CN110009746B - Automatic hexahedron grid generation method with boundary layer for reactor fuel assembly - Google Patents
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Abstract
The invention discloses a hexahedron grid automatic generation method with a boundary layer of a reactor fuel assembly, which comprises the following steps of 1, carrying out geometric pretreatment, and reserving thickness space of a grid of the boundary layer on the surface of a fuel rod; 2. the fluid area is divided into a complex geometric area and a simple geometric area with mixing wings; 3. finishing the meshing of the complex geometric area with the mixing wings obtained in the step 2 by utilizing a tetrahedral meshing method; 4. converting the tetrahedral mesh generated in the step 3 into a HEX8 hexahedral mesh; 5. converting the HEX8 hexahedral mesh generated in the step 4 into a HEX20 hexahedral mesh; 6. generating a simple geometric area grid; 7. generating boundary layer grids near the surface of the fuel rod; the invention solves the problems that computational fluid dynamics calculation software based on a spectral element method is difficult to establish a complex geometric model, a hexahedral mesh with complex geometry of a boundary layer cannot be generated, and the like.
Description
Technical Field
The invention belongs to the technical field of geometric hexahedral mesh generation methods, and particularly relates to an automatic hexahedral mesh generation method with a boundary layer for a reactor fuel assembly.
Background
At present, computational fluid dynamics analysis plays an important role in the fields of engineering calculation and scientific research as an important analysis method. At present, the computational fluid dynamics analysis tools are more in types, and the adopted numerical value discrete methods are different. Most of the conventional calculation methods have good geometric applicability and low calculation accuracy: the method is relatively tolerant in the aspect of grid division, and can utilize a tetrahedral grid to complete space dispersion and complete simulation calculation of a fluid domain surrounded by complex geometry. However, due to the inherent properties of the calculation method, the calculation accuracy is low, the flow field details cannot be effectively identified, and meanwhile, the calculation accuracy is difficult to improve in a secondary development mode. It is therefore quite difficult to perform high-precision computing tasks.
The spectral element method is a spatially discrete method. When the partial differential equation is discretely solved, the method adopts a high-order polynomial as a basis function, so that the accuracy of a calculation result can be greatly improved. When the high-precision model is used for calculating the fluid flow and heat transfer analysis, the accuracy of the result can be guaranteed as much as possible by using the spectral element method for solving, the flow details of the fluid can be accurately captured, and reliable and effective data support is provided for design analysis. The computational fluid dynamics software based on the spectral element method is used as second-generation fluid dynamics analysis software, has higher computational accuracy and convergence rate, and can solve the problem that the analytical prediction result of the current computational fluid dynamics software is inaccurate at the computational method level.
However, the conventional spectral element method is difficult to popularize, one of the outstanding contradictions is that the spectral element method can only adopt hexahedral mesh to support calculation, and the conventional hexahedral mesh division process is generally completed manually, namely, the conventional hexahedral mesh division process is realized by adopting a flow of geometric partitioning, geometric association, mesh parameter setting and mesh generation. The process not only requires a technician to have quite high grid division experience, but also has large workload and low grid generation efficiency, and most importantly, the scheme cannot be adopted to complete geometric division on a complex structure. Therefore, the automatic hexahedron mesh generation method has great significance for the application of the spectral element method.
Disclosure of Invention
The invention aims to provide an automatic generating method of hexahedral meshes with boundary layers of a reactor fuel assembly, which solves the problem that the hexahedral meshes with the boundary layers cannot be generated by adopting a proper method due to too complicated geometric models when the thermal hydraulic analysis of the reactor fuel assembly is carried out, and provides possibility for utilizing computational fluid mechanics software based on a spectral element method to complete the thermal hydraulic analysis of the reactor fuel assembly.
