A parameter-based method and device for dividing a single channel structure of a propeller

Abstract

The application provides a parameter-based propeller single-flow channel structure division method and device. The method comprises the following steps: determining a space rectangular coordinate system of a propeller, and generating a three-dimensional geometric model corresponding to a single-flow channel of the propeller based on the space rectangular coordinate system of the propeller and geometric parameters of the propeller; then establishing an integral block corresponding to the three-dimensional geometric model of the propeller, and dividing the integral block into at least two target regions; then performing division processing on the at least two target regions, and performing correlation processing on the at least two target regions after processing. The single-flow channel establishment mode and the grid arrangement strategy can greatly reduce the grid division difficulty, improve the grid quality and efficiency, and provide guarantee for subsequent calculation.

Description

Technical Field

[0001] This application belongs to the field of computational fluid dynamics mesh generation technology, and specifically relates to a method and apparatus for parameterized propeller single-channel structure partitioning. Background Technology

[0002] In the design and calculation of traditional marine metal propellers, the blades are generally assumed to be rigid, without considering the influence of hydrodynamic loads on the blade structural characteristics. However, for propellers with complex geometries and structures, as well as new composite material propellers, the elastic deformation effect of the blades can have a certain impact on propeller operation. Therefore, there are higher requirements for solving the propeller flow field characteristics. The ability to accurately predict the hydrodynamic characteristics and load conditions of propellers using appropriate methods, and how to accurately predict the hydrodynamic characteristics of propellers for in-depth research (such as the analysis of propeller noise and vibration, and the design of new propellers), are all necessary prerequisites for conducting in-depth research on propellers.

[0003] Currently, experimentation remains one of the main methods for obtaining propeller hydrodynamic characteristics. However, to compensate for the shortcomings of experimentation, such as high cost, long cycle, and difficulty in observing the internal flow details, computational fluid dynamics (CFD) simulation research is needed. Mesh generation is a prerequisite for CFD research. However, existing methods for mesh generation of propeller single-channel structures are mostly based on manual experience, which not only fails to guarantee the efficiency and accuracy of mesh generation but also easily leads to a large investment of labor costs. Summary of the Invention

[0004] This application addresses the aforementioned technical problems of existing methods for dividing single-channel propeller structures, which rely heavily on manual experience, failing to guarantee efficiency and accuracy and incurring significant labor costs. It proposes a parameterized method and apparatus for dividing single-channel propeller structures, the specific scheme of which is as follows:

[0005] In a first aspect, embodiments of this application provide a parameterized propeller single-channel structure partitioning method, including:

[0006] Determine the spatial rectangular coordinate system of the propeller, and generate a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the spatial rectangular coordinate system and the geometric parameters of the propeller.

[0007] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, and divide the monolithic block into at least two target regions;

[0008] At least two target regions are segmented, and the processed at least two target regions are associated.

[0009] In one alternative to the first aspect, determining the propeller's spatial rectangular coordinate system includes:

[0010] Obtain the geometry of the propeller and use the center of the propeller disk as the origin of the spatial rectangular coordinate system;

[0011] Determine at least two coordinate axes of the spatial rectangular coordinate system based on the propeller's rotation axis;

[0012] The spatial rectangular coordinate system of the propeller is determined based on the origin of the spatial rectangular coordinate system and at least two coordinate axes of the spatial rectangular coordinate system.

[0013] In another alternative to the first aspect, the propeller's geometric parameters include the propeller blade profile pitch and the propeller's radius parameter.

[0014] Based on the propeller's spatial Cartesian coordinate system and geometric parameters, a three-dimensional geometric model of the propeller corresponding to a single flow channel is generated, including:

[0015] Based on the propeller's spatial rectangular coordinate system and the propeller blade profile pitch, the two-dimensional curve expression of the propeller is determined.

[0016] The cylindrical coordinate system of the propeller is obtained from the spatial rectangular coordinate system of the propeller, and the two-dimensional curve expression of the propeller is transformed based on the cylindrical coordinate system of the propeller.

[0017] Based on the propeller's radius parameters and the processed two-dimensional curve expression of the propeller, a three-dimensional geometric model of the propeller corresponding to a single flow channel is obtained.

[0018] In another alternative to the first aspect, before establishing the monolithic block corresponding to the three-dimensional geometric model of the propeller and dividing the monolithic block into at least two target regions, the method further includes:

[0019] Determine if there are any defects in the three-dimensional geometric model of the propeller;

[0020] When a defect is detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is repaired until the three-dimensional geometric model of the propeller is free of defects.

[0021] When no defects are detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is classified.

[0022] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, including:

[0023] Create a monolithic block corresponding to the three-dimensional geometric model of the processed propeller.

[0024] In another alternative to the first aspect, the entire block is divided into at least two target regions, including:

[0025] The entire block is divided according to the preset first direction to obtain the target area of ​​the propeller shaft, the target area of ​​the propeller hub cap, and the target area of ​​the propeller hub.

[0026] In another alternative to the first aspect, at least two target regions are partitioned, including:

[0027] The target area of ​​the propeller hub cap is extended according to the preset second direction;

[0028] The target area of ​​the hub cap of the processed propeller is subjected to "Y-shaped" segmentation.

[0029] The target area of ​​the propeller hub is segmented according to a preset third direction;

[0030] The center block of the target area of ​​the rotor hub of the processed propeller is subjected to "O-type" segmentation.

[0031] In another alternative to the first aspect, after segmenting at least two target regions and before associating the processed at least two target regions, the method further includes:

[0032] The part corresponding to the rotation domain in the whole block is extracted and processed, and the blade tip end face region is determined from the processed whole block; wherein, the rotation domain of the whole block is determined based on the three-dimensional geometric model of the propeller after classification.

[0033] The leaf tip area is divided into "O-shaped" sections.

[0034] The processed at least two target regions are associated, including:

[0035] The at least two target regions after processing, as well as the processed leaf tip end face region, are subjected to correlation processing.

