Airfoil optimization method and device, storage medium, electronic device and computer program product
By optimizing the airfoil, using the target weight coefficient and the scaling technology of the standard circular airfoil, the existing airfoil has solved the problem of poor buckling resistance, and improved the safety and aerodynamic performance of the wind power blades.
Patent Information
- Application Number
- CN202411995976.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-31
- Publication Date
- 2025-05-06
AI Technical Summary
The existing airfoil has poor buckling resistance near the maximum chord length, which leads to prone to fracture of large wind power blades.
By determining the maximum thickness ratio of the target airfoil and the standard circular airfoil, scaling the point coordinates of the standard circular airfoil, obtaining the optimized target coordinate set, and optimizing the airfoil based on the target weight coefficient to improve buckling resistance.
The buckling resistance of the airfoil is improved, and the risk of blade breakage or damage is reduced under extreme wind conditions, while ensuring the aerodynamic performance of the airfoil.
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Abstract
Description
Technical Field
[0001] The present application relates to the field of blades, and more specifically, to an airfoil optimization method and device, a storage medium, an electronic device, and a computer program product. Background Art
[0002] In wind farms, large wind turbine blades over 100 meters are becoming more and more common. They usually weigh tens of tons, and the maximum chord length of the blade exceeds 5 meters. They are extremely prone to buckling near the maximum chord length, which is also the location where many large blades currently break. In order to improve the safety and reliability of the blades at this point, modern large blades are generally designed with a small belly plate added to the trailing edge of the section to improve the buckling resistance here. When designing the airfoil here, although the structural characteristics are mainly considered, the buckling stability considerations are ignored.
[0003] With regard to the problem of poor anti-buckling performance of existing airfoils in the related technology, no effective solution has been proposed so far.
[0004] Therefore, it is necessary to improve the related technology to overcome the above-mentioned defects in the related technology. Summary of the invention
[0005] The embodiments of the present application provide an airfoil optimization method and device, a storage medium, an electronic device, and a computer program product to at least solve the problem of poor anti-buckling performance of existing airfoils.
[0006] According to one aspect of an embodiment of the present application, there is provided an airfoil optimization method, comprising: determining a target airfoil and a standard circular airfoil, wherein the ratio of the maximum thickness to the chord length of the standard circular airfoil is equal to one; and scaling the coordinates of points in a first portion of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the coordinates of the scaled points in the first portion of the standard circular airfoil, the first portion being an area from the airfoil maximum thickness point to the trailing edge of the airfoil; determining a target weight coefficient; based on the target weight coefficient, obtaining a target coordinate set according to the first coordinate set and the second coordinate set, wherein the second coordinate set includes the coordinates of the points in the first portion of the target airfoil, and the target coordinate set includes the coordinates of the points in the first portion of the optimized target airfoil; optimizing the first portion of the target airfoil based on the target coordinate set.
[0007] In an exemplary embodiment, the coordinates of points in the first portion of the standard circular airfoil are scaled according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, including: determining the ratio of the maximum thickness of the target airfoil to the maximum thickness of the standard circular airfoil to obtain a target ratio; multiplying the ordinate of the coordinates of each point in the first portion of the standard circular airfoil by the target ratio to obtain the first coordinate set.
[0008] In an exemplary embodiment, based on the target weight coefficient, obtaining a target coordinate set according to the first coordinate set and the second coordinate set includes: when the first coordinate set includes the coordinates of N points in the first part of the standard circular airfoil and the second coordinate set includes the coordinates of the corresponding N points in the first part of the target airfoil, processing is performed according to the i-th coordinate in the first coordinate set and the i-th coordinate corresponding to the second coordinate set in the following manner to obtain the target coordinate set, wherein i is 1, 2, ..., N: the i-th coordinate in the first coordinate set is (x 1 ,y 1 ), the i-th coordinate in the second coordinate set is (x 1 ,y 2 ), the i-th coordinate in the target coordinate set is (x 1 ,y 1 *(1-C)+y 2 *C), where C is the target weight coefficient.
[0009] In an exemplary embodiment, the method also includes: determining multiple weight values that meet preset conditions from a preset range, wherein the preset conditions include: the target airfoil after optimization based on the weight coefficient meets preset aerodynamic performance; determining a first weight coefficient among the multiple weight values as the target weight coefficient, wherein a target curvature determined based on the first weight coefficient is greater than a target curvature determined based on weight coefficients other than the first weight coefficient among the multiple weight values; wherein the target curvature is equal to the sum of the absolute values of the average curvature of the pressure surface and the absolute values of the average curvature of the suction surface of the first part of the target airfoil after optimization based on the weight coefficient; wherein optimizing the target airfoil based on the weight coefficient includes: obtaining a reference coordinate set based on the first coordinate set and the second coordinate set based on the weight coefficient; and optimizing the first part of the target airfoil based on the reference coordinate set.
[0010] In an exemplary embodiment, the method further includes: determining the average curvature of the pressure surface of the first portion of the target airfoil by: determining an expression for the pressure surface of the first portion of the target airfoil; determining the curvatures of multiple points of the first portion of the target airfoil based on the expression for the pressure surface, and determining the average value of the curvatures of the multiple points as the average curvature of the pressure surface of the first portion of the target airfoil.
