Planet carrier back gouging optimization calculation method capable of reducing cost and improving efficiency

Abstract

The invention provides a cost-reducing and efficiency-increasing planet carrier back gouging optimization calculation method, which is characterized by comprising the following steps of: 1, determining a cutting surface of a parameterized model, and cutting a planet carrier into the parameterized model and a non-parameterized model; 2, a calculation model is established, and a non-parameter model is reserved; 3, obtaining various combinations of multi-arc composition parameters, and establishing an equation according to a geometric and position constraint relationship to obtain a parameterized model section under the overall coordinate system; 4, rotating the parameterized model screenshot grid to generate an entity grid, and exporting to generate a three-dimensional intermediate file; and 5, connecting entity grids of the non-parameter model and the parameterized model together, calculating to obtain multiple groups of stress values, extracting composition parameters of multiple arc segments corresponding to the minimum stress value, and drawing a back gouging drawing according to the group of parameters. According to the method, wind power gear box planet carrier back gouging is subjected to optimization calculation, so that cost is reduced, and efficiency is improved.

Description

Technical Field

[0001] The invention relates to the field of wind power gearboxes, and in particular to a planet carrier root cleaning optimization calculation method for wind power gearboxes for reducing costs and increasing efficiency. Background Art

[0002] With the rapid development of the domestic wind power market, the reliability of wind turbine structural parts has become increasingly important in design. The planetary frame of the wind turbine gearbox is a key component in the wind turbine, and its structural design is crucial. At present, finite element calculation is widely used in the structural design of the planetary frame. In the calculation of the planetary frame, the calculation results of the long head end root clearance are often too high, making it difficult to meet the safety factor requirements of relevant standards or specifications. Therefore, it is very necessary to design a suitable root clearance. However, the cost of purchasing an optimization software is high. If there is no optimization software to help, a lot of time will be wasted on repeated calculations, which is time-consuming and laborious. Therefore, it is very necessary to find an optimization calculation method that reduces costs and increases efficiency. Summary of the invention

[0003] The present invention provides a planet carrier root cleaning optimization calculation method for reducing costs and increasing efficiency, and its purpose is to solve the shortcomings of the prior art and optimize the calculation of the planet carrier root cleaning of a wind power gear box to reduce costs and increase efficiency.

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

[0005] A planet carrier root cleaning optimization calculation method for reducing costs and increasing efficiency, characterized by:

[0006] It includes five steps:

[0007] Step 1: According to the optimized part, the planet 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 rotating body. The projection length of the connecting surface with the non-parametric model in the plane parallel to the screen and passing through the central axis of the planet 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 overall coordinate system. The calculation model includes the planet carrier, pin shaft and spindle dummy. The spindle dummy is a hollow cylinder with a length from the bearing center plane of the spindle to the spindle end face. The position of the cross section of the parametric model in the plane parallel to the screen and passing through the center axis of the planet carrier in the overall coordinate system is called the first position. After the calculation model is calculated once, the solid mesh of the parametric model is deleted, and the remaining part is called the non-parametric model. In addition, the file that divides the two-dimensional mesh is saved, which is called the first template file.

[0009] Step 3: The parametric model has two concave right angles, and multi-arc clearing is designed at these two locations. Define the local coordinate system, and call the position of the parametric model section in the local coordinate system the second position, which differs from the overall coordinate system by only an axial value. First, determine several commonly used types of multi-arc segments based on experience, then determine the component parameters based on the geometric relationship and give the upper and lower limits of each parameter, and use Latin hypercube sampling to obtain multiple combinations of component parameters. Then, establish an equation based on the geometric and positional constraint relationship of the multi-arc segment, give the interval value, output the coordinates of all interval points of the multi-arc segment, and then connect the two multi-arc segments with other points of the parametric model in sequence. After position conversion, that is, from the second position to the first position, the parametric model section in the overall coordinate system is obtained.