[0036] Secondly, embodiments of this application provide a parameterized propeller single-channel structure partitioning device, comprising:

[0037] The first processing module is used to determine the spatial rectangular coordinate system of the propeller and generate a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the spatial rectangular coordinate system of the propeller and the geometric parameters of the propeller.

[0038] The second processing module is used to create an integral block corresponding to the three-dimensional geometric model of the propeller, and to divide the integral block into at least two target regions;

[0039] The third processing module is used to perform segmentation processing on at least two target regions and to perform association processing on the processed at least two target regions.

[0040] In one alternative embodiment of the second aspect, the first processing module includes:

[0041] The first determining unit is used to obtain the geometric structure of the propeller and take the center of the propeller disk as the origin of the spatial rectangular coordinate system.

[0042] The second determining unit is used to determine at least two coordinate axes of the spatial rectangular coordinate system based on the propeller's rotation axis.

[0043] The third determining unit is used to determine the spatial rectangular coordinate system of the propeller based on the origin of the spatial rectangular coordinate system and at least two coordinate axes of the spatial rectangular coordinate system.

[0044] In another alternative of the second aspect, the propeller's geometric parameters include the propeller blade profile pitch and the propeller's radius parameters.

[0045] The first processing module also includes:

[0046] The fourth determining unit is used to determine the two-dimensional curve expression of the propeller based on the propeller's spatial rectangular coordinate system and the propeller blade profile pitch.

[0047] The transformation unit is used to obtain the cylindrical coordinate system of the propeller from the spatial rectangular coordinate system of the propeller, and to perform transformation processing on the two-dimensional curve expression of the propeller based on the cylindrical coordinate system of the propeller.

[0048] The fifth determining unit is used to obtain the three-dimensional geometric model of the propeller corresponding to a single flow channel based on the radius parameters of the propeller and the processed two-dimensional curve expression of the propeller.

[0049] In another alternative embodiment of the second aspect, the second processing module further includes:

[0050] The judgment unit is used to determine whether there are defects in the three-dimensional geometric model of the propeller before establishing the integral block corresponding to the three-dimensional geometric model of the propeller and dividing the integral block into at least two target regions.

[0051] The first detection unit is used to repair the three-dimensional geometric model of the propeller when a defect is detected in the three-dimensional geometric model of the propeller, until the three-dimensional geometric model of the propeller is free of defects.

[0052] The second detection unit is used to classify the three-dimensional geometric model of the propeller when it is detected that there are no defects in the three-dimensional geometric model of the propeller.

[0053] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, including:

[0054] Create a monolithic block corresponding to the three-dimensional geometric model of the processed propeller.

[0055] In another alternative embodiment of the second aspect, the second processing module further includes:

[0056] The entire block is divided according to the preset first direction to obtain the target area of ​​the propeller shaft, the target area of ​​the propeller hub cap, and the target area of ​​the propeller hub.

[0057] In another alternative embodiment of the second aspect, the third processing unit includes:

[0058] The first processing unit is used to extend the target area of ​​the propeller hub cap according to a preset second direction;

[0059] The second processing unit is used to perform "Y-shaped" segmentation on the target area of ​​the hub cap of the processed propeller.

[0060] The third processing unit is used to perform segmentation processing on the target area of ​​the propeller hub according to a preset third direction;

[0061] The fourth processing unit is used to perform "O-type" segmentation on the center block of the target area of ​​the rotor hub after processing.

[0062] In another alternative to the second aspect, the third processing module further includes:

[0063] The sixth determining unit is used to extract the part corresponding to the rotation domain in the whole block after the at least two target regions are segmented and before the at least two target regions are associated, and to determine the blade tip surface region from the processed whole block; wherein, the rotation domain of the whole block is determined based on the three-dimensional geometric model of the propeller after classification.

[0064] The fifth processing unit is used to perform "O-type" segmentation on the tip surface area of ​​the leaf;

[0065] The processed at least two target regions are associated, including:

[0066] The at least two target regions after processing, as well as the processed leaf tip end face region, are subjected to correlation processing.

[0067] Thirdly, embodiments of this application provide yet another parameterized propeller single-channel structure partitioning device, including a processor and a memory;

[0068] The processor is connected to the memory;

[0069] Memory, used to store executable program code;

[0070] The processor runs a program corresponding to the executable program code by reading the executable program code stored in the memory, so as to implement the parameterized propeller single-channel structure partitioning method provided by the first aspect or any implementation of the first aspect of the embodiments of this application.

[0071] Fourthly, embodiments of this application provide a computer storage medium storing a computer program, which includes program instructions. When executed by a processor, the program instructions can implement the parameterized propeller single-channel structure partitioning method provided by the first aspect or any implementation of the first aspect of this application.

[0072] In this embodiment, when performing structured mesh generation for a single-channel propeller, the propeller's spatial Cartesian coordinate system is first determined, and a three-dimensional geometric model of the propeller corresponding to the single-channel is generated based on the propeller's spatial Cartesian coordinate system and geometric parameters. Next, a monolithic block corresponding to the propeller's three-dimensional geometric model is established, and this block is divided into at least two target regions. Then, the at least two target regions are subdivided, and the processed at least two target regions are associated. This single-channel establishment method and mesh layout strategy significantly reduce the difficulty of mesh generation, improve mesh quality and efficiency, and provide a guarantee for subsequent calculations. Attached Figure Description

[0073] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0074] Figure 1 A flowchart illustrating a parameterized propeller single-channel structure partitioning method provided in this application embodiment;

[0075] Figure 2 A schematic diagram illustrating the effect of a spatial rectangular coordinate system for a propeller provided in an embodiment of this application;

[0076] Figure 3 A schematic diagram illustrating the effect of a cylindrical coordinate system for a propeller provided in an embodiment of this application;

[0077] Figure 4 A schematic diagram of curve parameter relationships provided in an embodiment of this application;

[0078] Figure 5This is a schematic diagram illustrating the overall block division effect of a propeller provided in an embodiment of this application;

[0079] Figure 6 This is a schematic diagram illustrating the processing effect of the target area of ​​the hub cap of a propeller, provided in an embodiment of this application.

