Blade optimization method and device, storage medium, electronic device and computer program product

Abstract

The invention discloses a blade optimization method and device, a storage medium, an electronic device and a computer program product, and relates to the field of blades, and the blade optimization method comprises the steps that the airfoil profile distribution condition of a target blade is determined, the airfoil profile distribution condition is used for indicating the distribution condition of N airfoil profiles in the target blade and the relative thickness of each airfoil profile in the N airfoil profiles, and N is an integer greater than or equal to 2; according to the airfoil profile distribution condition of the target blade, the optimal operation lift-drag ratio of each airfoil profile in the N airfoil profiles is determined, and the optimal operation lift-drag ratio is the operation lift-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil profile; and optimizing the airfoil profile of the target blade according to the optimal operation lift-drag ratio and the maximum operation lift-drag ratio of each airfoil profile in the N airfoil profiles. By the adoption of the technical scheme, the problem that the wing section of the blade cannot be optimized well is solved.

Description

Technical Field

[0001] The present application relates to the field of blades, and more specifically, to a blade optimization method and device, a storage medium, an electronic device, and a computer program product. Background Art

[0002] The weight of large wind turbine blades above 100 meters is tens of tons, which directly affects the cost of wind turbine blades. At the same time, it affects the blade load, and then affects the weight and reliability of other components of the unit. In order to reduce the weight of wind turbine blades, it is necessary to increase the thickness of the blades as much as possible to improve their structural efficiency. However, the increase in blade thickness will lead to a decrease in the aerodynamic efficiency of the blades. Therefore, how to better determine the airfoil distribution is more critical, but there is currently no good method to optimize the airfoil.

[0003] With regard to the problem in the related art that the airfoil of the blade cannot be optimized well, no effective solution has been proposed yet.

[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 a blade optimization method and device, a storage medium, an electronic device, and a computer program product to at least solve the problem of being unable to optimize the airfoil of the blade.

[0006] According to one aspect of an embodiment of the present application, a blade optimization method is provided, comprising: determining an airfoil distribution of a target blade, wherein the airfoil distribution is used to indicate the distribution of N types of airfoils in the target blade and the relative thickness of each of the N airfoils, and N is an integer greater than or equal to 2; determining an optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is an operating lift-to-drag ratio corresponding to a maximum wind power conversion efficiency of the airfoil; and optimizing the airfoil of the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

[0007] In an exemplary embodiment, the airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils, including: when there are a first airfoil and a second airfoil among the N airfoils, and the relative thickness of the first airfoil is greater than the relative thickness of the second airfoil, determining whether the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil; when the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil, replacing the second airfoil in the target blade with the first airfoil.

[0008] In an exemplary embodiment, after replacing the second airfoil in the target blade with the first airfoil, the method further includes: replacing the target airfoil in the target blade with the first airfoil, wherein the target airfoil is an airfoil in the target blade whose relative thickness is less than the relative thickness of the second airfoil.

[0009] In an exemplary embodiment, determining the airfoil distribution of a target blade includes: obtaining a power generation requirement and a load requirement of the target blade; and determining the airfoil distribution of the target blade that meets the power generation requirement and the load requirement.

[0010] In an exemplary embodiment, the airfoil distribution of the target blade that meets the power generation requirement and the load requirement is determined, and the method further includes: obtaining an airfoil set, wherein the airfoil set has airfoils with a plurality of different relative thicknesses; based on the airfoil set, determining the airfoil distribution of the target blade that meets the power generation requirement and the load requirement, wherein the airfoils in the airfoil distribution are the airfoils in the airfoil set.

[0011] In an exemplary embodiment, determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade includes: determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade through a wind turbine simulation tool.

[0012] According to another aspect of an embodiment of the present application, a blade optimization device is also provided, including: a first determination module, used to determine the airfoil distribution of a target blade, wherein the airfoil distribution is used to indicate the distribution of N types of airfoils in the target blade and the relative thickness of each of the N airfoils, and N is an integer greater than or equal to 2; a second determination module, used to determine the optimal operating lift-to-drag ratio of each of the N airfoils based on the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil; and an optimization module, used to optimize the airfoil of the target blade based on the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

[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 blade optimization method when running.

