CN-115310221-B - Parameterization-based propeller single-channel structure division method and device

CN115310221BCN 115310221 BCN115310221 BCN 115310221BCN-115310221-B

Abstract

The application provides a parameterized propeller single-flow-channel structure dividing method and device, wherein the method comprises the steps of determining a space rectangular coordinate system of a propeller, and generating a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the space rectangular coordinate system of the propeller and geometric parameters of the propeller; then, the whole block corresponding to the three-dimensional geometric model of the propeller is established, the whole block is divided into at least two target areas, the at least two target areas are subjected to subdivision processing, and the processed at least two target areas are subjected to association processing. The grid division difficulty can be greatly reduced through a single-runner establishing mode and a grid arrangement strategy, and the grid quality and efficiency are improved so as to provide guarantee for subsequent calculation.

Inventors

HE WEI
LIU QIAN
HE PENGPENG
MA XIAOGANG
LI ZIRU

Assignees

武汉理工大学

Dates

Publication Date: 20260508
Application Date: 20220719

Claims (8)

1. The utility model provides a partitioning method of a single-channel structure of a propeller based on parameterization, which is characterized by comprising the following steps: Determining a space rectangular coordinate system of a propeller, and generating a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the space rectangular coordinate system of the propeller and geometric parameters of the propeller; Establishing an integral block corresponding to the three-dimensional geometric model of the propeller, and dividing the integral block into at least two target areas; Performing subdivision processing on the at least two target areas, and performing association processing on the at least two processed target areas; The dividing the integral block into at least two target areas includes: Dividing the integral block according to a preset first direction to obtain a propeller shaft target area of the propeller, a hub cap target area of the propeller and a propeller hub target area of the propeller, wherein the preset first direction is parallel to an X axis in a space rectangular coordinate system of the propeller, and a coordinate origin and the X axis in a cylindrical coordinate system of the propeller are consistent with the coordinate origin and the X axis in the space rectangular coordinate system of the propeller; the splitting processing of the at least two target areas comprises the following steps: Performing extension treatment on a hub cap target area of the propeller according to a preset second direction, wherein the preset second direction is the negative direction of the Y axis of a space rectangular coordinate system of the propeller; Performing Y-shaped subdivision treatment on the treated hub cap target area of the propeller; splitting the propeller hub target area of the propeller according to a preset third direction, wherein the preset third direction is a Z-axis direction parallel to a space rectangular coordinate system of the propeller; and performing O-shaped dissection treatment on the central block of the hub target area of the propeller after treatment.
2. The method of claim 1, wherein the determining a spatial rectangular coordinate system of the propeller comprises: Acquiring the geometric structure of a propeller, and taking the center of a propeller disc surface of the propeller as the origin of coordinates of a space rectangular coordinate system; determining at least two coordinate axes of a space rectangular coordinate system according to a propeller rotating shaft of the propeller; and determining the space rectangular coordinate system of the propeller according to the coordinate origin of the space rectangular coordinate system and at least two coordinate axes of the space rectangular coordinate system.
3. The method of claim 1, wherein the geometric parameters of the propeller include a blade profile pitch of the propeller and a radius parameter of the propeller; the generating a three-dimensional geometric model of the propeller corresponding to a single flow channel based on a space rectangular coordinate system of the propeller and geometric parameters of the propeller comprises the following steps: determining a two-dimensional curve expression of the propeller according to a space rectangular coordinate system of the propeller and a blade section pitch of the propeller; obtaining a cylindrical coordinate system of the propeller according to the spatial rectangular coordinate system of the propeller, and converting a two-dimensional curve expression of the propeller based on the cylindrical coordinate system of the propeller; And obtaining a three-dimensional geometric model of the propeller corresponding to a single flow channel according to the radius parameter of the propeller and the processed two-dimensional curve expression of the propeller.
4. The method of claim 1, further comprising, prior to said establishing a monolithic block corresponding to the three-dimensional geometric model of the propeller and dividing the monolithic block into at least two target areas: judging whether the three-dimensional geometric model of the propeller has defects or not; when detecting that the three-dimensional geometric model of the propeller has defects, repairing the three-dimensional geometric model of the propeller until the three-dimensional geometric model of the propeller has no defects; When detecting that the three-dimensional geometric model of the propeller has no defects, classifying the three-dimensional geometric model of the propeller; the building of the integral block corresponding to the three-dimensional geometric model of the propeller comprises the following steps: And establishing an integral block corresponding to the processed three-dimensional geometric model of the propeller.
5. The method according to claim 1, wherein after the splitting process is performed on the at least two target areas, before the correlating process is performed on the at least two target areas after the processing, further comprising: Extracting a part corresponding to a rotation domain in the integral block, and determining a blade tip end surface area from the processed integral block, wherein the rotation domain of the integral block is determined based on the three-dimensional geometric model of the propeller after classification processing; Performing an "O-shaped" splitting treatment on the blade tip end face region; the performing association processing on the at least two processed target areas includes: And carrying out association treatment on the treated at least two target areas and the treated blade tip end surface area.
6. A parameterized propeller single-flow-channel structure dividing device, comprising: The first processing module is used for determining a space rectangular coordinate system of the propeller and generating a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the space rectangular coordinate system of the propeller and geometric parameters of the propeller; the second processing module is used for establishing an integral block corresponding to the three-dimensional geometric model of the propeller and dividing the integral block into at least two target areas; The third processing module is used for carrying out subdivision processing on the at least two target areas and carrying out association processing on the at least two processed target areas; The dividing the integral block into at least two target areas includes: Dividing the integral block according to a preset first direction to obtain a propeller shaft target area of the propeller, a hub cap target area of the propeller and a propeller hub target area of the propeller, wherein the preset first direction is parallel to an X axis in a space rectangular coordinate system of the propeller, and a coordinate origin and the X axis in a cylindrical coordinate system of the propeller are consistent with the coordinate origin and the X axis in the space rectangular coordinate system of the propeller; the splitting processing of the at least two target areas comprises the following steps: Performing extension treatment on a hub cap target area of the propeller according to a preset second direction, wherein the preset second direction is the negative direction of the Y axis of a space rectangular coordinate system of the propeller; Performing Y-shaped subdivision treatment on the treated hub cap target area of the propeller; splitting the propeller hub target area of the propeller according to a preset third direction, wherein the preset third direction is a Z-axis direction parallel to a space rectangular coordinate system of the propeller; and performing O-shaped dissection treatment on the central block of the hub target area of the propeller after treatment.
7. The device for dividing the single-channel structure of the propeller based on parameterization is characterized by comprising a processor and a memory; the processor is connected with the memory; the memory is used for storing executable program codes; The processor runs a program corresponding to executable program code stored in the memory by reading the executable program code for performing the method according to any one of claims 1-5.
8. A computer readable storage medium, on which a computer program is stored, which computer program, when being executed by a processor, implements the method according to any of claims 1-5.