[0080] Figure 7 A schematic diagram illustrating the processing effect of the target area of ​​the propeller hub provided in an embodiment of this application;

[0081] Figure 8 A schematic diagram of a parameterized propeller single-channel structure partitioning device provided in this application embodiment;

[0082] Figure 9 This is a schematic diagram of another parameterized propeller single-channel structure partitioning device provided in the embodiments of this application. Detailed Implementation

[0083] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings.

[0084] In the following description, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The following description provides multiple embodiments of this application, which can be substituted or combined with each other. Therefore, this application can also be considered to include all possible combinations of the same and / or different embodiments described. Thus, if one embodiment includes features A, B, and C, and another embodiment includes features B and D, then this application should also be considered to include embodiments containing one or more other possible combinations of A, B, C, and D, even if such embodiments are not explicitly described in the following text.

[0085] The following description provides examples and does not limit the scope, applicability, or examples set forth in the claims. Changes may be made to the function and arrangement of the described elements without departing from the scope of this application. Various processes or components may be appropriately omitted, substituted, or added to the examples. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. Furthermore, features described with respect to some examples may be combined into other examples.

[0086] Please see Figure 1 , Figure 1 The diagram shows a flowchart of a parameterized propeller single-channel structure partitioning method provided in an embodiment of this application.

[0087] like Figure 1As shown, this parameterized propeller single-channel structure partitioning method may include at least the following steps:

[0088] Step 102: Determine the spatial rectangular coordinate system of the propeller, and generate a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the spatial rectangular coordinate system of the propeller and the geometric parameters of the propeller.

[0089] Specifically, when performing structured mesh generation for a single-channel propeller, the geometry of the propeller to be processed can be determined first, and a spatial Cartesian coordinate system corresponding to the propeller can be obtained based on the propeller's geometry. The origin of the spatial Cartesian coordinate system corresponding to the propeller can be, but is not limited to, any location within the propeller's geometry. Furthermore, after determining any one coordinate axis in the spatial Cartesian coordinate system, the properties of the coordinate axes (e.g., the perpendicularity theorem and the right-hand rule) can be used to determine the other two coordinate axes.

[0090] For better understanding, as an optional embodiment of this application, determining the spatial rectangular coordinate system of the propeller includes:

[0091] Obtain the geometry of the propeller and use the center of the propeller disk as the origin of the spatial rectangular coordinate system;

[0092] Determine at least two coordinate axes of the spatial rectangular coordinate system based on the propeller's rotation axis;

[0093] The spatial rectangular coordinate system of the propeller is determined based on the origin of the spatial rectangular coordinate system and at least two coordinate axes of the spatial rectangular coordinate system.

[0094] Specifically, in determining the spatial rectangular coordinate system of the propeller, the propeller's geometry can be obtained first. This geometry can be used to characterize the spatial structure of the propeller to be processed. In this embodiment, the propeller's geometry can be obtained by scanning with geometric modeling software, but is not limited to this method. Next, mathematical analysis can be performed on the obtained propeller geometry to determine geometric parameters such as the center position, shaft center position, or blade radius. The center of the propeller disk can be used as the origin of the spatial rectangular coordinate system, but is not limited to this method.

[0095] Furthermore, after determining the origin of the spatial rectangular coordinate system, the axis of rotation of the propeller, located at the center of the propeller disk, can be used as the X-axis of this spatial rectangular coordinate system, but is not limited to it. In other words, the X-axis of this spatial rectangular coordinate system can coincide with the axis of rotation of the propeller, located at the center of the propeller disk, and the downward direction of the axis of rotation of the propeller, located at the center of the propeller disk, can be set as the positive direction of the X-axis in this spatial rectangular coordinate system. Then, based on the X-axis of the spatial rectangular coordinate system, the axis perpendicular to the axis of rotation of the propeller, located at the center of the propeller disk, can be used as the Y-axis in this spatial rectangular coordinate system. The Y-axis of this spatial rectangular coordinate system can, but is not limited to, pass through the center of the propeller blades, and the positive direction of the Y-axis points towards the propeller blades.

[0096] Furthermore, after obtaining the X-axis and Y-axis in the spatial rectangular coordinate system, the Z-axis can be determined using, but is not limited to, the right-hand rule. Based on the determined origin, X-axis, Y-axis, and Z-axis, the spatial rectangular coordinate system can then be established. (See here for more information.) Figure 2 The diagram shown illustrates the effect of a spatial rectangular coordinate system for a propeller according to an embodiment of this application. This application can be, but is not limited to, providing... Figure 2 The positional relationships between the X-axis, Y-axis, and Z-axis in the spatial rectangular coordinate system shown are not elaborated here.

[0097] It is understood that, after obtaining the spatial rectangular coordinate system of the propeller, the embodiments of this application can also obtain a corresponding cylindrical coordinate system based on the spatial rectangular coordinate system of the propeller. The origin and X-axis of the cylindrical coordinate system of the propeller may, but are not limited to, be consistent with the origin and X-axis of the spatial rectangular coordinate system of the propeller. The radius r of the cylindrical coordinate system of the propeller is a radial coordinate with outwards being positive. The included angle of the cylindrical coordinate system of the propeller... Take the positive direction about the X-axis in the cylindrical coordinate system, according to the right-hand rule. (See here for more information.) Figure 3 The diagram shown illustrates the effect of a cylindrical coordinate system for a propeller according to an embodiment of this application. This application can be, but is not limited to, providing... Figure 3 The positional relationships between the X-axis, Y-axis, and Z-axis in the spatial rectangular coordinate system shown are not elaborated here.