[0014] According to another aspect of an embodiment of the present application, there is further provided an electronic device, comprising a memory and a processor, wherein a computer program is stored in the memory, wherein the processor is configured to execute the above-mentioned blade 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 blade optimization method is implemented when the computer program is executed by a processor.

[0016] In the present application, the optimal operating lift-to-drag ratio of each airfoil is determined by determining the distribution of multiple airfoils of the target blade and the relative thickness of each airfoil, and then the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each airfoil. Since the airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of the airfoil, the problem of not being able to optimize the airfoil of the blade is solved. 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 a blade optimization method according to an embodiment of the present application;

[0020] Figure 2 is a flow chart of a blade optimization method according to an embodiment of the present application;

[0021] Figure 3 It is a structural block diagram of a blade 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 solution of the present application, the technical solution 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 the present 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 a blade 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 only for illustration and does not limit the structure of the mobile terminal. Figure 1 More or fewer components as shown, or with Figure 1 Different configurations are 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 method for detecting pneumatic imbalance 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 can 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 combinations 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 problem, this embodiment provides a blade optimization method, including but not limited to being applied to the above mobile terminal. Figure 2 is a flow chart of a blade optimization method according to an embodiment of the present application. Figure 2 As shown, the process includes the following steps S202-S206:

[0028] Step S202: determining the airfoil distribution of the target blade, wherein the airfoil distribution is used to indicate the distribution of N airfoils in the target blade and the relative thickness of each of the N airfoils, where N is an integer greater than or equal to 2;

[0029] Optionally, the blade optimization method of the present application begins with determining the airfoil distribution of the target blade. This step requires clarifying the N airfoil designs used at different positions on the blade, as well as the specific relative thickness of each airfoil. N is an integer greater than or equal to 2, which means that at least two airfoils of different thicknesses are required for comparison and optimization.

[0030] It should be noted that the work in this stage provides basic data for subsequent optimization strategies, ensuring the targetedness and comprehensiveness of the optimization process.

[0031] Step S204: determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil;

[0032] Optionally, after determining the airfoil distribution, the optimal operating lift-to-drag ratio of each airfoil is calculated. The optimal operating lift-to-drag ratio refers to the ratio of lift to drag when the blade can convert wind energy into electrical energy in the most efficient manner under a specific airfoil design.

[0033] It should be noted that the optimal operating lift-to-drag ratio is a key indicator for evaluating the aerodynamic performance of airfoil design, as it is directly related to the power generation efficiency of the blade. By using professional wind power software (such as Bladed) for simulation analysis, the lift-to-drag ratio data of each airfoil under optimal operating conditions can be obtained. The purpose of this step is to accurately identify which airfoils perform well in aerodynamic efficiency through data analysis, providing a scientific basis for subsequent optimization decisions.

[0034] Step S206: optimizing the airfoil of the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

[0035] Optionally, by comparing the lift-to-drag ratios of different airfoils, relatively thin airfoils are gradually replaced with relatively thick airfoils, provided that the lift-to-drag ratio of the thick airfoil is at least not inferior to the optimal lift-to-drag ratio of the thin airfoil.

[0036] It should be noted that by optimizing the airfoil of the target blade, the structure of the blade can be optimized, the material demand and loss can be reduced, and thus the weight of the blade can be reduced.

[0037] It should be noted that this replacement strategy can effectively improve the structural efficiency of the blade without sacrificing the aerodynamic efficiency of the blade, that is, while ensuring that the blade can efficiently capture wind energy, increase the thickness of the blade to enhance its structural strength, thereby reducing the weight and material cost of the blade. In this way, the present application solves the problem of decreased aerodynamic efficiency and increased load that may be caused by increasing the thickness of the blade, and achieves a balanced optimization of the blade design in terms of structure and aerodynamic performance.