In order to achieve the purpose, the invention adopts the following technical scheme:
an automatic generating method of hexahedral mesh with boundary layers of a reactor fuel assembly, comprising the steps of:
step 1: geometric pretreatment process: according to the actual structure of the reactor fuel assembly, UG10.0 three-dimensional modeling software is used for three-dimensional modeling of the fuel assembly, and modeling contents comprise modeling of mixing wings and modeling of fuel rods: firstly, completing two-dimensional sketch drawing of a mixing wing structure by using a structure diagram of an actual reactor fuel assembly; then obtaining a three-dimensional mixing wing model with thickness by utilizing the stretching function of UG10.0 software, and bending the mixing wing model by utilizing the known bending function to complete the establishment of the mixing wing model; then, establishing a three-dimensional fuel rod model by a stretching method; reserving a thickness space of a boundary layer grid on the surface of the fuel rod when a three-dimensional fuel rod model is established; then establishing a fluid region outside the reactor fuel assembly by utilizing the Boolean logic function of UG10.0 software;
step 2: partitioning process of fluid region: dividing a reactor fuel assembly calculation fluid area into a simple geometric area and a complex geometric area with mixing wings, specifically, respectively establishing planes with the normal lines consistent with the axes of the fuel rods at the upstream 1cm and the downstream 1cm of the mixing wings, and dividing the calculation fluid area into three parts by taking the two planes as interfaces, so as to be beneficial to subsequent respective processing;
and step 3: tetrahedral meshing process of complex geometric areas with blending wings: and (3) utilizing ANSYS-ICEM software to complete the meshing task of the complex geometric area obtained in the step (2) by using the known tetrahedral mesh automatic meshing function: only setting the macroscopic size of the tetrahedral mesh, and completing the tetrahedral mesh division process of the complex geometric area with the mixing wings by utilizing the known automatic calculation function of ANSYS-ICEM software;
and 4, step 4: process of transformation of tetrahedral mesh into HEX8 hexahedral mesh: in ANSYS-ICEM software, utilizing the function of converting the known tetrahedral mesh into HEX8 hexahedral mesh, splitting all the tetrahedral meshes in the complex geometric area with the mixing wings obtained in the step 3, wherein each tetrahedral mesh is split into four HEX8 hexahedral meshes, and obtaining HEX8 hexahedral mesh division results in the complex geometric area with the mixing wings;
and 5: process of HEX8 hexahedral mesh to HEX20 hexahedral mesh: and (4) marking the midpoints on the edges of all the HEX8 hexahedron grids obtained in the step (4) by utilizing the known function of increasing the midpoints of the edges of the grids in ANSYS-ICEM software, and completing the conversion process of converting the HEX8 hexahedron grids into the HEX20 hexahedron grids in the complex geometric area with the blending wings. At the moment, the surface grids on the interface of the complex geometric area with the mixing wings and the simple geometric area are all quadrilateral grids;
step 6: simple geometric area mesh generation process: stretching the surface grid on the interface of the complex geometric area with the mixing wings and the simple geometric area in the step 5 in the simple geometric area by utilizing the grid stretching function in ANSYS-ICEM software to obtain a HEX20 hexahedral grid in the simple geometric area;
and 7: generation process of boundary layer grid near fuel rod surface: the specific method comprises the following steps:
step 7-1: in ANSYS-ICEM software, combining a surface grid on the surface of the fuel rod in a complex geometric area and a surface grid on the surface of the fuel rod in a simple geometric area, and placing the surface grids in the same part;
step 7-2: and (3) stretching the surface grids on the surface of the fuel rod along the direction of the normal line in the surface of the fuel rod by utilizing the grid stretching function of ANSYS-ICEM software to obtain hexahedron grids, wherein the generated hexahedron grids need to fill the reserved positions in the step (1) and serve as boundary layer grids near the surface of the fuel rod.
Compared with the prior art, the invention has the following advantages:
1. the grid generation method realizes the complex geometric hexahedron grid generation process by means of UG10.0 three-dimensional modeling software and ANSYS ICEM grid division software, and provides convenience for popularization of computational fluid mechanics software based on a spectral element method;
2. the grid generation method adopts a highly automated grid generation method, and compared with the traditional manual grid generation method, the grid generation method can greatly reduce the operation steps and workload of technicians and improve the working efficiency.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
Fig. 2 is a schematic diagram of a three-dimensional geometric model of a bundle of advanced pressurized water reactor fuel assemblies 5 × 5.
Fig. 3 is a schematic view of the flow field area.
FIG. 4 is a sectional view of a simple geometric region and a complex geometric region with mixing wings.
FIG. 5 is a schematic representation of tetrahedral mesh in a complex geometry area with kneading wings.
Fig. 6 is a schematic diagram of HEX20 hexahedral meshing in a complex geometric area with blending wings.