[0098] Furthermore, after obtaining the propeller's spatial rectangular coordinate system, a three-dimensional geometric model of the propeller corresponding to a single flow channel can be generated based on this spatial rectangular coordinate system and the propeller's geometric parameters. The propeller's geometric parameters can be, but are not limited to, those obtained from the aforementioned propeller geometry, and may include parameters such as the propeller blade pitch, radius parameters, and the number of blades. It is understood that the three-dimensional geometric model of the propeller corresponding to a single flow channel can be a single-flow channel three-dimensional geometric model, whose model structure is consistent with the propeller structure. To facilitate subsequent calculations, this embodiment of the application can export this three-dimensional geometric model in a format recognizable by ANSYS ICEM software. Here, ANSYS ICEM software can, but is not limited to, perform meshing processing on the imported single-flow channel three-dimensional geometric model to generate a more accurate structured mesh for the propeller.

[0099] As another optional embodiment of this application, the geometric parameters of the propeller include the blade profile pitch and the radius parameter of the propeller.

[0100] Based on the propeller's spatial Cartesian coordinate system and geometric parameters, a three-dimensional geometric model of the propeller corresponding to a single flow channel is generated, including:

[0101] Based on the propeller's spatial rectangular coordinate system and the propeller blade profile pitch, the two-dimensional curve expression of the propeller is determined.

[0102] The cylindrical coordinate system of the propeller is obtained from the spatial rectangular coordinate system of the propeller, and the two-dimensional curve expression of the propeller is transformed based on the cylindrical coordinate system of the propeller.

[0103] Based on the propeller's radius parameters and the processed two-dimensional curve expression of the propeller, a three-dimensional geometric model of the propeller corresponding to a single flow channel is obtained.

[0104] Specifically, in the process of generating the three-dimensional geometric model of the propeller corresponding to a single flow channel, the following two-dimensional curve expression of the propeller can be obtained by first assuming that the propeller blades have no longitudinal tilt or skew, based on the propeller's spatial rectangular coordinate system and the propeller blade profile pitch:

[0105]

[0106] In the above formula, , This can be expressed as the pitch angle of the propeller blade profile, and its specific expression can be: P can be represented as the pitch; H and h can be represented as parameters controlling the axial length of a single flow channel.

[0107] It is understood that, in the embodiments of this application, it is possible, but not limited to, taking 10 points from each of the three small intervals [-hH, h+H] and substituting them into the above formula to obtain the x and y coordinates of 30 points.

[0108] Furthermore, based on the aforementioned two-dimensional curve expression of the propeller, and considering the changes in longitudinal and skew profiles of each blade, the two-dimensional curve expression of the propeller is shifted, resulting in the shifted expression shown below:

[0109]

[0110] In the above formula, It can be expressed as the total pitch, and r can be expressed as the corresponding radius. It can be represented as a lateral angle.

[0111] It is understood that, in the embodiments of this application, the x and y coordinates of the 30 points mentioned above can be substituted into the above-mentioned moving expression to obtain the point coordinates of the two-dimensional curve of the plane below a certain radius of the periodic boundary when the blade has pitch and skew. See also the following: Figure 4 The schematic diagram of a curve parameter relationship provided by the embodiment of this application is illustrated here. Based on relevant knowledge of fluid dynamics and conventional technical means in this field, it will not be elaborated further here.

[0112] Furthermore, the cylindrical coordinate system of the propeller can be obtained from the propeller's spatial rectangular coordinate system (the origin and X-axis of this cylindrical coordinate system can, but are not limited to, being consistent with the origin and X-axis of the propeller's spatial rectangular coordinate system), and the aforementioned translation expression can be transformed into the global coordinate expression shown below:

[0113]

[0114] It is understood that, in the embodiments of this application, all the point coordinates mentioned above can be substituted into the aforementioned global coordinate expression, and different points can be repeatedly substituted into the aforementioned expression to obtain the three-dimensional curves of the single-channel periodic boundary under different radii. Then, all the point coordinates corresponding to the global coordinate expression can be arranged in the positive X-axis direction, and a single-channel periodic boundary surface can be generated based on 3D modeling software. The required rotation angle for replication is obtained according to the number of blades, and then used to divide the rotation domain into single channels. The application of 3D modeling software can be, but is not limited to, conventional techniques in the art, and will not be elaborated upon here.

[0115] Step 104: Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, and divide the monolithic block into at least two target regions.

[0116] Specifically, after obtaining the three-dimensional geometric model of the propeller corresponding to a single flow channel, it is possible, but not limited to, to create an integral block corresponding to the three-dimensional geometric model of the propeller based on ANSYS ICEM software. The creation method can be to first import the three-dimensional geometric model of the propeller corresponding to a single flow channel into ANSYS ICEM software, and then, through a set automated program, parse the imported three-dimensional geometric model of the propeller corresponding to a single flow channel and create the corresponding integral block to facilitate subsequent structured partitioning.

[0117] As another optional embodiment of this application, before establishing the integral block corresponding to the three-dimensional geometric model of the propeller and dividing the integral block into at least two target regions, the method further includes:

[0118] Determine if there are any defects in the three-dimensional geometric model of the propeller;

[0119] When a defect is detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is repaired until the three-dimensional geometric model of the propeller is free of defects.

[0120] When no defects are detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is classified.

[0121] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, including:

[0122] Create a monolithic block corresponding to the three-dimensional geometric model of the processed propeller.

[0123] Specifically, after importing the 3D geometric model of the propeller corresponding to a single flow channel into the ANSYS ICEM software, a preset automated program can be used to check the 3D geometric model to determine if there are any defects. It is understood that these defects can be, but are not limited to, incomplete or damaged structures in the 3D geometric model. When defects are detected in the propeller's 3D geometric model, the ANSYS ICEM software can automatically repair the 3D geometric model based on its geometric structure until no defects are detected in the propeller's 3D geometric model.

[0124] When the 3D geometric model of the propeller is found to be free of defects, existing points and lines in the model can be automatically deleted using ANSYS ICEM software, but this is not limited to the method described above. A new topological geometry can then be created by setting geometric tolerances. Next, ANSYS ICEM software can be used to check if the curves in the topological geometry are red. When a red curve is detected, it indicates that the topological geometry has been initially created. The 3D geometric model of the propeller can then be classified, but this is not limited to the method described above, to meet subsequent calculation requirements.