Description

Parameterization-based propeller single-channel structure division method and device Technical Field The application belongs to the technical field of computational fluid dynamics grid generation, and particularly relates to a method and a device for dividing a single-flow-channel structure of a propeller based on parameterization. Background In the design and calculation of the traditional marine metal material propeller, the blade is generally assumed to be rigid, the influence of hydrodynamic load on the structural characteristics of the blade is not considered, and the elastic deformation effect of the blade can have a certain influence on the operation of the propeller for the propeller with complex geometric shape and structure and the novel composite material propeller. Therefore, there is a higher requirement on the solution of the propeller flow field characteristics, whether to accurately predict the hydrodynamic characteristics and the load conditions of the propeller by adopting a proper method, and how to accurately predict the deep research of the hydrodynamic characteristics of the propeller on the propeller (such as the analysis of noise and vibration of the propeller and the design of a novel propeller) are all necessary preconditions for developing the deep research on the propeller. At present, the test is still one of the main ways for obtaining the hydrodynamic characteristics of the propeller, and in order to make up the defects of high test cost, long period, difficult observation of flow details in a flow field and the like, computational Fluid Dynamics (CFD) simulation research needs to be carried out, and grid division is a precondition for realizing the CFD research. However, the existing method for dividing the single-flow-channel structure of the propeller mainly uses manual experience, so that the dividing efficiency and accuracy cannot be ensured, and a large amount of labor cost is easily input. Disclosure of Invention The application provides a parameterized propeller single-channel structure dividing method and a parameterized propeller single-channel structure dividing device, which mainly take manual experience, can not ensure dividing efficiency and accuracy, and are easy to cause a great deal of labor cost investment, and the like, and the parameterized propeller single-channel structure dividing method and the parameterized propeller single-channel structure dividing device have the following specific scheme: In a first aspect, an embodiment of the present application provides a method for partitioning a single-channel structure of a propeller based on parameterization, including: determining a space rectangular coordinate system of the propeller, and generating a three-dimensional geometric model of the propeller corresponding to the single flow channel based on the space rectangular coordinate system of the propeller and geometric parameters of the propeller; establishing an integral block corresponding to the three-dimensional geometric model of the propeller, and dividing the integral block into at least two target areas; And carrying out subdivision processing on at least two target areas, and carrying out association processing on the processed at least two target areas. In an alternative of the first aspect, determining the spatial rectangular coordinate system of the propeller includes: Acquiring the geometric structure of the propeller, and taking the center of the propeller disc surface of the propeller as the origin of coordinates of a space rectangular coordinate system; determining at least two coordinate axes of a space rectangular coordinate system according to a propeller rotating shaft of the propeller; and determining the space rectangular coordinate system of the propeller according to the coordinate origin of the space rectangular coordinate system and at least two coordinate axes of the space rectangular coordinate system. In a further alternative of the first aspect, the geometrical parameters of the propeller include a blade profile pitch of the propeller and a radius parameter of the propeller; Generating a three-dimensional geometric model of the propeller corresponding to a single flow channel based on a space rectangular coordinate system of the propeller and geometric parameters of the propeller, comprising: determining a two-dimensional curve expression of the propeller according to the space rectangular coordinate system of the propeller and the section pitch of the propeller blade; Obtaining a cylindrical coordinate system of the propeller according to the spatial rectangular coordinate system of the propeller, and converting a two-dimensional curve expression of the propeller based on the cylindrical coordinate system of the propeller; And obtaining a three-dimensional geometric model of the propeller corresponding to the single flow channel according to the radius parameter of the propeller and the processed two-dimensional curve expres