[0011] In an exemplary embodiment, the method further includes: determining the average curvature of the suction surface of the first part of the target airfoil by: determining an expression for the suction surface of the first part of the target airfoil; determining the curvatures of multiple points of the first part of the target airfoil based on the expression for the suction surface, and determining the average value of the curvatures of the multiple points as the average curvature of the suction surface of the first part of the target airfoil.
[0012] According to another aspect of an embodiment of the present application, there is also provided an airfoil optimization device, comprising: a first determination module, for determining a target airfoil and a standard circular airfoil, wherein the ratio of the maximum thickness to the chord length of the standard circular airfoil is equal to one; a scaling module, for scaling the coordinates of points in the first part of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the coordinates of the points in the first part of the scaled standard circular airfoil, and the first part is the area from the airfoil maximum thickness point to the trailing edge of the airfoil; a second determination module, for determining a target weight coefficient; a third determination module, for obtaining a target coordinate set based on the first coordinate set and the second coordinate set based on the target weight coefficient, wherein the second coordinate set includes the coordinates of the points in the first part of the target airfoil, and the target coordinate set includes the coordinates of the points in the first part of the optimized target airfoil; an optimization module, for optimizing the first part of the target airfoil based on the target coordinate set.
[0013] According to another aspect of the embodiment of the present application, a computer-readable storage medium is further provided, wherein the computer-readable storage medium includes a stored program, wherein the program is configured to execute the above-mentioned airfoil optimization method when running.
[0014] According to another aspect of the embodiment of the present application, there is also provided an electronic device, including a memory and a processor, wherein the memory stores a computer program, wherein the processor is configured to execute the above-mentioned airfoil optimization method through the computer program.
[0015] According to another aspect of the embodiments of the present application, a computer program product is provided, including a computer program, and the above-mentioned airfoil optimization method is implemented when the computer program is executed by a processor.
[0016] The present application, by determining the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil, scales the coordinates of the points in the area from the maximum thickness point of the airfoil to the trailing edge of the standard circular airfoil, obtains a first coordinate set, and then based on the target weight coefficient, determines the coordinates of the optimized points in the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil according to the coordinates of the points in the same area of the first coordinate set and the target airfoil, thereby optimizing the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil. Since the scaling is performed in proportion to the maximum thickness of the target airfoil, the basic structure of the airfoil is guaranteed. Then, by selecting the target weight coefficient, the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil is optimized based on the target weight, so that the sum of the absolute values of the curvature of the suction surface and the pressure surface of the optimized target airfoil is greater than the preset threshold, thereby improving the anti-buckling property of the target airfoil, thereby solving the problem of poor anti-buckling property of the existing airfoil. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.
[0018] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.
[0019] Figure 1 It is a hardware structure block diagram of a mobile terminal of an airfoil optimization method according to an embodiment of the present application;
[0020] Figure 2 is a flow chart of an airfoil optimization method according to an embodiment of the present application;
[0021] Figure 3 It is a structural block diagram of an airfoil optimization device according to an embodiment of the present application. DETAILED DESCRIPTION
[0022] In order to enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of this application.
[0023] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.
[0024] The method embodiments provided in the embodiments of the present application can be executed in a mobile terminal, a computer terminal or a similar computing device. Taking running on a mobile terminal as an example, Figure 1 is a hardware structure block diagram of a mobile terminal of an airfoil optimization method according to an embodiment of the present application. Figure 1 As shown, the mobile terminal may include one or more ( Figure 1 Only one is shown in the figure) a processor 102 (the processor 102 may include but is not limited to a processing device such as a microprocessor (MP) or a programmable logic device (FPGA)) and a memory 104 for storing data, wherein the mobile terminal may also include a transmission device 106 and an input / output device 108 for communication functions. It can be understood by those skilled in the art that Figure 1 The structure shown is for illustration only and does not limit the structure of the mobile terminal. Figure 1 More or fewer components as shown, or with Figure 1 Different configurations shown.
[0025] The memory 104 can be used to store computer programs, for example, software programs and modules of application software, such as the computer program corresponding to the airfoil optimization method in the embodiment of the present application. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, that is, to implement the above method. The memory 104 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some examples, the memory 104 may further include a memory remotely arranged relative to the processor 102, and these remote memories may be connected to the mobile terminal via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and a combination thereof.
[0026] The transmission device 106 is used to receive or send data via a network. The specific example of the above network may include a wireless network provided by a communication provider of the mobile terminal. In one example, the transmission device 106 includes a network adapter (Network Interface Controller, referred to as NIC), which can be connected to other network devices through a base station so as to communicate with the Internet. In one example, the transmission device 106 can be a radio frequency (RF) module, which is used to communicate with the Internet wirelessly.
[0027] In order to solve the above problems, this embodiment provides an airfoil optimization method, including but not limited to being applied to the above mobile terminal. Figure 2 is a flow chart of an airfoil optimization method according to an embodiment of the present application, such as Figure 2 As shown, the process includes the following steps S202 to S210, and there is no specific order in which steps S202 and S204 are executed:
[0028] Step S202: determining a target airfoil and a standard circular airfoil, wherein a ratio of a maximum thickness to a chord length of the standard circular airfoil is equal to one;
[0029] It should be noted that the target airfoil is an airfoil based on an existing design and may need to be improved in terms of structural strength or aerodynamic performance; the standard circular airfoil is an idealized airfoil model with a ratio of maximum thickness to chord length of 1, which means that the thickness of the entire airfoil from the leading edge to the trailing edge is uniform. This airfoil shape theoretically has good structural stability.