[0125] When the curve in the topological geometry is not red, it indicates that the three-dimensional geometric model of the propeller still has defects. It is necessary to use ANSYS ICEM software to automatically repair the three-dimensional geometric model according to its geometric structure until the three-dimensional geometric model of the propeller is found to be free of any defects.

[0126] It should be noted that when classifying the 3D geometric model of the propeller using ANSYS ICEM software, it is possible, but not limited to, naming and classifying boundary conditions such as the interface of the rotating domain, the back of the blade, and the front of the blade. This classification method is not only beneficial for mesh generation, but also facilitates subsequent fusion with the static domain mesh and automatic identification in the solution settings.

[0127] Furthermore, after classifying the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the classified propeller can be modeled based on the preset automatic program of ANSYS ICEM software to obtain the integral block corresponding to the single flow channel.

[0128] Furthermore, after obtaining the integral block corresponding to the propeller, the integral block can be divided according to a preset first direction to obtain the target area of ​​the propeller shaft, the target area of ​​the propeller hub, and the target area of ​​the propeller hub. The method of dividing the integral block can be, but is not limited to, using the preset automatic program of the aforementioned ANSYSICEM software, selecting the portion of the integral block parallel to the X-axis in the spatial rectangular coordinate system to divide it once before and once after the propeller, thus dividing the integral block into a cuboid region before the propeller (i.e., the target area corresponding to the propeller shaft), a cuboid region near the propeller blades (i.e., the target area corresponding to the propeller hub), and a cuboid region after the propeller (i.e., the target area corresponding to the propeller hub). For a better understanding, please refer to [link to relevant documentation]. Figure 5 The diagram shown illustrates the overall block division effect of a propeller according to an embodiment of this application.

[0129] Of course, the embodiments of this application may not be limited to the above-described method of dividing the whole block, nor may they be limited to replacing the ANSYS ICEM software mentioned above with other types of software.

[0130] Step 106: Divide at least two target regions and perform association processing on the at least two processed target regions.

[0131] Specifically, after dividing the overall block into at least two target regions, each of the at least two regions can be subdivided separately to make the mesh generation rate of each processed region faster and more efficient.

[0132] As another optional embodiment of this application, the process of segmenting at least two target regions includes:

[0133] The target area of ​​the propeller hub cap is extended according to the preset second direction;

[0134] The target area of ​​the hub cap of the processed propeller is subjected to "Y-shaped" segmentation.

[0135] The target area of ​​the propeller hub is segmented according to a preset third direction;

[0136] The center block of the target area of ​​the rotor hub of the processed propeller is subjected to "O-type" segmentation.

[0137] Specifically, this example uses at least the target regions of the propeller shaft, the propeller hub, and the propeller hub as described above. For details on the segmentation of the propeller hub target region, please refer to [link / reference needed]. Figure 6 The diagram illustrates the processing effect of a target area of ​​a propeller hub cap according to an embodiment of this application. Figure 6 As shown, it is possible, but not limited to, first stretching the bottom surface of the propeller hub cap target area along the negative Y-axis of the spatial rectangular coordinate system. Then, all blocks in the stretched propeller hub cap target area are sectioned along the X-axis parallel to the spatial rectangular coordinate system (see the left side of Figure 6A). Next, all blocks can be merged by referring to multiple nodes (see 1 and 2, 3 and 4 in the right side of Figure 6A). The resulting triangular prism region is then subjected to "Y-blocking" in the NSYS ICEM software using the "Blocking→Edit Block→Convert BlockType" operation. In the "Set Type" column, "Y-Block" is selected to perform "Y-type subdivision" to obtain the blocks corresponding to the processed propeller hub cap target area (see Figure 6B).

[0138] Understandably, after performing a "Y-shaped" partitioning of the target region of the propeller hub, it is possible, but not limited to, further partitioning the resulting block along both sides of the X-axis parallel to the spatial rectangular coordinate system. This is to avoid additional interfaces within the rotating domain generated by the single-channel rotation affecting computational accuracy and efficiency. Here, the above operation adds a buffer region between the blade surface mesh and the periodic boundary, ensuring that while meeting the requirement of the blade mesh being perpendicular to the blade surface, the angle between the mesh near the periodic boundary and the boundary remains within an acceptable range, thereby reducing the difficulty of improving mesh quality.

[0139] When performing segmentation on the target area of ​​the propeller hub cap, please refer to the following: Figure 7The diagram illustrates the processing effect of a propeller hub target area according to an embodiment of this application. Figure 7 As shown, the target area of ​​the propeller hub can be divided twice along the Z-axis direction parallel to the spatial rectangular coordinate system, so that the blade is located in the block in the middle (see 7A). Then, the "Blocking→SplitBlock→Ogrid Block" operation is performed using ANSYS ICEM software, and the above blocks are selected based on "Select Block(s)" to obtain the block corresponding to the target area of ​​the propeller hub after processing (see 7B).

[0140] As another optional embodiment of this application, after segmenting at least two target regions and before performing association processing on the processed at least two target regions, the method further includes:

[0141] The part corresponding to the rotation domain in the whole block is extracted and processed, and the blade tip end face region is determined from the processed whole block; wherein, the rotation domain of the whole block is determined based on the three-dimensional geometric model of the propeller after classification.

[0142] The leaf tip area is divided into "O-shaped" sections.

[0143] The processed at least two target regions are associated, including:

[0144] The at least two target regions after processing, as well as the processed leaf tip end face region, are subjected to correlation processing.

[0145] Specifically, for the blade portion with end faces at the blade tip, the aforementioned triangular prism region can be removed, but is not limited to this step. The block can be radially divided into two regions: from the blade tip to the blade root and from the blade tip to the top of the single flow channel. This operation effectively controls the mesh size at the blade tip. The radial meshing strategy for the blade tip to blade root region is the same; please refer to the relevant steps mentioned above, which will not be elaborated upon here.