Fig. 7 is a schematic view of a HEX20 hexahedral mesh of simple geometric regions and complex geometric regions with blending wings.
FIG. 8 is a schematic view of boundary layer grids near the surface of a fuel rod.
Detailed Description
The present invention will be described in further detail below with reference to the flow chart of FIG. 1, taking an example of an advanced pressurized water reactor fuel assembly 5 × 5 bar bundle:
the method comprises the following steps of 1, establishing a three-dimensional geometric model of an advanced pressurized water reactor fuel assembly 5 × 5 bundle by using UG10.0 three-dimensional modeling software, wherein modeling content comprises two-dimensional sketch drawing of a mixing wing structure by using a structure diagram of the advanced pressurized water reactor fuel assembly 5 × 5 bundle, obtaining a three-dimensional mixing wing model with thickness by using a stretching function of the UG10.0 software, bending the mixing wing model by using a bending function, completing establishment of the mixing wing model, then establishing a three-dimensional fuel rod model by using a stretching method, paying attention to increase the diameter of a fuel rod when establishing the geometric model, increasing the thickness of a boundary layer at the reserved surface of the fuel rod, generating a grid in a step 7, establishing the three-dimensional geometric model of the advanced pressurized water reactor fuel assembly 5 × 5 bundle as shown in a figure 2, and then establishing a fluid region outside the pressurized water reactor fuel assembly 5 × 5 by using a Boolean logic function of the UG10.0 software, wherein the obtained fluid region is as shown in a figure 3.
And 2, a fluid region partitioning process, namely dividing the calculated fluid region of the rod bundle of the advanced pressurized water reactor fuel assembly 5 × 5 into a simple geometric region and a complex geometric region with a mixing wing, specifically, respectively establishing a plane with the normal line consistent with the axis of the fuel rod at the upstream 1cm and the downstream 1cm of the mixing wing, and taking the two planes as interfaces to divide the fluid region into three parts for facilitating subsequent respective processing, wherein the partitioning result of the embodiment is shown in fig. 4.
And step 3: tetrahedral meshing process of complex geometric areas with blending wings: and (3) utilizing ANSYS-ICEM software to complete the grid division task of the complex geometric area obtained in the step (2) by using the automatic tetrahedron grid division function: only the macro size of the tetrahedral mesh needs to be set, and the automatic calculation function of ANSYS-ICEM software is utilized to complete the tetrahedral mesh division process of the complex geometric area with the mixing wings, and the automatically divided tetrahedral mesh is shown in FIG. 5.
And 4, step 4: process of transformation of tetrahedral mesh into HEX8 hexahedral mesh: in the ANSYS-ICEM software, by using the function of converting the tetrahedral mesh into the HEX8 hexahedral mesh, all the tetrahedral meshes in the complex geometric area with the blending wings obtained in step 3 are split, each tetrahedral mesh is split into four HEX8 hexahedral meshes, the HEX8 hexahedral mesh division result is obtained in the complex geometric area with the blending wings, and the final generated mesh is shown in fig. 6.
And 5: process of HEX8 hexahedral mesh to HEX20 hexahedral mesh: in ANSYS-ICEM software, marking the midpoints on the edges of all the HEX8 hexahedron grids obtained in the step 4 by utilizing the function of increasing the midpoints of the edges of the grids, and completing the conversion process of converting the HEX8 hexahedron grids in the complex geometric area with the mixing wings into the HEX20 hexahedron grids; at the moment, the surface grids on the interface of the complex geometric area with the mixing wings and the simple geometric area are all quadrilateral grids.
Step 6: simple geometric area mesh generation process: in ANSYS-ICEM software, by utilizing the mesh stretching function, stretching the surface mesh on the interface of the complex geometric area with the mixing wings and the simple geometric area in the step 5 in the simple geometric area to obtain a HEX20 hexahedral mesh in the simple geometric area, wherein the final mesh result is shown in FIG. 7;
and 7: generation process of boundary layer grid near fuel rod surface: the specific method comprises the following steps:
step 7-1: in ANSYS-ICEM software, combining a surface grid on the surface of the fuel rod in a complex geometric area and a surface grid on the surface of the fuel rod in a simple geometric area, and placing the surface grids in the same part;
step 7-2: and (3) stretching the surface grids on the surface of the fuel rod along the direction of the normal line in the surface of the fuel rod by utilizing the grid stretching function of ANSYS-ICEM software to obtain hexahedron grids, wherein the generated hexahedron grids need to fill the reserved positions in the step (1) and serve as boundary layer grids near the surface of the fuel rod. The final boundary layer mesh is the annular mesh in fig. 8.
