A cost-reducing and efficiency-improving optimization calculation method for root cleaning of a planetary carrier

Abstract

The application provides a cost-reducing and efficiency-improving optimization calculation method for a planet carrier root cutting, and is characterized in that: step one is to determine a cutting surface of a parameterized model, and cut the planet carrier into a parameterized model and a non-parameter model; step two is to establish a calculation model and reserve the non-parameter model; step three is to obtain a plurality of combinations of parameters of a plurality of arc segments, establish equations according to geometric and position constraint relationships, and obtain a parameterized model section under a general coordinate system; step four is to rotate a parameterized model section grid to generate a solid grid, and export a three-dimensional intermediate file; and step five is to connect the non-parameter model and the parameterized model solid grid together, calculate a plurality of stress values, extract the composition parameters of the plurality of arc segments corresponding to the minimum stress value, and draw a root cutting drawing according to the parameters. The application optimizes the calculation of the planet carrier root cutting of a wind power gear box, and reduces the cost and improves the efficiency.

Description

Technical Field

[0001] This invention relates to the field of wind turbine gearboxes, specifically to a cost-reducing and efficiency-enhancing optimization calculation method for planetary carriers in wind turbine gearboxes. Background Technology

[0002] With the rapid development of the domestic wind power market, the reliability of wind turbine structural components is becoming increasingly important in design. The planetary gearbox carrier is a key component of a wind turbine, and its structural design is crucial. Currently, finite element analysis (FEM) is widely used in the structural design of planetary gearbox carriers. However, in these calculations, the results for the long end root clearing are often too high, making it difficult to meet the safety factor requirements of relevant standards or specifications. Therefore, designing appropriate root clearing is essential. However, purchasing optimization software is costly, and without its assistance, a significant amount of time is wasted on repetitive calculations, which is both time-consuming and labor-intensive. Therefore, finding a cost-effective and efficient optimization calculation method is crucial. Summary of the Invention

[0003] This invention provides a cost-reducing and efficiency-enhancing optimization calculation method for planetary gear carrier root cleaning. Its purpose is to overcome the shortcomings of the existing technology and optimize the root cleaning calculation of the planetary gear carrier of wind turbine gearbox to reduce costs and increase efficiency.

[0004] The technical solution adopted by this invention to solve its technical problem is:

[0005] A cost-reducing and efficiency-enhancing planetary carrier root clearing optimization calculation method, characterized by:

[0006] It includes five steps:

[0007] Step 1: Based on the optimization area, the planetary carrier is cut into a parametric model and a non-parametric model. The cutting surface is divided into two planes and two circular surfaces. The parametric model is a solid of revolution. The projection length of the connection surface with the non-parametric model in a plane parallel to the screen and passing through the central axis of the planetary carrier is preferably an integer multiple of the cross-sectional mesh size of the parametric model.

[0008] Step 2: Establish a finite element model in the global coordinate system. The computational model includes the planetary carrier, pins, and a dummy spindle. The dummy spindle is a hollow cylinder, with its length measured from the bearing center face to the spindle end face. The position of the cross-section of the parametric model in the global coordinate system, parallel to the screen and passing through the planetary carrier's central axis, is called the first position. After the computational model has been calculated once, the parametric model's solid mesh is deleted, leaving the non-parametric model. A separate file containing the two-dimensional mesh is saved, called the first template file.

[0009] Step 3: The parametric model has two concave right angles. Multi-arc segments are designed at these two locations for root clearing. A local coordinate system is defined, and the position of the parametric model section in the local coordinate system is called the second position. It differs from the global coordinate system only by an axial value. First, several commonly used multi-arc segment types are determined empirically. Then, the component parameters are determined based on geometric relationships, and the upper and lower limits of each parameter are given. Latin hypercube sampling is used to obtain various combinations of component parameters. Then, equations are established based on the geometric and positional constraints of the multi-arc segments, and interval values ​​are given. The coordinates of all interval points of the multi-arc segments are output. Then, the two multi-arc segments are connected to other points of the parametric model in sequence. After position transformation, i.e., from the second position to the first position, the parametric model section in the global coordinate system is obtained.