[0146] Because the blade curvature changes significantly at 0.5r and near the blade tip, additional meshing is required to ensure the surface mesh fits the blade geometry. Therefore, for the region from the blade tip to the top of the single flow channel, it is possible, but not limited to, first deleting blocks inside the blade that do not belong to the rotation domain, and then performing an "internal O-type mesh" on the special structure of the blade tip end face. Using the aforementioned ANSYS ICEM software as an example, the execution steps are as follows:

[0147] (1) Click the “Split Block” button, then click the “Ogrid Block” button;

[0148] (2) In the “Select Block(s)” option, select the block between the blade tip and the top of the single flow channel;

[0149] (3) In the “Select Face(s)” option, select the “Face” corresponding to the blade tip end face and the top of the single flow channel, and click “Apply”.

[0150] Furthermore, after subdividing each of the at least two target regions, a mapping relationship can be established for each of the processed target regions, and the structured mesh of the propeller single channel can be obtained by adjusting the nodes in association.

[0151] Please see Figure 8 , Figure 8 This paper presents a schematic diagram of a parameterized propeller single-channel structure partitioning device according to an embodiment of this application.

[0152] like Figure 8 As shown, the parameterized propeller single-channel structure partitioning device may include at least a first processing module 801, a second processing module 802, and a third processing module 803, wherein:

[0153] The first processing module 801 is used to determine the spatial rectangular coordinate system of the propeller and generate a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the spatial rectangular coordinate system of the propeller and the geometric parameters of the propeller.

[0154] The second processing module 802 is used to create an integral block corresponding to the three-dimensional geometric model of the propeller, and to divide the integral block into at least two target regions;

[0155] The third processing module 803 is used to perform segmentation processing on at least two target regions and to perform association processing on the processed at least two target regions.

[0156] In some possible embodiments, the first processing module includes:

[0157] The first determining unit is used to obtain the geometric structure of the propeller and take the center of the propeller disk as the origin of the spatial rectangular coordinate system.

[0158] The second determining unit is used to determine at least two coordinate axes of the spatial rectangular coordinate system based on the propeller's rotation axis.

[0159] The third determining unit is used to determine the spatial rectangular coordinate system of the propeller based on the origin of the spatial rectangular coordinate system and at least two coordinate axes of the spatial rectangular coordinate system.

[0160] In some possible embodiments, the propeller's geometric parameters include the propeller blade profile pitch and the propeller's radius parameters.

[0161] The first processing module also includes:

[0162] The fourth determining unit is used to determine the two-dimensional curve expression of the propeller based on the propeller's spatial rectangular coordinate system and the propeller blade profile pitch.

[0163] The transformation unit is used to obtain the cylindrical coordinate system of the propeller from the spatial rectangular coordinate system of the propeller, and to perform transformation processing on the two-dimensional curve expression of the propeller based on the cylindrical coordinate system of the propeller.

[0164] The fifth determining unit is used to obtain the three-dimensional geometric model of the propeller corresponding to a single flow channel based on the radius parameters of the propeller and the processed two-dimensional curve expression of the propeller.

[0165] In some possible embodiments, the second processing module further includes:

[0166] The judgment unit is used to determine whether there are defects in the three-dimensional geometric model of the propeller before establishing the integral block corresponding to the three-dimensional geometric model of the propeller and dividing the integral block into at least two target regions.

[0167] The first detection unit is used to repair the three-dimensional geometric model of the propeller when a defect is detected in the three-dimensional geometric model of the propeller, until the three-dimensional geometric model of the propeller is free of defects.

[0168] The second detection unit is used to classify the three-dimensional geometric model of the propeller when it is detected that there are no defects in the three-dimensional geometric model of the propeller.

[0169] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, including:

[0170] Create a monolithic block corresponding to the three-dimensional geometric model of the processed propeller.

[0171] In some possible embodiments, the second processing module further includes:

[0172] The entire block is divided according to the preset first direction to obtain the propeller shaft target area, the propeller hub cap target area, and the propeller hub target area.

[0173] In some possible embodiments, the third processing unit includes:

[0174] The first processing unit is used to extend the target area of ​​the propeller hub cap according to a preset second direction;

[0175] The second processing unit is used to perform "Y-shaped" segmentation on the target area of ​​the hub cap of the processed propeller.

[0176] The third processing unit is used to perform segmentation processing on the target area of ​​the propeller hub according to a preset third direction;

[0177] The fourth processing unit is used to perform "O-type" segmentation on the center block of the target area of ​​the rotor hub after processing.

[0178] In some possible embodiments, the third processing module further includes:

[0179] The sixth determining unit is used to extract the part corresponding to the rotation domain in the whole block after the at least two target regions are segmented and before the at least two target regions are associated, and to determine the blade tip surface region from the processed whole block; wherein, the rotation domain of the whole block is determined based on the three-dimensional geometric model of the propeller after classification.

[0180] The fifth processing unit is used to perform "O-type" segmentation on the tip surface area of ​​the leaf;

[0181] The processed at least two target regions are associated, including:

[0182] The at least two target regions after processing, as well as the processed leaf tip end face region, are subjected to correlation processing.

[0183] Those skilled in the art will clearly understand that the technical solutions of the embodiments of this application can be implemented by means of software and / or hardware. In this specification, "unit" and "module" refer to software and / or hardware that can independently complete or cooperate with other components to complete a specific function, wherein the hardware may be, for example, a field-programmable gate array (FPGA), an integrated circuit (IC), etc.

[0184] Please see Figure 9 , Figure 9 This paper presents a schematic diagram of another parameterized propeller single-channel structure partitioning device provided in an embodiment of this application.

[0185] like Figure 9 As shown, the parameterized propeller single-channel structure partitioning device 900 may include: at least one processor 901, at least one network interface 904, user interface 903, memory 905, and at least one communication bus 902.

[0186] The communication bus 902 can be used to realize the connection and communication of the above components.

[0187] The user interface 903 may include buttons, and the optional user interface may also include a standard wired interface or a wireless interface.