The invention is not described in detail and is within the knowledge of a person skilled in the art.
Claims (1)
1. An automatic generating method of hexahedral mesh with boundary layers of a reactor fuel assembly, characterized by comprising the following steps:
step 1: geometric pretreatment process: according to the actual structure of the reactor fuel assembly, UG10.0 three-dimensional modeling software is used for three-dimensional modeling of the fuel assembly, and modeling contents comprise modeling of mixing wings and modeling of fuel rods: firstly, completing two-dimensional sketch drawing of a mixing wing structure by using a structure diagram of an actual reactor fuel assembly; then obtaining a three-dimensional mixing wing model with thickness by utilizing the stretching function of UG10.0 software, and bending the mixing wing model by utilizing the bending function to complete the establishment of the mixing wing model; then, establishing a three-dimensional fuel rod model by a stretching method; reserving a thickness space of a boundary layer grid on the surface of the fuel rod when a three-dimensional fuel rod model is established; then establishing a fluid region outside the reactor fuel assembly by utilizing the Boolean logic function of UG10.0 software;
step 2: partitioning process of fluid region: dividing a reactor fuel assembly calculation fluid area into a simple geometric area and a complex geometric area with a mixing wing, specifically, respectively establishing planes 1cm upstream and 1cm downstream of the mixing wing, wherein the normal line of the established planes needs to be parallel to the axis of the fuel rod, and dividing the fluid area into three parts by taking the two planes as an interface, so as to be beneficial to subsequent respective processing;
and step 3: tetrahedral meshing process of complex geometric areas with blending wings: and (3) utilizing ANSYS-ICEM software to complete the grid division task of the complex geometric area obtained in the step (2) by using the automatic tetrahedron grid division function: only setting the macro size of the tetrahedral mesh, and completing the tetrahedral mesh division process of the complex geometric area with the mixing wings by utilizing the automatic calculation function of ANSYS-ICEM software;
and 4, step 4: process of transformation of tetrahedral mesh into HEX8 hexahedral mesh: in ANSYS-ICEM software, splitting all tetrahedral meshes in the complex geometric area with the mixing wings obtained in the step 3 by using the function of converting the tetrahedral meshes into HEX8 hexahedral meshes, wherein each tetrahedral mesh is split into four HEX8 hexahedral meshes, and obtaining HEX8 hexahedral mesh division results in the complex geometric area with the mixing wings;
and 5: process of HEX8 hexahedral mesh to HEX20 hexahedral mesh: in ANSYS-ICEM software, marking the midpoints on the edges of all the HEX8 hexahedron grids obtained in the step 4 by utilizing the function of increasing the midpoints of the edges of the grids, and completing the conversion process of converting the HEX8 hexahedron grids in the complex geometric area with the mixing wings into the HEX20 hexahedron grids; at the moment, the surface grids on the interface of the complex geometric area with the mixing wings and the simple geometric area are all quadrilateral grids;
step 6: simple geometric area mesh generation process: in ANSYS-ICEM software, stretching the surface grid on the interface of the complex geometric area with the mixing wings and the simple geometric area in the step 5 in the simple geometric area by utilizing the grid stretching function to obtain an HEX20 hexahedral grid in the simple geometric area;
and 7: generation process of boundary layer grid near fuel rod surface: the specific method comprises the following steps:
step 7-1: in ANSYS-ICEM software, combining a surface grid on the surface of the fuel rod in a complex geometric area and a surface grid on the surface of the fuel rod in a simple geometric area, and placing the surface grids in the same part;
step 7-2: and (3) stretching the surface grids on the surface of the fuel rod along the direction of the normal line in the surface of the fuel rod by utilizing the grid stretching function of ANSYS-ICEM software to obtain hexahedron grids, wherein the generated hexahedron grids need to fill the reserved positions in the step (1) and serve as boundary layer grids near the surface of the fuel rod.
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