[0030] Step S204: scaling the coordinates of the points in the first part of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the scaled coordinates of the points in the first part of the standard circular airfoil, and the first part is an area from the maximum thickness point of the airfoil to the trailing edge of the airfoil;
[0031] It should be noted that, according to the ratio of the maximum thickness of the target airfoil to the maximum thickness of the standard circular airfoil, the geometric dimensions of the tail of the standard circular airfoil (from the maximum thickness point to the trailing edge) are adjusted to obtain the first coordinate set. This process is essentially to adjust the shape of the standard circular airfoil to match the thickness and chord length of the target airfoil while retaining the structural advantages of the standard circular airfoil, providing a basis for subsequent optimization.
[0032] Optionally, the standard circle is divided into two parts, a front and a rear part, and the coordinate points of the rear half are selected as the points in the first part of the standard circular airfoil.
[0033] Step S206: Determine the target weight coefficient;
[0034] It should be noted that the selection of the target weight coefficient is the key, which determines the proportion of the target airfoil and the adjusted standard circular airfoil in the final optimized airfoil, that is, the balance point between structural stability and aerodynamic efficiency.
[0035] Optionally, the first portion of the target airfoil is optimized based on the target weight coefficient so that the sum of the absolute values of the curvatures of the suction surface and the pressure surface of the first portion of the optimized target airfoil is greater than a preset threshold.
[0036] Step S208: Based on the target weight coefficient, obtain a target coordinate set according to the first coordinate set and the second coordinate set, wherein the second coordinate set includes coordinates of points in the first part of the target airfoil, and the target coordinate set includes coordinates of points in the first part of the optimized target airfoil;
[0037] Optionally, determine the chordwise position x of the maximum thickness of the target airfoil i , so according to x i The target airfoil is divided into a front and a rear part, wherein the rear part of the target airfoil is the first part of the target airfoil.
[0038] It should be noted that the chord-wise position refers to the position along the chord line of the airfoil (the straight line from the leading edge to the trailing edge of the airfoil).
[0039] It should be noted that based on the target weight coefficient and the tail coordinate points of the scaled standard circular airfoil and the target airfoil, the coordinate set of the tail of the optimized target airfoil is calculated through the intelligent optimization algorithm. This step comprehensively considers the aerodynamic performance and structural strength of the airfoil, and strives to find the optimal tail shape of the airfoil.
[0040] Step S210: Optimizing a first portion of the target airfoil based on the target coordinate set.
[0041] It should be noted that the tail of the target airfoil is structurally optimized according to the target coordinate set obtained after optimization. This optimization aims to improve the anti-buckling property of the tail of the airfoil, that is, to enhance its structural stability under the action of wind, while ensuring that the aerodynamic performance of the airfoil, such as the ratio of lift to drag, meets the design requirements.
[0042] It should be noted that the above steps can not only effectively improve the anti-buckling ability of the wind turbine blade airfoil, reduce the risk of blade breakage or damage under extreme wind conditions, but also ensure the high efficiency of the airfoil in aerodynamic performance. For large wind turbine blades above 100 meters, the results of airfoil optimization will significantly improve their safety and economy, enhance the overall performance of wind power generation systems, and reduce maintenance costs and potential environmental impacts. Through the optimization of intelligent algorithms, the shape of the tail of the airfoil can be more accurately controlled, and the optimal balance between structural stability and aerodynamic performance can be found, thereby designing wind turbine blades with better performance.
[0043] In the above steps, by determining the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil, the coordinates of the points in the area from the maximum thickness point of the airfoil to the trailing edge of the standard circular airfoil are scaled to obtain a first coordinate set, and then based on the target weight coefficient, the coordinates of the optimized points in the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil are determined according to the coordinates of the points in the same area of the first coordinate set and the target airfoil, thereby optimizing the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil. Since the scaling is performed in proportion to the maximum thickness of the target airfoil, the basic structure of the airfoil is guaranteed. Then, by selecting the target weight coefficient, the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil is optimized based on the target weight, so that the sum of the absolute values of the curvature of the suction surface and the pressure surface of the optimized target airfoil is greater than the preset threshold, thereby improving the anti-buckling property of the target airfoil, thereby solving the problem of poor anti-buckling property of the existing airfoil.
[0044] In an exemplary embodiment, scaling the coordinates of the points in the first portion of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set can be achieved by the following steps S11-S12:
[0045] Step S11: determining a ratio of the maximum thickness of the target airfoil to the maximum thickness of the standard circular airfoil to obtain a target ratio;
[0046] Optionally, the relative thickness of the target airfoil is 40%, that is, the maximum thickness of the target airfoil is 40% of its chord length, and the relative thickness of the standard circular airfoil is 1, then the target ratio is 0.4 (40% / 1=0.4).
[0047] It should be noted that the maximum thickness to chord length ratio of the standard circular airfoil is 1, while the thickness of the target airfoil may be different, so by determining this ratio, it can be ensured that the scaling of the standard circular airfoil can accurately match the shape requirements of the target airfoil while retaining the structural advantages of the tail of the standard circular airfoil.