[0188] The network interface 904 may include, but is not limited to, Bluetooth modules, NFC modules, Wi-Fi modules, etc.

[0189] The processor 901 may include one or more processing cores. The processor 901 connects to various parts within the electronic device 900 using various interfaces and lines. It executes instructions, programs, code sets, or instruction sets stored in the memory 905, and calls data stored in the memory 905 to perform various functions and process data within the routing device 900. Optionally, the processor 901 may be implemented using at least one hardware form of DSP, FPGA, or PLA. The processor 901 may integrate one or more of the following: CPU, GPU, and modem. The CPU primarily handles the operating system, user interface, and applications; the GPU is responsible for rendering and drawing the content required for display; and the modem handles wireless communication. It is understood that the modem may also not be integrated into the processor 901 and may be implemented as a separate chip.

[0190] The memory 905 may include RAM or ROM. Optionally, the memory 905 may include a non-transitory computer-readable medium. The memory 905 may be used to store instructions, programs, code, code sets, or instruction sets. The memory 905 may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing an operating system, instructions for at least one function (such as touch function, sound playback function, image playback function, etc.), instructions for implementing the above-described method embodiments, etc.; the data storage area may store data involved in the above-described method embodiments, etc. Optionally, the memory 905 may also be at least one storage device located remotely from the aforementioned processor 901. Figure 5 As shown, the memory 905, which serves as a computer storage medium, may include an operating system, a network communication module, a user interface module, and an application program based on parameterized propeller single-channel structure partitioning.

[0191] Specifically, the processor 901 can be used to call the parameterized propeller single-channel structure partitioning application stored in the memory 905, and specifically perform the following operations:

[0192] Determine the spatial rectangular coordinate system of the propeller, and generate a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the spatial rectangular coordinate system and the geometric parameters of the propeller.

[0193] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, and divide the monolithic block into at least two target regions;

[0194] At least two target regions are segmented, and the processed at least two target regions are associated.

[0195] In some possible embodiments, determining the propeller's spatial Cartesian coordinate system includes:

[0196] Obtain the geometry of the propeller and use the center of the propeller disk as the origin of the spatial rectangular coordinate system;

[0197] Determine at least two coordinate axes of the spatial rectangular coordinate system based on the propeller's rotation axis;

[0198] The spatial rectangular coordinate system of the propeller is determined based on the origin of the spatial rectangular coordinate system and at least two coordinate axes of the spatial rectangular coordinate system.

[0199] In some possible embodiments, the propeller's geometric parameters include the propeller blade profile pitch and the propeller's radius parameters.

[0200] Based on the propeller's spatial Cartesian coordinate system and geometric parameters, a three-dimensional geometric model of the propeller corresponding to a single flow channel is generated, including:

[0201] Based on the propeller's spatial rectangular coordinate system and the propeller blade profile pitch, the two-dimensional curve expression of the propeller is determined.

[0202] The cylindrical coordinate system of the propeller is obtained from the spatial rectangular coordinate system of the propeller, and the two-dimensional curve expression of the propeller is transformed based on the cylindrical coordinate system of the propeller.

[0203] Based on the propeller's radius parameters and the processed two-dimensional curve expression of the propeller, a three-dimensional geometric model of the propeller corresponding to a single flow channel is obtained.

[0204] In some possible embodiments, before creating a monolithic block corresponding to the three-dimensional geometric model of the propeller and dividing the monolithic block into at least two target regions, the method further includes:

[0205] Determine if there are any defects in the three-dimensional geometric model of the propeller;

[0206] When a defect is detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is repaired until the three-dimensional geometric model of the propeller is free of defects.

[0207] When no defects are detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is classified.

[0208] Create a monolithic block corresponding to the three-dimensional geometric model of the propeller, including:

[0209] Create a monolithic block corresponding to the three-dimensional geometric model of the processed propeller.

[0210] In some possible embodiments, the entire block is divided into at least two target regions, including:

[0211] The entire block is divided according to the preset first direction to obtain the propeller shaft target area, the propeller hub cap target area, and the propeller hub target area.

[0212] In some possible embodiments, the process of segmenting at least two target regions includes:

[0213] The target area of ​​the propeller hub cap is extended according to the preset second direction;

[0214] The target area of ​​the hub cap of the processed propeller is subjected to "Y-shaped" segmentation.

[0215] The target area of ​​the propeller hub is segmented according to a preset third direction;

[0216] The center block of the target area of ​​the rotor hub of the processed propeller is subjected to "O-type" segmentation.

[0217] In some possible embodiments, after segmenting at least two target regions and before associating the processed at least two target regions, the method further includes:

[0218] The part corresponding to the rotation domain in the whole block is extracted and processed, and the blade tip end face region is determined from the processed whole block; wherein, the rotation domain of the whole block is determined based on the three-dimensional geometric model of the propeller after classification.

[0219] The leaf tip area is divided into "O-shaped" sections.

[0220] The processed at least two target regions are associated, including:

[0221] The at least two target regions after processing, as well as the processed leaf tip end face region, are subjected to correlation processing.

[0222] This application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the above-described method. The computer-readable storage medium may include, but is not limited to, any type of disk, including floppy disks, optical disks, DVDs, CD-ROMs, microdrives, as well as magneto-optical disks, ROMs, RAMs, EPROMs, EEPROMs, DRAMs, VRAMs, flash memory devices, magnetic cards or optical cards, nanosystems (including molecular memory ICs), or any type of medium or device suitable for storing instructions and / or data.

[0223] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0224] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0225] In the several embodiments provided in this application, it should be understood that the disclosed apparatus can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some service interface; the indirect coupling or communication connection between apparatuses or units may be electrical or other forms.

[0226] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0227] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0228] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage device (CMD). Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a memory and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of this application. The aforementioned memory includes various media capable of storing program code, such as a USB flash drive, read-only memory (ROM), random access memory (RAM), portable hard drive, magnetic disk, or optical disk.

[0229] Those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, which may include: a flash drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk, etc.