[0010] Step 4: Use a meshing program to mesh the parametric model cross-section in the global coordinate system and extract the 2D element matrix and node matrix. Write this into the first template file to generate multiple 2D intermediate files. Since it's impossible to guarantee that the number of elements on the connecting lines between each parametric model screenshot and the non-parametric model is the same, two processing methods are used: For those with different numbers of elements, manually adjust the node positions on the connecting lines to achieve node overlap, then rotate the 2D mesh to generate a solid mesh with the same angular spacing as the non-parametric model and overlap the nodes, then export the 3D intermediate file; for those with the same number of elements, the operation steps are similar to the above, except that node overlap is directly completed by the finite element software. Save the process file recording the above steps as the second template file, and then use optimization software to read the second template file to automatically generate multiple 3D intermediate files.

[0011] Step 5: Open the nonparametric model using finite element software, import the 3D intermediate file, combine the two parts together, then reassemble the nodes and export. Save this process file as the third template file. Then, use optimization software to read the third template file, replace the names of the imported 3D intermediate file and the exported file; the exported file is called the calculation intermediate file. Use the optimization software to call the finite element software to perform batch calculations on the calculation intermediate files, obtaining multiple result intermediate files. Then, use the optimization software to read all the result intermediate files, extract the component parameters of the multi-arc segment corresponding to the minimum stress value, and output them. Finally, draw the root clearing 2D diagram based on the component parameters.

[0012] The advantages of this invention are:

[0013] 1. Since the type of multi-arc segments is determined first, when establishing the equations, we only need to focus on the characteristics of the multi-arc segments themselves, without needing to use a more complex algorithm to find a suitable combination of multi-arc segments. This not only reduces the programming difficulty but also saves programming time.

[0014] 2. Compared with commercial optimization software, because the algorithm is relatively simple, an optimization software can be developed independently with very little manpower, saving procurement costs and additional software development expenses, and shortening the software development cycle.

[0015] 3. Because the optimization algorithm only modifies the parametric model of the planetary carrier and the parametric model has a simple structure, the non-parametric model only needs to be processed once, which reduces a lot of repetitive work and improves work efficiency.

[0016] 4. The optimized calculation process utilizes template files and intermediate files to achieve batch calculations, greatly improving calculation efficiency. Attached Figure Description

[0017] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0018] Figure 1 Cross section of the parametric model of the planetary carrier of a wind turbine gearbox;

[0019] Figure 2 A calculation model for the planetary carrier of a wind turbine gearbox;

[0020] Figure 3 This is a non-parametric model of the planetary carrier of a wind turbine gearbox. Detailed Implementation

[0021] To more clearly illustrate the technical solution of the present invention, the accompanying drawings used in the description will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other embodiments can be obtained based on these drawings without creative effort. To facilitate understanding of the present invention, the present invention will be described in more detail below with reference to the accompanying drawings and specific embodiments.

[0022] It should be noted that when an element is described as being "fixed to" another element, it can be directly on the other element, or one or more intermediate elements may exist between them. When an element is described as being "connected to" another element, it can be directly connected to the other element, or one or more intermediate elements may exist between them. The terms "upper," "lower," "inner," "outer," "bottom," etc., used in this specification indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] The specific implementation of this invention is as follows:

[0024] like Figure 1 , Figure 2 , Figure 3 As shown:

[0025] Step 1: Based on the optimized area, the planetary carrier needs to have a parametric model pre-cut from the long end. Figure 1 The graphic abcdFijma in the diagram represents the cross-section of the parametric model. Rotating it one full turn gives the parametric model. cd is the original plane of planet carrier 1, referred to here as web plane 100. dF, Fi, and ij are the original faces of planet carrier 1. The cutting surfaces are divided into two planes and two circular faces. The face containing ab and jm is the cutting plane 200, and the face containing bc and ma is the cutting circular face. Their positions are not only affected by the structural dimensions of the planet carrier, but the lengths of ab, bc, jm, and ma are preferably integer multiples of the cross-sectional mesh size of the parametric model, which is beneficial for handling node overlap.