[0010] Step 4: Use the meshing program to mesh the parametric model section in the overall coordinate system and extract the two-dimensional unit matrix and node matrix, write them into the first template file, and generate multiple two-dimensional intermediate files. Because it is impossible to ensure that the number of units on the connecting line of each parametric model screenshot is the same as that of the non-parametric model, two processing methods are used: for units with different numbers, manually adjust the node positions on the connecting line of the section to achieve node overlap, and then rotate the two-dimensional grid to generate a solid grid with the same angle interval as the non-parametric model and overlap the nodes, and export the three-dimensional intermediate file; for units with the same number of units, the operation steps are similar to the above, except that the finite element software is used directly when the nodes overlap, and the process file recording the above steps is saved as the second template file, and then the optimization software is used to read the second template file to automatically generate multiple three-dimensional intermediate files.

[0011] Step 5: Use finite element software to open the non-parametric model, import the three-dimensional intermediate file, combine the two parts, overlap the nodes and export them. Save the process files of these operations as the third template file. Then use the optimization software to read the third template file, replace the name of the imported three-dimensional intermediate file and the name of the export file, and the export file is called the calculation intermediate file. The optimization software calls the finite element software to batch calculate the calculation intermediate files to obtain multiple result intermediate files, and then use the optimization software to read all the result intermediate files, extract the composition parameters of the multi-arc segment corresponding to the minimum stress value and output them, and finally draw the root clearing two-dimensional diagram according to the composition parameters.

[0012] The present invention is beneficial in that:

[0013] 1. Because the multi-arc segment type is determined first, when establishing the equation, you only need to pay attention to the characteristics of the multi-arc segment itself, and there is no need to use more complex algorithms to find a suitable multi-arc segment combination. 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, a set of optimization software can be developed independently with very little manpower cost, saving procurement funds and additional software development costs, 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 process of optimizing calculations realizes batch calculations with the help of template files and intermediate files, which greatly improves the calculation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0018] Figure 1 The parametric model section of the planet carrier of the wind turbine gearbox;

[0019] Figure 2 Calculate the model for the planetary carrier of wind turbine gearbox;

[0020] Figure 3 It is the non-parametric model of the planetary carrier of wind turbine gearbox. DETAILED DESCRIPTION

[0021] In order to more clearly illustrate the technical solution of the present invention, the following will briefly introduce the drawings required for the description. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other embodiments can be obtained based on these drawings without creative work. In order to facilitate the understanding of the present invention, the present invention is described in more detail below in combination with the drawings and specific embodiments.

[0022] It should be noted that when an element is described as being "fixed to" another element, it may be directly on the other element, or one or more centered elements may exist therebetween. When an element is described as being "connected" to another element, it may be directly connected to the other element, or one or more centered elements may exist therebetween. The terms "upper", "lower", "inner", "outer", "bottom", etc. used in this specification indicate an 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 present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", "third", etc., etc. are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

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

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

[0025] Step 1: According to the optimized part, the planet carrier needs to cut out a parametric model at the long head end in advance. Figure 1 The figure abcdFijma in the figure is the cross section of the parametric model. Rotating it once is the parametric model. cd is the original plane of the planet carrier 1, which is called the web plane 100 here. dF, Fi, ij are the original faces of the planet carrier 1. The cutting surface is divided into two planes and two circular faces. The faces where ab and jm are located are the cutting plane 200, and the faces where bc and ma are located are the cutting circular faces. Their positions are not only affected by the structural size of the planet carrier, but also the lengths of ab, bc, jm and ma are preferably integer multiples of the mesh size of the parametric model cross section, which is conducive to the processing of node overlap.