[0230] The above are merely exemplary embodiments of this disclosure and should not be construed as limiting the scope of this disclosure. Any equivalent changes and modifications made in accordance with the teachings of this disclosure shall still fall within the scope of this disclosure. Those skilled in the art will readily conceive of embodiments of this disclosure upon considering the specification and practicing the disclosure herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not described herein. The specification and embodiments are to be considered exemplary only, and the scope and spirit of this disclosure are defined by the claims.

Claims

1. A parameterized propeller single-channel structure partitioning method, characterized in that, include: A spatial rectangular coordinate system for the propeller is determined, and a three-dimensional geometric model of the propeller corresponding to a single flow channel is generated based on the spatial rectangular coordinate system and the geometric parameters of the propeller. Establish an integral block corresponding to the three-dimensional geometric model of the propeller, and divide the integral block into at least two target regions; The at least two target regions are segmented, and the processed at least two target regions are associated. The step of dividing the overall block into at least two target regions includes: The entire block is divided according to a preset first direction to obtain the propeller shaft target area, the propeller hub target area, and the propeller hub target area; the preset first direction is parallel to the X-axis in the propeller's spatial rectangular coordinate system, and the origin and X-axis in the propeller's cylindrical coordinate system are consistent with the origin and X-axis in the propeller's spatial rectangular coordinate system. The process of segmenting the at least two target regions includes: The hub cap target area of ​​the propeller is extended according to a preset second direction; the preset second direction is the negative Y-axis of the propeller's spatial rectangular coordinate system. The target area of ​​the hub cap of the processed propeller is subjected to "Y-shaped" segmentation. The target region of the propeller hub is segmented according to a preset third direction; the preset third direction is the Z-axis direction parallel to the spatial rectangular coordinate system of the propeller. The center block of the target area of ​​the rotor hub of the processed propeller is subjected to "O-type" segmentation.

2. The method according to claim 1, characterized in that, The determination of the propeller's spatial rectangular coordinate system includes: Obtain the geometry of the propeller and take the center of the propeller disk as the origin of the spatial rectangular coordinate system; At least two coordinate axes of a spatial rectangular coordinate system are determined based on the propeller's rotation axis; The spatial rectangular coordinate system of the propeller is determined based on the origin of the spatial rectangular coordinate system and at least two coordinate axes of the spatial rectangular coordinate system.

3. The method according to claim 1, characterized in that, The geometric parameters of the propeller include the blade profile pitch and the radius parameter of the propeller. The process of generating a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the propeller's spatial Cartesian coordinate system and the propeller's geometric parameters includes: Based on the spatial rectangular coordinate system of the propeller and the pitch of the propeller blade profile, the two-dimensional curve expression of the propeller is determined; The cylindrical coordinate system of the propeller is obtained from the spatial rectangular coordinate system of the propeller, and the two-dimensional curve expression of the propeller is transformed based on the cylindrical coordinate system of the propeller. Based on the radius parameters of the propeller and the processed two-dimensional curve expression of the propeller, a three-dimensional geometric model of the propeller corresponding to a single flow channel is obtained.

4. The method according to claim 1, characterized in that, Before establishing the integral block corresponding to the three-dimensional geometric model of the propeller and dividing the integral block into at least two target regions, the method further includes: Determine whether the three-dimensional geometric model of the propeller has defects; When a defect is detected in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is repaired until the three-dimensional geometric model of the propeller is free of defects. When it is detected that there are no defects in the three-dimensional geometric model of the propeller, the three-dimensional geometric model of the propeller is classified. The integral block corresponding to the three-dimensional geometric model of the propeller includes: Create an integral block corresponding to the three-dimensional geometric model of the processed propeller.

5. The method according to claim 1, characterized in that, After the segmentation process of the at least two target regions and before the association process of the processed at least two target regions, the method further includes: The portion of the overall block corresponding to the rotation domain is extracted, and the blade tip region is determined from the processed overall block; wherein, the rotation domain of the overall block is determined based on the three-dimensional geometric model of the propeller after classification. The leaf tip end face area is subjected to "O-type" segmentation. The association process for the at least two target regions after processing includes: The at least two target regions and the leaf tip end face region after processing are associated.

6. A parameterized propeller single-channel structure partitioning device, characterized in that, include: The first processing module is used to determine the spatial rectangular coordinate system of the propeller, and generate a three-dimensional geometric model of the propeller corresponding to a single flow channel based on the spatial rectangular coordinate system of the propeller and the geometric parameters of the propeller. The second processing module is used to create an integral block corresponding to the three-dimensional geometric model of the propeller, and to divide the integral block into at least two target regions; The third processing module is used to perform segmentation processing on the at least two target regions and to perform association processing on the processed at least two target regions; The step of dividing the overall block into at least two target regions includes: The entire block is divided according to a preset first direction to obtain the propeller shaft target area, the propeller hub target area, and the propeller hub target area; the preset first direction is parallel to the X-axis in the propeller's spatial rectangular coordinate system, and the origin and X-axis in the propeller's cylindrical coordinate system are consistent with the origin and X-axis in the propeller's spatial rectangular coordinate system. The process of segmenting the at least two target regions includes: The hub cap target area of ​​the propeller is extended according to a preset second direction; the preset second direction is the negative Y-axis of the propeller's spatial rectangular coordinate system. The hub cap target area of ​​the processed propeller is subjected to "Y-shaped" segmentation. The target region of the propeller hub is segmented according to a preset third direction; the preset third direction is the Z-axis direction parallel to the spatial rectangular coordinate system of the propeller. The center block of the target area of ​​the rotor hub of the processed propeller is subjected to "O-type" segmentation.

7. A parameterized propeller single-channel structure partitioning device, characterized in that, Including the processor and memory; The processor is connected to the memory; The memory is used to store executable program code; The processor runs a program corresponding to the executable program code by reading the executable program code stored in the memory, in order to perform the method as described in any one of claims 1-5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the method as described in any one of claims 1-5.

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