[0026] Step 2: Establish a finite element model in the global coordinate system. The calculation model includes planet carrier 1, pin 2, and spindle 3. Spindle 3 is modeled as a dummy spindle, i.e., a hollow cylinder. The length taken is from the bearing center surface 4 of spindle 3 to the end face of spindle 3. The end face is not labeled because it is obscured by the planet carrier. The position of the cross-section of the parametric model in the global coordinate system in a plane parallel to the screen and passing through the central axis of planet carrier 1 is called the first position. The modeling method can be found in Invention 201911181148.9: "A Fatigue Calculation Method for Planetary Carriers of Wind Turbine Gearboxes Based on Frictional Contact". First, the surface pressure between the planetary carrier 1 and the contraction disk is calculated based on the thick-walled cylinder theory. Then, this surface pressure is applied to the outer surface of the long end of the planetary carrier 1 according to the width of the contraction disk. Next, the contact between the pin 2 and the planetary carrier 1, and between the main shaft 3 and the planetary carrier 1, is set as frictional contact. The fit between the pin 2 and the planetary carrier 1 is represented by an offset, and the contact between the main shaft 3 and the planetary carrier 1 is set as just contact. Finally, bearing force is applied to the exposed surface of each pin, and a fixed constraint is added to the bearing center plane 4. After processing the calculation model, the first calculation is performed using finite element software to ensure that the calculation can proceed normally. After the calculation, the solid mesh of the parametric model is deleted, leaving the part called the non-parametric model, which still contains all data such as mesh, contact, constraint, and load. Additionally, the file containing the two-dimensional mesh needs to be saved; this is called the first template file.

[0027] Step 3: The parametric model has two concave right angles, AdE and GiK, where multi-segment root clearing is designed. Combined with... Figure 1 As shown, the parametric model section is in Figure 1The position in the equation is called the second position, defined by a local coordinate system X1O1Y1, which differs from the global coordinate system only by an axial value. Since there are many possible compositions of multi-arc segments, designing the most suitable multi-arc segment is very difficult. Therefore, we consider directly determining several commonly used multi-arc segment types based on experience. For each type, the composition parameters of the multi-arc segment are determined based on geometric relationships, and the upper and lower limits of each parameter are given. Then, Latin hypercube sampling is used to obtain various combinations of composition parameters. Next, equations are established based on the geometric and positional constraints of the multi-arc segments, interval values ​​are given, and the coordinates of all interval points of the multi-arc segment are output. Two multi-arc segments are then connected sequentially to the lines ab, bc, cA, EF, FG, Kj, jm, and ma to form a parametric model section in the local coordinate system. A position transformation is then performed, from the second position to the first position, to obtain the parametric model section in the global coordinate system. This facilitates the overlap of nodes between the parametric model and the non-parametric model. The position transformation relationship and the definition of the axial values ​​here are related to the programming approach, and the specific operations can be implemented in the program using existing technology.

[0028] Step 4: Use a meshing program to mesh the parametric model section in the global coordinate system, extract the 2D element matrix and node matrix, and write them into the first template file to generate a 2D intermediate file. Because the component parameters of the multi-segment have multiple combinations, there will be more than one set of multi-segment satisfying the equations. Therefore, the number of 2D intermediate files generated from multi-segment satisfying the equations is determined. Due to the influence of the size of the parametric model and the multi-segment structure, it cannot be guaranteed that the number of elements on the connecting lines between each parametric model screenshot and the non-parametric model is the same. Therefore, two processing methods were adopted: For those with different numbers of elements, each 2D intermediate file was imported into the finite element software in sequence. Based on the mesh size and number at the connection position of the nonparametric model and the parametric model section, the mesh nodes on the lines ab, bc, jm, and ma were manually adjusted to achieve node overlap. Then, the 2D mesh was rotated to generate a solid mesh with the same angular interval as the nonparametric model and the nodes were overlapped. Finally, the solid mesh was exported to generate a 3D intermediate file. For those with the same number of elements, the operation steps were similar to the above, except that the step of manually adjusting the node position was omitted. The finite element software was used directly to make the nodes overlap. The process file recording the above steps was saved as the second template file. Then, the optimization software was used to read the second template file and automatically generate the 3D intermediate file.