[0026] Step 2: Establish a finite element model in the overall coordinate system. The calculation model includes the planet carrier 1, the pin 2 and the main shaft 3. The main shaft 3 is made into a main shaft dummy during modeling, that is, a hollow cylinder. The length is from the bearing center plane 4 of the main shaft 3 to the end face of the main shaft 3. The end face is not numbered because it is blocked by the planet carrier. The position of the cross section of the parametric model in the overall coordinate system in the plane parallel to the screen and passing through the central axis of the planet carrier 1 is called the first position. The modeling method can be found in Invention 201911181148.9: "A fatigue calculation method for a planetary carrier of a wind power gearbox based on friction contact". First, the surface pressure between the planetary carrier 1 and the shrink disk is calculated based on the thick-walled cylinder theory, and then the surface pressure is applied to the outer surface of the long head end of the planetary carrier 1 according to the width of the shrink disk; then, the contact between the pin 2 and the planetary carrier 1, the main shaft 3 and the planetary carrier 1 is set to friction contact, the fit between the pin 2 and the planetary carrier 1 is reflected by the offset, and the contact between the main shaft 3 and the planetary carrier 1 is set to just contact; finally, the bearing force is applied to the exposed surface of each pin, and a fixed constraint is added to the bearing center plane 4. After the calculation model is processed, 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 parameterized model is deleted, and the remaining part is called the non-parametric model, which also contains all data such as mesh, contact, constraints and loads. In addition, the file that divides the two-dimensional grid needs to be saved, which is called the first template file.

[0027] Step 3: The parametric model has two concave right angles, AdE and GiK, where multi-arc root cleaning is designed. Figure 1 As shown in Figure 1The position in is called the second position, and the local coordinate system X1O1Y1 is defined. It differs from the global coordinate system by only one axial value. Because there are many kinds of compositions of multi-arc segments, it is very difficult to design the most suitable multi-arc segment. Therefore, it is considered to determine several commonly used types of multi-arc segments directly based on experience. For each type, the composition parameters of the multi-arc segment are determined according to the geometric relationship and the upper and lower limits of each parameter are given. Then, Latin hypercube sampling is used to obtain various combinations of composition parameters. Then, according to the geometric and position constraint relationship of the multi-arc segment, an equation is established, the interval value is given, the coordinates of all interval points of the multi-arc segment are output, and the two multi-arc segments are connected with the straight lines ab, bc, cA, EF, FG, Kj, jm and ma in sequence to form a parametric model section in the local coordinate system, and then the position conversion is performed, that is, from the second position to the first position, to obtain the parametric model section in the global coordinate system, so that the parametric model and the non-parametric model nodes coincide. The position conversion relationship and the definition of the axial value here are related to the programming ideas, and the specific operation can be embodied in the program with the existing technology programming.

[0028] Step 4: Use the meshing program to mesh the parametric model section in the overall coordinate system and extract the two-dimensional unit matrix and node matrix, and write them into the first template file to generate a two-dimensional intermediate file. Because there are many combinations of the constituent parameters of the multi-arc segment, there will not be only one set of multi-arc segments that satisfy the equation, so the number of two-dimensional intermediate files generated by the multi-arc segments that satisfy the equation is determined. Due to the size of the parametric model and the influence of the multi-arc segment structure, it cannot be guaranteed that the number of units on the line connecting each parametric model screenshot and the non-parametric model is the same. Therefore, two processing methods are divided accordingly: for units with different numbers, each 2D intermediate file is imported into the finite element software in turn, and the mesh nodes on the lines ab, bc, jm and ma are manually adjusted according to the mesh size and number of the cross-section connection positions of the non-parametric model and the parametric model to achieve node overlap, and then the 2D mesh is rotated to generate a solid mesh with the same angle interval as the non-parametric model and the nodes are overlapped, and finally the solid mesh is exported to generate a 3D intermediate file; for units with the same number, the operation steps are similar to the above, except that the step of manually adjusting the node position is omitted, and the finite element software is used directly to make the nodes overlap, and the process file recording the above steps is saved as the second template file, and then the optimization software is used to read the second template file to automatically generate a 3D intermediate file.