[0038] In the above steps, the optimal operating lift-to-drag ratio of each airfoil is determined by determining the distribution of multiple airfoils of the target blade and the relative thickness of each airfoil, and then the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each airfoil. Since the airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of the airfoil, the problem of not being able to optimize the airfoil of the blade is solved.

[0039] In an exemplary embodiment, the airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils, which can be achieved by the following steps S11-S12:

[0040] Step S11: when there are a first airfoil and a second airfoil in the N airfoils, and the relative thickness of the first airfoil is greater than the relative thickness of the second airfoil, determining whether the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil;

[0041] It should be noted that the core of this comparison is to determine whether the maximum operating lift-to-drag ratio of the first airfoil is at least equal to the optimal operating lift-to-drag ratio of the second airfoil. The maximum operating lift-to-drag ratio reflects the aerodynamic efficiency of the airfoil at the maximum load-bearing capacity, while the optimal operating lift-to-drag ratio is the performance under the best wind energy conversion efficiency. If the maximum operating lift-to-drag ratio of the first airfoil can reach or exceed the optimal operating lift-to-drag ratio of the second airfoil, it means that even under the most extreme operating conditions, the aerodynamic performance of the thick airfoil is at least not inferior to the performance of the thin airfoil under optimal conditions.

[0042] Step S12: when the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil, replacing the second airfoil in the target blade with the first airfoil.

[0043] Optionally, based on the comparison result of step S11, if the maximum operating lift-to-drag ratio of the first airfoil (thick airfoil) is indeed greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil (thin airfoil), then the next step is to replace all sections of the target blade using the second airfoil with the first airfoil.

[0044] It should be noted that this replacement can not only improve the structural efficiency of the blade, that is, enhance its strength and reduce its weight, but also ensure that the aerodynamic efficiency of the blade will not decrease, and can even be improved under certain conditions. This strategy cleverly solves the contradiction between increasing the thickness of the blade and maintaining the aerodynamic efficiency. By replacing the airfoil, the blade is optimized in both structural strength and aerodynamic performance.

[0045] Optionally, by comparing the optimal operating lift-to-drag ratio of a target blade airfoil with a relative thickness of 12% and the maximum operating lift-to-drag ratio of a target blade airfoil with a relative thickness of 18%, if the maximum lift-to-drag ratio of the target blade airfoil with a relative thickness of 18% is greater than or equal to the optimal operating lift-to-drag ratio of the target blade airfoil with a relative thickness of 12%, all sections with a relative thickness of 12% are replaced with target blade airfoils with a relative thickness of 18%; similarly, by comparing the optimal operating lift-to-drag ratio of the target blade airfoil with a relative thickness of 18% and the maximum lift-to-drag ratio of a target blade airfoil with a relative thickness of 21%, if the maximum lift-to-drag ratio of the target blade airfoil with a relative thickness of 21% is greater than or equal to the optimal operating lift-to-drag ratio of the target blade airfoil with a relative thickness of 18%, all sections with a relative thickness of 18% are replaced with target blade airfoils with a relative thickness of 21%.

[0046] It should be noted that by accurately comparing the lift-to-drag performance of airfoils of different relative thicknesses, a scientific upgrade of blade design is achieved, ensuring that while increasing the thickness of the blade to enhance structural efficiency, aerodynamic efficiency is not sacrificed. By applying thick airfoils whose aerodynamic performance is not inferior to that of thin airfoils to blade design, this application effectively reduces the weight and cost of the blades, improves the load-bearing capacity of the blades, and thereby improves the overall operating efficiency and economy of the wind turbine. This method breaks through the empirical limitations of traditional design and provides a new, more scientific and efficient optimization path for the design of wind turbine blades.

[0047] In an exemplary embodiment, after replacing the second airfoil in the target blade with the first airfoil, the method further includes the following steps: replacing the target airfoil in the target blade with the first airfoil, wherein the target airfoil is an airfoil in the target blade whose relative thickness is less than the relative thickness of the second airfoil.