[0048] Step S12: multiplying the ordinate of the coordinates of each point in the first part of the standard circular airfoil by the target ratio to obtain the first coordinate set.
[0049] Optionally, the calculated target ratio R is used to scale the ordinate of each point in the tail (first part) of the standard circular airfoil. The specific operation is to scale the ordinate y of each point c Multiply by the target ratio R to get the scaled coordinate y c *R. After such processing, the tail shape of the standard circular airfoil will be adjusted according to the thickness ratio of the target airfoil, and a first coordinate set including the coordinates of the points of the tail of the scaled standard circular airfoil is generated.
[0050] It should be noted that through the above steps, the tail shape can be adjusted to adapt to the thickness and aerodynamic performance requirements of the target airfoil while retaining the structural stability advantages of the standard circular airfoil. This processing method ensures the accuracy of the airfoil optimization process, so that the optimized airfoil not only meets the design requirements in terms of aerodynamic performance, but also has a stronger anti-buckling ability in structure, especially in application scenarios such as wind turbine blades that have high requirements for structural strength, which can significantly improve the safety and reliability of blades under high wind speed conditions.
[0051] In an exemplary embodiment, based on the target weight coefficient, obtaining the target coordinate set according to the first coordinate set and the second coordinate set can be achieved by the following steps: when the first coordinate set includes the coordinates of N points in the first part of the standard circular airfoil and the second coordinate set includes the coordinates of the corresponding N points in the first part of the target airfoil, the following steps are performed according to the i-th coordinate in the first coordinate set and the i-th coordinate corresponding to the second coordinate set to obtain the target coordinate set, wherein i is 1, 2, ..., N: the i-th coordinate in the first coordinate set is (x 1 ,y1 ), the i-th coordinate in the second coordinate set is (x 1 ,y 2 ), the i-th coordinate in the target coordinate set is (x 1 ,y 1 *(1-C)+y 2 *C), where C is the target weight coefficient.
[0052] Optionally, where y 1 and 2 The positive and negative attributes in the coordinate axes are the same. For example, if the i-th coordinate in the first coordinate set is (1, 2), then the i-th coordinate in the second coordinate set is (1, 1); if the i-th coordinate in the first coordinate set is (1, -2), then the i-th coordinate in the second coordinate set is (1, -1).
[0053] It should be noted that the i-th coordinate in the target coordinate set is (x 1 ,y 1 *(1-C)+y 2 *C), which means that for the i-th ordinate, it will move closer to the target airfoil at a ratio of C along the y-axis according to the value of the weight coefficient C, while maintaining the characteristics of the standard circular airfoil at a ratio of (1-C). 1 remains unchanged, since the optimization is mainly concerned with the effect of the ordinate on the anti-buckling performance of the airfoil.
[0054] It should be noted that this method can finely control the fusion of the standard circular airfoil and the tail shape of the target airfoil to achieve the best balance between structural stability and aerodynamic efficiency. The selection of the target weight coefficient C is the core, which determines the shape characteristics of the final airfoil tail, that is, the comprehensive performance of structural strength and aerodynamic performance.
[0055] It should be noted that the tail design of the standard circular airfoil tends to provide better structural stability. By adjusting the C value, the comprehensive curvature difference of the tail of the airfoil can be increased, thereby effectively improving the anti-buckling ability and reducing the risk of blade breakage due to insufficient structural stability.
[0056] It should be noted that the target airfoil usually has specific requirements for aerodynamic performance. The adjustment of the C value ensures that the optimized airfoil is structurally optimized while maintaining or improving aerodynamic efficiency. Through intelligent algorithms, the optimal C value can be found so that key aerodynamic parameters such as the lift-to-drag ratio of the airfoil under wind force meet the design goals.
[0057] In an exemplary embodiment, the method further comprises the following steps S21-S22:
[0058] Step S21: determining a plurality of weight values satisfying preset conditions from a preset range, wherein the preset conditions include: the target airfoil after optimization based on the weight coefficients satisfies preset aerodynamic performance;
[0059] Optionally, a set of weight values that can make the target airfoil optimized based on the weight coefficient meet the preset aerodynamic performance requirements is screened out from a preset weight value range (e.g., between 0 and 1). The preset aerodynamic performance can be a target lift-to-drag ratio, a maximum lift coefficient, or other performance indicators related to aerodynamic efficiency. Through this step, it can be ensured that the optimized airfoil meets the design requirements in terms of aerodynamic performance.
[0060] Optionally, with the target aerodynamic performance of the blade as a constraint, a rapid airfoil analysis (Rapid Foil, referred to as RFOIL) or an eXtensible airfoil analysis (eXtensible FOIL, referred to as XFOIL) is used to calculate the aerodynamic performance of the airfoil design point.
[0061] Step S22: determining a first weight coefficient among the plurality of weight values as the target weight coefficient, wherein a target curvature determined based on the first weight coefficient is greater than a target curvature determined based on weight coefficients among the plurality of weight values other than the first weight coefficient;
[0062] Wherein, the target curvature is equal to the sum of the absolute value of the average curvature of the pressure surface and the absolute value of the average curvature of the suction surface of the first part of the target airfoil optimized based on the weight coefficient;
[0063] Among them, optimizing the target airfoil based on the weight coefficient includes: obtaining a reference coordinate set according to the first coordinate set and the second coordinate set based on the weight coefficient; and optimizing the first part of the target airfoil according to the reference coordinate set.