[0029] Step 5: Use finite element software to open the non-parametric model, import the three-dimensional intermediate file, combine the two parts, overlap the nodes and export them. Save the process files of these operations as the third template file. Then use the optimization software to read the third template file, replace the name of the imported three-dimensional intermediate file and the name of the export file, and the export file is called the calculation intermediate file. The optimization software calls the finite element software to batch calculate the calculation intermediate files to obtain multiple result intermediate files, and 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, and finally draw the root cleaning drawing according to the component parameters.

[0030] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the embodiments can be referred to each other. The above description of the disclosed embodiments enables professionals and technicians in this field to implement or use the present invention. Various modifications to these embodiments will be obvious to professionals and technicians in this field, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to these embodiments shown in this article, but will comply with the widest range consistent with the principles and novel features disclosed herein.

Claims

1. A planet carrier root cleaning optimization calculation method for reducing costs and increasing efficiency, characterized by: It includes five steps: Step 1: According to the optimized part, the planet carrier is cut into a parametric model and a non-parametric model. The cutting surface is divided into two planes and two circumferential surfaces. The parametric model is a rotating body. The projection length of the connecting surface with the non-parametric model in the plane parallel to the screen and passing through the central axis of the planet carrier is preferably an integer multiple of the cross-sectional mesh size of the parametric model. Step 2: Establish a finite element model in the overall coordinate system. The calculation model includes the planet carrier, the pin shaft and the spindle prosthesis. The spindle prosthesis is a hollow cylinder with a length from the bearing center plane to the spindle end face. The position of the cross section of the parametric model in the plane parallel to the screen and passing through the center axis of the planet carrier in the overall coordinate system is called the first position. After the calculation model is calculated once, the solid mesh of the parametric model is deleted, and the remaining part is called the non-parametric model. In addition, the file for dividing the two-dimensional mesh is saved, which is called the first template file. Step 3: The parametric model has two concave right angles, and multi-arc segment root cleaning is designed at these two locations; define the local coordinate system, and the position of the parametric model section in the local coordinate system is called the second position, which is only different from the overall coordinate system by an axial value; first determine several commonly used multi-arc segment types based on experience, and then determine the component parameters based on the geometric relationship and give the upper and lower limits of each parameter, and use Latin hypercube sampling to obtain multiple combinations of component parameters; Then, an equation is established according to the geometric and positional constraint relationship of the multi-arc segment, and the interval value is given, and the coordinates of all interval points of the multi-arc segment are output. Then, two multi-arc segments are sequentially connected with other points of the parametric model, and after position transformation, that is, from the second position to the first position, the parametric model section in the overall 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 unit matrix and node matrix, write them into the first template file, and generate multiple two-dimensional intermediate files; Since it is impossible to ensure that the number of units on the connecting line of each parametric model screenshot and the non-parametric model is the same, two processing methods are used: for units with different numbers, the node positions on the connecting line of the cross section are manually adjusted to achieve node overlap, and then the two-dimensional grid is rotated to generate a solid grid with the same angle interval as the non-parametric model and the nodes are overlapped, and the three-dimensional intermediate file is exported; for units with the same number, the operation steps are similar to the above, except that the finite element software is used directly to complete the node overlap, and the process file recording the above steps is saved as the second template file, and then the optimization software is used to read the second template file to automatically generate multiple three-dimensional intermediate files; Step 5: Use finite element software to open the non-parametric model, import the 3D intermediate file, combine the two parts together, overlap the nodes and export; save the process files of these operations as the third template file; Then the third template file is read by using the optimization software, and the name of the imported three-dimensional intermediate file and the name of the exported file are replaced, and the exported file is called the calculation intermediate file; The optimization software calls the finite element software to batch calculate the intermediate files to obtain multiple result intermediate files. The optimization software is then used to read all the result intermediate files, extract the composition parameters of the type of multi-arc segments corresponding to the minimum stress value and output them. Finally, a root clearing two-dimensional diagram is drawn according to the composition parameters.

2. A planet carrier root cleaning optimization calculation method for reducing costs and increasing efficiency as claimed in claim 1, characterized in that: Based on this method, an optimization software is developed to facilitate the implementation of various operations.

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