[0029] Step 5: Open the nonparametric model using finite element software, import the 3D intermediate file, combine the two parts together, then reassemble the nodes and export. Save this process file as the third template file. Then, use optimization software to read the third template file, replace the names of the imported 3D intermediate file and the exported file; the exported file is called the calculation intermediate file. Use the optimization software to call the finite element software to perform batch calculations on the calculation intermediate files, obtaining multiple result intermediate files. Then, use the optimization software to read all the result intermediate files, extract the component parameters of the multi-arc segment corresponding to the minimum stress value, and output them. Finally, draw the root clearance drawing based on the component parameters.

[0030] The various embodiments described in this specification are presented in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A cost-reducing and efficiency-enhancing planetary carrier root clearing optimization calculation method, characterized in that: It includes five steps: Step 1: Based on the optimization area, the planetary carrier is cut into a parametric model and a non-parametric model. The cutting surface is divided into two planes and two circular surfaces. The parametric model is a solid of revolution. The projection length of the connection surface with the non-parametric model in the plane parallel to the screen and passing through the central axis of the planetary carrier is an integer multiple of the cross-sectional mesh size of the parametric model. Step 2: Establish a finite element model in the global coordinate system. The calculation model includes a planetary carrier, a pin shaft, and a dummy spindle. The dummy spindle is a hollow cylinder, and its length is taken from the bearing center face to the spindle end face. The position of the cross section of the parametric model in the global coordinate system in a plane parallel to the screen and passing through the central axis of the planetary carrier is called the first position. After the calculation model has been calculated once, delete the solid mesh of the parametric model. The remaining part is called the non-parametric model. In addition, save the file that divides the two-dimensional mesh, which is called the first template file. Step 3: The parametric model has two concave right angles. Design multi-arc segments at these two locations to clear the roots. Define a local coordinate system. The position of the parametric model section in the local coordinate system is called the second position. The local coordinate system differs from the global coordinate system only by an axial value. First, determine several commonly used multi-arc segment types based on experience. Then, determine the component parameters based on geometric relationships and give the upper and lower limits of each parameter. Use Latin hypercube sampling to obtain multiple combinations of component parameters. Then, based on the geometric and positional constraints of the multi-arc segments, equations are established and interval values ​​are given. The coordinates of all interval points of the multi-arc segments are output. Then, the two multi-arc segments are connected to other points of the parametric model in sequence. After position transformation, that is, from the second position to the first position, the parametric model section in the global coordinate system is obtained. Step 4: Use a meshing program to mesh the parametric model section in the global coordinate system and extract the two-dimensional element matrix and node matrix, write them into the first template file, and generate multiple two-dimensional intermediate files; Because it's impossible to guarantee that the number of elements on the connecting lines between each parametric model screenshot and the non-parametric model is the same, two processing methods were used: For those with different numbers of elements, the node positions on the connecting lines of the cross sections were manually adjusted to achieve node overlap, and then the 2D mesh was rotated to generate a solid mesh with the same angular spacing as the non-parametric model and overlapped the nodes, before exporting the 3D intermediate file; For those with the same number of elements, the node positions on the connecting lines of the cross sections were directly adjusted by the finite element software to achieve node overlap, and then the 2D mesh was rotated to generate a solid mesh with the same angular spacing as the non-parametric model and overlapped the nodes, before exporting the 3D intermediate file. Save the process file recording the above steps as the second template file, and then use optimization software to read the second template file and automatically generate multiple 3D intermediate files; Step 5: Open the nonparametric model with finite element software, import the 3D intermediate file, combine the two parts together, then merge the nodes and export; save the process files of these operations as the third template file. Then, the optimization software is used to read the third template file, replace the name of the imported 3D intermediate file and the name of the exported file. The exported file is called the calculation intermediate file. By using optimization software to call finite element software to perform batch calculations on intermediate calculation files, multiple intermediate result files are obtained. Then, the optimization software reads all intermediate result files, extracts the component parameters of the multi-arc segment corresponding to the minimum stress value, and outputs them. Finally, a two-dimensional diagram of the root clearing is drawn based on the component parameters.

2. The cost-reduction and efficiency-enhancing planetary carrier root clearing optimization calculation method as described in claim 1, characterized in that: Based on this method, develop an optimization software to facilitate various operations.

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