[0064] Optionally, a first weight coefficient is determined as a target weight coefficient from a plurality of weight values that satisfy a preset condition. The selection criterion is that the sum of the absolute values of the average curvatures of the pressure surface and the suction surface of the tail (first part) of the airfoil optimized based on this weight coefficient (target curvature) is the largest. This means that, through the intelligent optimization algorithm, a target weight value can be found so that the airfoil reaches the optimal state in terms of structural stability (anti-buckling performance) without sacrificing its aerodynamic performance.
[0065] It should be noted that, through steps S21 and S22, an intelligent algorithm can be used to automatically screen and determine the optimal weight value. The preset range and screening conditions of the weight value ensure the systematic and scientific nature of the airfoil optimization process, and avoid the uncertainty caused by blind adjustment. The introduction of this method makes the airfoil design process more automated and intelligent, reduces labor costs, shortens the design cycle, and can quickly iterate and use intelligent algorithms to find the optimal airfoil design, which has a significant effect on accelerating product development in the wind power industry and enhancing market competitiveness. In addition, through the dynamic adjustment of the weight value, the shape of the tail of the airfoil can be finely controlled to ensure that the structure and aerodynamic performance of the airfoil in a specific area are optimal, which is crucial to improving the safety and reliability of wind turbine blades under extreme wind conditions.
[0066] In an exemplary embodiment, the method further comprises the following steps: determining the average curvature of the pressure surface of the first portion of the target airfoil by following the steps S31-S32:
[0067] Step S31: determining an expression of the pressure surface of the first part of the target airfoil;
[0068] Optionally, a polynomial fitting is used to obtain an expression of the target airfoil on the pressure surface.
[0069] Step S32: determining the curvature of a plurality of points of the first portion of the target airfoil based on the expression of the pressure surface, and determining an average value of the curvatures of the plurality of points as an average curvature of the pressure surface of the first portion of the target airfoil.
[0070] Optionally, 10 points are selected in the first part of the target airfoil (the second half of the airfoil), whose horizontal coordinate is the smallest x i , the maximum is 1; using the expression of the target airfoil on the pressure surface, the sum of the curvatures at the 10 points is calculated respectively, and the average curvature of the 10 points is calculated to obtain the average curvature of the pressure surface of the first part of the target airfoil.
[0071] It should be noted that selecting multiple points for calculation can more comprehensively reflect the curvature distribution of the pressure surface in the tail region. The purpose of averaging is to obtain a comprehensive indicator that reflects the average curvature state of the pressure surface in the entire tail region.
[0072] It should be noted that in applications such as wind turbine blades, airfoil design must consider both structural stability and aerodynamic efficiency. By calculating the average curvature, we can more clearly understand the structural characteristics of the tail of the airfoil, so that we can take into account both structural optimization and aerodynamic performance optimization during design, promote the close integration of structural design and aerodynamic design, and improve the overall design level.
[0073] In an exemplary embodiment, the method further comprises the following steps: determining the average curvature of the suction surface of the first portion of the target airfoil by following the steps S41-S42:
[0074] Step S41: determining an expression of the suction surface of the first part of the target airfoil;
[0075] Optionally, a polynomial fitting is used to obtain an expression of the target airfoil on the suction surface.
[0076] Step S42: determining the curvature of a plurality of points of the first portion of the target airfoil based on the expression of the suction surface, and determining an average value of the curvatures of the plurality of points as an average curvature of the suction surface of the first portion of the target airfoil.
[0077] Optionally, 10 points are selected in the first part of the target airfoil (the rear half of the airfoil), whose horizontal coordinates are as small as xi and as large as 1; the expression of the target airfoil on the suction surface is used to calculate the sum of the curvatures at the 10 points respectively, and the average curvature of the 10 points is calculated to obtain the average curvature of the suction surface of the first part of the target airfoil.
[0078] It should be noted that calculating the curvature of multiple points and averaging them can comprehensively reflect the curvature distribution of the suction surface area and provide a quantitative index to evaluate the anti-buckling performance of the target airfoil.
[0079] It should be noted that the curvature of the suction surface also affects the anti-buckling performance of the airfoil. By calculating the average curvature, the geometric characteristics of the suction surface in the tail area of the airfoil can be comprehensively evaluated, providing key data for optimizing the anti-buckling performance.
[0080] It should be noted that the curvatures of the pressure and suction surfaces need to be balanced to achieve optimal structural stability and aerodynamic performance. The mean curvature calculation provides quantitative indicators of not only the pressure surface, but also the suction surface. These two indicators can be considered comprehensively to find the optimal balance point of the airfoil design.
[0081] It should be noted that the mean curvature, as a key parameter in airfoil design, can support the operation of the intelligent optimization algorithm. The optimization algorithm will use the mean curvature data of the pressure and suction surfaces, combined with other design constraints, to automatically adjust the airfoil design, find the optimal solution for structural stability and aerodynamic performance, and improve the automation and efficiency of the design.
