precision model carries out calculating fluid flowing and passes
When heat analysis, carries out solving the accuracy that can ensure result as far as possible using spectral element method, can accurately capture fluid
Flowing details, for design analysis reliable and effective data supporting is provided.Cfdrc based on spectral element method
As second generation flow dynamics analysis software, computational accuracy and convergence rate with higher can be in calculation method level solutions
The inaccurate problem of certainly current cfdrc analysis prediction result.
However, spectral element method popularization at present is more difficult, one of them contradiction more outstanding is that spectral element method can only
It supports to calculate using hexahedral mesh, and hexahedral mesh partition process is generally using manually completing at present, i.e., using geometry point
Block-geometry associativity-setting mesh parameter-generation grid process is realized.The process does not require nothing more than technical staff with quite high
Grid dividing experience, and heavy workload, grid formation efficiency are low, it is most important that can not use the party for labyrinth
Case is completed geometry and is divided.Because a kind of hexahedral mesh automatic generation method of the invention is to the more careless using having of spectral element method
Justice.
Summary of the invention
The object of the present invention is to provide a kind of hexahedral mesh with boundary layer of reactor fuel assemblies to automatically generate
Method, this method solve when carrying out reactor fuel assemblies thermal hydraulic analysis, since geometrical model excessively complexity causes
Can not using suitable method generate have boundary layer hexahedral mesh the problem of, for utilize the calculating based on spectral element method
Hydrodynamics software completes reactor fuel assemblies thermal hydraulic analysis and provides possibility.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of hexahedral mesh automatic generation method with boundary layer of reactor fuel assemblies, includes the following steps:
Step 1: geometry preprocessing process: according to actual reactor fuel assemblies structure, with 10.0 three-dimensional modeling of UG
Software carries out the three-dimensional modeling of fuel assembly, and modeling contents include the modeling for mixing the wing and the modeling of fuel rod: firstly, using real
The structure chart of border reactor fuel assemblies is completed to mix the two-dimentional sketch drafting of wing structure；And then utilize the drawing of 10.0 software of UG
It stretches function and obtains the three-dimensional of thickness and mix wing model, and wing model bending will be mixed using well known bending function, complete to stir
The foundation of mixed wing model；Then, three-dimensional fuel rod model is established by the method for stretching；Establishing three-dimensional fuel stick model
When, reserve the thickness space of fuel rod surface body fitted anisotropic mesh；It is established followed by the boolean logic function of 10.0 software of UG anti-
Answer the fluid mass outside heap fuel assembly；
Step 2: reactor fuel assemblies calculating fluid mass the subregion process of fluid mass: being divided into simple geometry region
With with the complex geometry region of the wing is mixed, specifically, wing upstream 1cm is being mixed and downstream 1cm establishes normal and fuel respectively
The consistent plane of mandrel line will calculate fluid mass and be divided into three parts, be conducive to subsequent difference using above-mentioned two plane as interface
Processing；
Step 3: the tetrahedral grid partition process with the complex geometry region for mixing the wing: soft using ANSYS-ICEM
Part completes the grid dividing in complex geometry region obtained in step 2 using the automatic partition functionality of tetrahedral grid well known to it
Task: the macro-size of setting tetrahedral grid is only needed, and complete using the well known automatic computing function of ANSYS-ICEM software
At the tetrahedral grid partition process with the complex geometry region for mixing the wing；
Step 4: tetrahedral grid is converted to the process of HEX8 hexahedral mesh: in ANSYS-ICEM software, utilizing it
Well known tetrahedral grid is converted into the function of HEX8 hexahedral mesh, will be obtained with the complexity for mixing the wing in step 3
All tetrahedral grids in geometric areas are divided, and each tetrahedral grid splits into four HEX8 hexahedral mesh,
With obtaining HEX8 hexahedral mesh division result in the complex geometry region for mixing the wing；
Step 5:HEX8 hexahedral mesh is converted to the process of HEX20 hexahedral mesh: in ANSYS-ICEM software, benefit
Increase the function at Grid Edge midpoint, the middle click-through on all HEX8 hexahedral mesh sides obtained to step 4 well known to it
Line flag is completed to be converted to HEX20 hexahedral mesh with the HEX8 hexahedral mesh in the complex geometry region for mixing the wing
Conversion process.At this point, being four sides with the surface grids on the complex geometry region and simple geometry area limit face of mixing the wing
Shape grid；
Step 6: simple geometry area grid generating process: in ANSYS-ICEM software, using its grid stretch function,
To the surface grids being had in step 5 on the complex geometry region and simple geometry area limit face for mixing the wing in simple geometry region
Inside stretched, obtain the HEX20 hexahedral mesh in simple geometry region；
Step 7: the generating process of body fitted anisotropic mesh near fuel rod surface: the specific method is as follows:
Step 7-1: in ANSYS-ICEM software, by complex geometry region and simple geometry region internal combustion charge bar surface
Surface grids merge, and above-mentioned surface grids are placed in same section；
Step 7-2: using the grid stretch function of ANSYS-ICEM software, by the surface grids of fuel rod surface along fuel rod
Surface inter normal direction is stretched, and hexahedral mesh is obtained, and the hexahedral mesh of generation needs the position that will be reserved in step 1
It is full of, serves as fuel rod surface body fitted anisotropic mesh nearby.
Compared to the prior art compared with the present invention has following advantage:
1, this grid generation method is realized by UG10.0 3 d modeling software and ANSYS ICEM grid dividing software
Complex geometry hexahedral mesh generating process, the popularization for the cfdrc based on spectral element method are provided convenience；
2, this grid generation method uses supermatic grid generation method, generates compared to traditional artificial grid
The operating procedure and workload of technical staff can be greatly lowered in method, improve working efficiency.
Detailed description of the invention
Fig. 1 is the method for the present invention flow chart.
Fig. 2 is 5 × 5 cluster three-dimensional geometrical structure model schematic of advanced pressurized water reactor fuel assembly.
Fig. 3 is flow field regions schematic diagram.
Fig. 4 is simple geometry region and the subregion schematic diagram with the complex geometry region for mixing the wing.
Fig. 5 is with the tetrahedral grid schematic diagram in the complex geometry region for mixing the wing.
Fig. 6 is to divide schematic diagram with the HEX20 hexahedral mesh in the complex geometry region for mixing the wing.
Fig. 7 is simple geometry region and the HEX20 hexahedral mesh schematic diagram with the complex geometry region for mixing the wing.
Fig. 8 is fuel rod surface body fitted anisotropic mesh schematic diagram nearby.
Specific embodiment
The present invention is made into one by taking 5 × 5 cluster of advanced pressurized water reactor fuel assembly as an example below in conjunction with flow chart shown in Fig. 1
The detailed description of step:
Step 1: the three-dimensional geometry of 5 × 5 cluster of advanced pressurized water reactor fuel assembly is established with 10.0 3 d modeling software of UG
Model.Modeling contents include the modeling for mixing the wing and the modeling of fuel rod: firstly, utilizing 5 × 5 stick of advanced pressurized water reactor fuel assembly
The structure chart of beam is completed to mix the two-dimentional sketch drafting of wing structure；And then thickness has been obtained using the stretch function of 10.0 software of UG
The three-dimensional of degree mixes wing model, and will mix wing model bending using bending function, completes the foundation for mixing wing model；Then,
Three-dimensional fuel rod model is established by the method for stretching.When establishing geometrical model note that needing to increase fuel rod diameter, increase
Boundary layer thickness at the i.e. reserved fuel rod surface of amount, the generation for body fitted anisotropic mesh in step 7.The advanced pressure water established
The 3-D geometric model of 5 × 5 cluster of heap fuel assembly is as shown in Figure 2.It is built followed by the boolean logic function of 10.0 software of UG
Fluid mass outside vertical 5 × 5 cluster of advanced pressurized water reactor fuel assembly, obtained fluid mass are as shown in Figure 3.
Step 2: the subregion process of fluid mass: 5 × 5 cluster of advanced pressurized water reactor fuel assembly calculating fluid mass being divided into
Simple geometry region and with the complex geometry region for mixing the wing.Specifically, wing upstream 1cm is being mixed and downstream 1cm is built respectively
Fluid mass is divided into three parts, is conducive to by legislation line and the consistent plane of fuel rod axis using above-mentioned two plane as interface
Subsequent to handle respectively, the division result of this example is as shown in Figure 4.
Step 3: the tetrahedral grid partition process with the complex geometry region for mixing the wing: soft using ANSYS-ICEM
Part completes the grid dividing task in complex geometry region obtained in step 2 using the automatic partition functionality of its tetrahedral grid: only
The macro-size of tetrahedral grid need to be set, and completes to have using the automatic computing function of ANSYS-ICEM software and mixes the wing
The tetrahedral grid partition process in complex geometry region, the tetrahedral grid divided automatically are as shown in Figure 5.
Step 4: tetrahedral grid is converted to the process of HEX8 hexahedral mesh: in ANSYS-ICEM software, utilizing it
Tetrahedral grid is converted into the function of HEX8 hexahedral mesh, will be obtained with the complex geometry area for mixing the wing in step 3
All tetrahedral grids in domain are divided, and each tetrahedral grid splits into four HEX8 hexahedral mesh, are stirred having
HEX8 hexahedral mesh division result is obtained in the complex geometry region of the mixed wing, the grid ultimately generated is as shown in Figure 6.
Step 5:HEX8 hexahedral mesh is converted to the process of HEX20 hexahedral mesh: in ANSYS-ICEM software, benefit
Increasing the function at Grid Edge midpoint with it, the midpoint on all HEX8 hexahedral mesh sides obtained to step 4 is marked,
It completes to be converted to the converted of HEX20 hexahedral mesh with the HEX8 hexahedral mesh in the complex geometry region for mixing the wing
Journey；At this point, being quadrilateral mesh with the surface grids on the complex geometry region and simple geometry area limit face of mixing the wing.