[0082] It should be noted that, through the above steps S41 and S42, the average curvature of the suction surface in the tail area of the target airfoil can be accurately calculated, providing key structural parameters for the airfoil optimization design. This method not only helps to improve the anti-buckling performance of the airfoil and ensure its structural safety under extreme conditions, but also ensures the balance between the structure and aerodynamic performance of the airfoil design, promoting the development of wind power technology and the widespread application of clean energy.
[0083] Obviously, the above-described embodiments are only embodiments of a part of the present invention, rather than all embodiments. In order to better understand the above method, the above process is described below in conjunction with embodiments, but it is not intended to limit the technical solutions of the embodiments of the present invention, specifically:
[0084] 1. Based on the existing blade root airfoil (i.e. the target airfoil mentioned above), such as a 40% thickness standard airfoil, the airfoil coordinates are (x 40i ,y 40i ), and obtain the chordal position x of its maximum thickness i , and divide the airfoil into two parts, front and rear;
[0085] 2. The optimization design is carried out with the goal of maximizing the average curvature of the pressure surface and suction surface of the rear half of the airfoil, specifically:
[0086] (1) Select 10 points P in the rear half of the airfoil i , whose minimum horizontal coordinate is x i , the maximum value is 1;
[0087] (2) Use polynomial fitting to obtain the expression of the airfoil on the pressure surface, and calculate the curvature K at 10 points respectively i_P , the curvature K of the 10 points i_P Find the average value to get K a_P ;
[0088] (3) The expression of the airfoil on the suction surface is obtained by polynomial fitting, and its curvature K at 10 points is calculated respectively. i_S , the curvature K of the 10 points i_S Find the average value to get K a_S ;
[0089] (4) K a_P -K a_S represents the integrated curvature of the rear half of the airfoil;
[0090] 3. Select the standard circle as the reference geometric shape, with x i = 0.5 as the dividing line, dividing the standard circle into two parts, front and back, and selecting the coordinate point of the back half (x ci ,y ci), and according to the maximum thickness ratio R of the designed airfoil (relative thickness 40%) and the standard circular shape, the standard circular shape coordinates are scaled to obtain the new coordinates (x ci ,y ci *R);
[0091] 4. Take the weighting coefficient C 1 , get the geometric coordinates of the second half of the designed airfoil (x 40i ,y 40i *C 1 +y ci *R*(1-C 1 ))
[0092] 5. Taking the target aerodynamic performance of the blade as the constraint, use RFOIL or XFOIL to calculate the aerodynamic performance of the airfoil design point.
[0093] 6. With the weighted coefficient as the independent variable, the maximum average curvature of the pressure surface and suction surface of the rear half of the airfoil as the goal, and the target aerodynamic performance of the blade as the constraint, an intelligent optimization algorithm is used to establish an optimization design method for the airfoil.
[0094] Through the description of the above implementation methods, those skilled in the art can clearly understand that the method according to the above embodiment can be implemented by means of software plus a necessary general hardware platform, and of course by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present application, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes a number of instructions for a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods of each embodiment of the present application.
[0095] In this embodiment, an airfoil optimization device is also provided, which is used to implement the above-mentioned embodiments and preferred embodiments, and the descriptions that have been made will not be repeated. As used below, the term "module" can implement a combination of software and / or hardware of a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.
[0096] Figure 3 : is a structural block diagram of an airfoil optimization device according to an embodiment of the present application, the device comprising:
[0097] A first determination module 302 is used to determine a target airfoil and a standard circular airfoil, wherein a ratio of a maximum thickness to a chord length of the standard circular airfoil is equal to one;
[0098] A scaling module 304 is used to scale the coordinates of the points in the first part of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the scaled coordinates of the points in the first part of the standard circular airfoil, and the first part is an area from the maximum thickness point of the airfoil to the trailing edge of the airfoil;
[0099] A second determination module 306 is used to determine a target weight coefficient;
[0100] A third determination module 308 is configured to obtain a target coordinate set based on the target weight coefficient and according to the first coordinate set and the second coordinate set, wherein the second coordinate set includes coordinates of points in the first part of the target airfoil, and the target coordinate set includes coordinates of points in the first part of the optimized target airfoil;
[0101] The optimization module 310 is configured to optimize the first portion of the target airfoil based on the target coordinate set.
[0102] The above device, by determining the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil, scales the coordinates of the points in the area from the maximum thickness point of the airfoil to the trailing edge of the standard circular airfoil, obtains a first coordinate set, and then based on the target weight coefficient, determines the coordinates of the optimized points in the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil according to the coordinates of the points in the same area of the first coordinate set and the target airfoil, thereby optimizing the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil. Since the scaling is performed in proportion to the maximum thickness of the target airfoil, the basic structure of the airfoil is guaranteed. Then, by selecting the target weight coefficient, the area from the maximum thickness point of the airfoil to the trailing edge of the target airfoil is optimized based on the target weight, so that the sum of the absolute values of the curvature of the suction surface and the pressure surface of the optimized target airfoil is greater than the preset threshold, thereby improving the anti-buckling property of the target airfoil, thereby solving the problem of poor anti-buckling property of the existing airfoil.
[0103] In an exemplary embodiment, the scaling module 304 is further used to determine the ratio of the maximum thickness of the target airfoil to the maximum thickness of the standard circular airfoil to obtain a target ratio; and multiply the ordinate of the coordinates of each point in the first part of the standard circular airfoil by the target ratio to obtain the first coordinate set.