Step 6: simple geometry area grid generating process: in ANSYS-ICEM software, using its grid stretch function,
To the surface grids being had in step 5 on the complex geometry region and simple geometry area limit face for mixing the wing in simple geometry region
It is inside stretched, obtains the HEX20 hexahedral mesh in simple geometry region, final grid result is as shown in Figure 7；
Step 7: the generating process of body fitted anisotropic mesh near fuel rod surface: the specific method is as follows:
Step 7-1: in ANSYS-ICEM software, by complex geometry region and simple geometry region internal combustion charge bar surface
Surface grids merge, and above-mentioned surface grids are placed in same section；
Step 7-2: using the grid stretch function of ANSYS-ICEM software, by the surface grids of fuel rod surface along fuel rod
Surface inter normal direction is stretched, and hexahedral mesh is obtained, and the hexahedral mesh of generation needs the position that will be reserved in step 1
It is full of, serves as fuel rod surface body fitted anisotropic mesh nearby.Final body fitted anisotropic mesh is cyclic annular grid in Fig. 8.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (1)
1. a kind of hexahedral mesh automatic generation method with boundary layer of reactor fuel assemblies, which is characterized in that including
Following steps:
Step 1: geometry preprocessing process: according to actual reactor fuel assemblies structure, with UG10.0 3 d modeling software
The three-dimensional modeling of fuel assembly is carried out, modeling contents include the modeling for mixing the wing and the modeling of fuel rod: firstly, using practical anti-
The structure chart of heap fuel assembly is answered to complete to mix the two-dimentional sketch drafting of wing structure；And then utilize the stretch function of UG10.0 software
The three-dimensional for obtaining thickness mixes wing model, and will mix wing model bending using bending function, and building for wing model is mixed in completion
It is vertical；Then, three-dimensional fuel rod model is established by the method for stretching；When establishing three-dimensional fuel stick model, fuel rod is reserved
The thickness space of surface boundary layer grid；It is established outside reactor fuel assemblies followed by the boolean logic function of UG10.0 software
Fluid mass；
Step 2: reactor fuel assemblies calculating fluid mass the subregion process of fluid mass: being divided into simple geometry region and band
There is the complex geometry region for mixing the wing, specifically, is mixing wing upstream 1cm and downstream 1cm establishes normal and fuel mandrel respectively
Fluid mass is divided into three parts using above-mentioned two plane as interface by the consistent plane of line, is handled respectively conducive to subsequent；
Step 3: the tetrahedral grid partition process with the complex geometry region for mixing the wing: utilizing ANSYS-ICEM software, make
The grid dividing task in complex geometry region obtained in step 2 is completed with the automatic partition functionality of its tetrahedral grid: only needing to set
Determine the macro-size of tetrahedral grid, and is completed using the automatic computing function of ANSYS-ICEM software with the complexity for mixing the wing
The tetrahedral grid partition process of geometric areas；
Step 4: tetrahedral grid is converted to the process of HEX8 hexahedral mesh: in ANSYS-ICEM software, utilizing its four sides
Volume mesh is converted into the function of HEX8 hexahedral mesh, will be obtained in the complex geometry region for mixing the wing in step 3
All tetrahedral grids divided, each tetrahedral grid splits into four HEX8 hexahedral mesh, with mixing the wing
Complex geometry region in obtain HEX8 hexahedral mesh division result；
Step 5:HEX8 hexahedral mesh is converted to the process of HEX20 hexahedral mesh: in ANSYS-ICEM software, utilizing it
Increase the function at Grid Edge midpoint, the midpoint on all HEX8 hexahedral mesh sides obtained to step 4 is marked, and completes
The conversion process of HEX20 hexahedral mesh is converted to the HEX8 hexahedral mesh in the complex geometry region for mixing the wing；This
When, it is quadrilateral mesh with the surface grids on the complex geometry region and simple geometry area limit face of mixing the wing；
Step 6: simple geometry area grid generating process: in ANSYS-ICEM software, using its grid stretch function, to step
In rapid 5 with mix the wing complex geometry region and simple geometry area limit face on surface grids in simple geometry region into
Row stretches, and obtains the HEX20 hexahedral mesh in simple geometry region；
Step 7: the generating process of body fitted anisotropic mesh near fuel rod surface: the specific method is as follows:
Step 7-1: in ANSYS-ICEM software, by the veil in complex geometry region and simple geometry region internal combustion charge bar surface
Lattice merge, and above-mentioned surface grids are placed in same section；
Step 7-2: using the grid stretch function of ANSYS-ICEM software, by the surface grids of fuel rod surface along fuel rod surface
Inter normal direction is stretched, and hexahedral mesh is obtained, and the hexahedral mesh of generation needs to fill the position reserved in step 1
It is full, serve as fuel rod surface body fitted anisotropic mesh nearby.
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