[0104] In an exemplary embodiment, the third determination module 308 is further configured to, when the first coordinate set includes coordinates of N points in the first portion of the standard circular airfoil and the second coordinate set includes coordinates of corresponding N points in the first portion of the target airfoil, perform processing according to the i-th coordinate in the first coordinate set and the i-th coordinate corresponding to the second coordinate set in the following manner to obtain the target coordinate set, wherein i is 1, 2, ..., N: the i-th coordinate in the first coordinate set is (x 1 ,y 1 ), the i-th coordinate in the second coordinate set is (x 1 ,y 2 ), the i-th coordinate in the target coordinate set is (x 1 ,y 1 *(1-C)+y 2 *C), where C is the target weight coefficient.
[0105] In an exemplary embodiment, the second determination module 306 is also used to determine multiple weight values that meet preset conditions from a preset range, wherein the preset conditions include: the target airfoil after optimization based on the weight coefficient meets preset aerodynamic performance; the first weight coefficient among the multiple weight values is determined as the target weight coefficient, wherein the target curvature determined based on the first weight coefficient is greater than the target curvature determined based on the weight coefficients other than the first weight coefficient among the multiple weight values; wherein the target curvature is equal to the sum of the absolute value of the average curvature of the pressure surface and the absolute value of the average curvature of the suction surface of the first part of the target airfoil after optimization based on the weight coefficient; wherein optimizing the target airfoil based on the weight coefficient includes: based on the weight coefficient, obtaining a reference coordinate set according to the first coordinate set and the second coordinate set; and optimizing the first part of the target airfoil according to the reference coordinate set.
[0106] In an exemplary embodiment, the second determination module 306 is also used to determine the average curvature of the pressure surface of the first part of the target airfoil in the following manner: determining an expression of the pressure surface of the first part of the target airfoil; determining the curvature of multiple points of the first part of the target airfoil based on the expression of the pressure surface, and determining the average value of the curvatures of the multiple points as the average curvature of the pressure surface of the first part of the target airfoil.
[0107] In an exemplary embodiment, the second determination module 306 is further used to determine the average curvature of the suction surface of the first part of the target airfoil in the following manner: determining an expression of the suction surface of the first part of the target airfoil; determining the curvature of multiple points of the first part of the target airfoil based on the expression of the suction surface, and determining the average value of the curvatures of the multiple points as the average curvature of the suction surface of the first part of the target airfoil.
[0108] An embodiment of the present application further provides a computer-readable storage medium, in which a computer program is stored, wherein the computer program is configured to execute the steps of any of the above method embodiments when running.
[0109] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:
[0110] S1, determining a target airfoil and a standard circular airfoil, wherein a ratio of a maximum thickness to a chord length of the standard circular airfoil is equal to one;
[0111] S2, scaling the coordinates of the points in the first part of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the scaled coordinates of the points in the first part of the standard circular airfoil, and the first part is an area from the maximum thickness point of the airfoil to the trailing edge of the airfoil;
[0112] S3, determine the target weight coefficient;
[0113] S4, based on the target weight coefficient, obtaining a target coordinate set according to the first coordinate set and the second coordinate set, wherein the second coordinate set includes coordinates of points in the first part of the target airfoil, and the target coordinate set includes coordinates of points in the first part of the optimized target airfoil;
[0114] S5, optimizing a first portion of the target airfoil based on the target coordinate set.
[0115] In an exemplary embodiment, the computer-readable storage medium may include, but is not limited to, various media that can store computer programs, such as a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk.
[0116] For specific examples in this embodiment, reference may be made to the examples described in the above embodiments and exemplary implementation modes, and this embodiment will not be described in detail herein.
[0117] An embodiment of the present application further provides a computer program product, including a computer program, and when the computer program is executed by a processor, the steps in any one of the above method embodiments are performed.
[0118] An embodiment of the present application further provides an electronic device, including a memory and a processor, wherein a computer program is stored in the memory, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.
[0119] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:
[0120] S1, determining a target airfoil and a standard circular airfoil, wherein a ratio of a maximum thickness to a chord length of the standard circular airfoil is equal to one;
[0121] S2, scaling the coordinates of the points in the first part of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the scaled coordinates of the points in the first part of the standard circular airfoil, and the first part is an area from the maximum thickness point of the airfoil to the trailing edge of the airfoil;
[0122] S3, determine the target weight coefficient;
[0123] S4, based on the target weight coefficient, obtaining a target coordinate set according to the first coordinate set and the second coordinate set, wherein the second coordinate set includes coordinates of points in the first part of the target airfoil, and the target coordinate set includes coordinates of points in the first part of the optimized target airfoil;
[0124] S5, optimizing a first portion of the target airfoil based on the target coordinate set.
[0125] In an exemplary embodiment, the electronic device may further include a transmission device and an input / output device, wherein the transmission device is connected to the processor, and the input / output device is connected to the processor.
[0126] For specific examples in this embodiment, reference may be made to the examples described in the above embodiments and exemplary implementation modes, and this embodiment will not be described in detail herein.
[0127] Obviously, those skilled in the art should understand that the above modules or steps of the present application can be implemented by a general computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, they can be implemented by a program code executable by a computing device, so that they can be stored in a storage device and executed by the computing device, and in some cases, the steps shown or described can be executed in a different order from that herein, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. Thus, the present application is not limited to any specific combination of hardware and software.
[0128] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.
Claims
1. A method for airfoil optimization, characterized in that: include: determining a target airfoil and a standard circular airfoil, wherein a ratio of a maximum thickness to a chord length of the standard circular airfoil is equal to one; and Scaling the coordinates of the points in the first part of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the scaled coordinates of the points in the first part of the standard circular airfoil, and the first part is an area from the maximum thickness point of the airfoil to the trailing edge of the airfoil; Determine the target weight coefficient; Based on the target weight coefficient, obtaining a target coordinate set according to the first coordinate set and the second coordinate set, wherein the second coordinate set includes coordinates of points in the first part of the target airfoil, and the target coordinate set includes coordinates of points in the first part of the optimized target airfoil; A first portion of the target airfoil is optimized based on the target coordinate set.
2. The method according to claim 1, characterized in that The coordinates of the points in the first part of the standard circular airfoil are scaled according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, including: Determining a ratio of a maximum thickness of the target airfoil to a maximum thickness of the standard circular airfoil to obtain a target ratio; The first set of coordinates is obtained by multiplying the ordinate of the coordinates of each point in the first portion of the standard circular airfoil by the target ratio.
3. The method according to claim 1, characterized in that Based on the target weight coefficient, obtaining a target coordinate set according to the first coordinate set and the second coordinate set includes: In the case where the first coordinate set includes coordinates of N points in the first part of the standard circular airfoil and the second coordinate set includes coordinates of corresponding N points in the first part of the target airfoil, the target coordinate set is obtained by processing according to the i-th coordinate in the first coordinate set and the i-th coordinate corresponding to the second coordinate set in the following manner, where i is 1, 2, ..., N: When the i-th coordinate in the first coordinate set is (x1, y1) and the i-th coordinate in the second coordinate set is (x1, y2), the i-th coordinate in the target coordinate set is (x1, y1*(1-C)+y2*C), where C is the target weight coefficient.
4. The method according to claim 1, characterized in that: The method further comprises: Determining a plurality of weight values satisfying preset conditions from a preset range, wherein the preset conditions include: the target airfoil after optimization based on the weight coefficients satisfies preset aerodynamic performance; Determining a first weight coefficient among the plurality of weight values as the target weight coefficient, wherein a target curvature determined based on the first weight coefficient is greater than a target curvature determined based on weight coefficients among the plurality of weight values other than the first weight coefficient; The target curvature is equal to the sum of the absolute value of the average curvature of the pressure surface and the absolute value of the average curvature of the suction surface of the first part of the target airfoil optimized based on the weight coefficient; Among them, optimizing the target airfoil based on the weight coefficient includes: obtaining a reference coordinate set according to the first coordinate set and the second coordinate set based on the weight coefficient; and optimizing the first part of the target airfoil according to the reference coordinate set.
5. The method according to claim 4, characterized in that The method further comprises: The average curvature of the pressure surface of the first portion of the target airfoil is determined by: determining an expression for a pressure surface of a first portion of the target airfoil; The curvatures of a plurality of points of the first portion of the target airfoil are determined based on the expression of the pressure surface, and an average value of the curvatures of the plurality of points is determined as an average curvature of the pressure surface of the first portion of the target airfoil.
6. The method according to claim 4, characterized in that The method further comprises: The average curvature of the suction surface of the first portion of the target airfoil is determined by: determining an expression for a suction surface of a first portion of the target airfoil; The curvatures of a plurality of points of the first portion of the target airfoil are determined based on the expression of the suction surface, and an average value of the curvatures of the plurality of points is determined as an average curvature of the suction surface of the first portion of the target airfoil.
7. An airfoil optimization device, characterized in that: include: A first determination module is used to determine a target airfoil and a standard circular airfoil, wherein a ratio of a maximum thickness to a chord length of the standard circular airfoil is equal to one; a scaling module, configured to scale the coordinates of points in a first portion of the standard circular airfoil according to the maximum thickness of the target airfoil and the maximum thickness of the standard circular airfoil to obtain a first coordinate set, wherein the first coordinate set includes the scaled coordinates of the points in the first portion of the standard circular airfoil, the first portion being an area from the maximum thickness point of the airfoil to the trailing edge of the airfoil; A second determination module is used to determine a target weight coefficient; a third determination module, configured to obtain a target coordinate set according to the first coordinate set and the second coordinate set based on the target weight coefficient, wherein the second coordinate set includes coordinates of points in the first part of the target airfoil, and the target coordinate set includes coordinates of points in the first part of the optimized target airfoil; An optimization module is used to optimize a first portion of the target airfoil based on the target coordinate set.
8. A computer-readable storage medium, characterized in that: The computer-readable storage medium includes a stored program, wherein the program executes the method according to any one of claims 1 to 6 when executed.
9. An electronic device comprising a memory and a processor, characterized in that: A computer program is stored in the memory, and the processor is configured to execute the method according to any one of claims 1 to 6 through the computer program.
10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the method according to any one of claims 1 to 6 is implemented.
Citation Information
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Optimization design method for airfoil profile of aircraft
CN120930551A