[0048] Alternatively, if the first airfoil (thick airfoil) not only exhibits superior aerodynamic performance in comparison with the second airfoil, but also theoretically or through simulation analysis, its maximum operating lift-to-drag ratio is at least equal to the optimal operating lift-to-drag ratio of the thinner airfoil (target airfoil) in the target blade, then replacing the target airfoil with the first airfoil can also improve the structural efficiency without reducing the aerodynamic efficiency. This iterative replacement process starts with the thinner airfoil and gradually advances to the thinner airfoil until all airfoils that meet the conditions are replaced.

[0049] Optionally, the optimal operating lift-to-drag ratio of a target blade airfoil with a relative thickness of 12% and the maximum operating lift-to-drag ratio of a target blade airfoil with a relative thickness of 18% are compared; if the maximum lift-to-drag ratio of the target blade airfoil with a relative thickness of 18% is greater than or equal to the optimal operating lift-to-drag ratio of the target blade airfoil with a relative thickness of 12%, all sections with a relative thickness lower than 12% are replaced with target blade airfoils with a relative thickness of 18%; similarly, the optimal operating lift-to-drag ratio of the target blade airfoil with a relative thickness of 18% and the maximum lift-to-drag ratio of a target blade airfoil with a relative thickness of 21% are compared; if the maximum lift-to-drag ratio of the target blade airfoil with a relative thickness of 21% is greater than or equal to the optimal operating lift-to-drag ratio of the target blade airfoil with a relative thickness of 18%, all sections with a relative thickness lower than 18% are replaced with target blade airfoils with a relative thickness of 21%, and so on, until a target blade airfoil with a relative thickness of 40% (the largest relative thickness among the target blade airfoils), and finally an airfoil distribution with a greater relative thickness is obtained.

[0050] It should be noted that through this iterative optimization step, the structural performance of the blade is further strengthened, while the aerodynamic efficiency of the blade is maintained, allowing the use of relatively thicker airfoils in the blade design, which not only reduces the amount of material used and reduces the weight of the blade, but also enhances the strength and durability of the blade, thereby reducing maintenance costs. At the same time, by ensuring that the aerodynamic performance of the replacement airfoil is at least not inferior to that of the original airfoil, this method avoids the risk of aerodynamic performance degradation that may be caused by the pursuit of structural efficiency, and maintains the power generation efficiency of the blade and the overall operational reliability of the unit.

[0051] In an exemplary embodiment, determining the airfoil distribution of the target blade may be achieved by following the steps S21-S22:

[0052] Step S21: obtaining the power generation requirement and load requirement of the target blade;

[0053] It should be noted that the power generation requirement usually reflects the power output standard that the blade design should achieve within the expected wind speed range, while the load requirement focuses on the maximum stress and deformation limit that the blade is subjected to under extreme wind conditions, ensuring that the blade can maintain structural stability and safety under various operating environments. This link is crucial, defining the goals and boundary conditions of the optimized design, ensuring that the subsequent airfoil distribution design can meet the performance requirements and safety standards of the blade.

[0054] Step S22: Determine the airfoil distribution of the target blade that meets the power generation requirement and the load requirement.

[0055] Optionally, based on the power generation requirement and load requirement obtained in step S21, the airfoil distribution of the target blade that can meet both requirements is further determined. This process involves the detailed design and optimization of the blade airfoil, and by comprehensively considering the aerodynamic performance, structural strength, and performance of various airfoils under different operating conditions, a set of airfoil distribution solutions that can ensure sufficient power generation without exceeding the load limit is selected.

[0056] It should be noted that the above steps ensure that the blades can withstand the expected load while generating electricity efficiently, thereby improving the overall performance and reliability of the blades; through scientific optimization of the airfoil distribution, the weight of the blades is effectively reduced, reducing material costs and the difficulty of transportation and installation; the power generation and load requirements are integrated in the design stage, avoiding the uncertainty and waste of resources in subsequent design adjustments, and improving the design efficiency and the market competitiveness of the blades.

[0057] In an exemplary embodiment, determining the airfoil distribution of the target blade that meets the power generation requirement and the load requirement, the method further includes the following steps S31-S32:

[0058] Step S31: obtaining an airfoil set, wherein the airfoil set includes airfoils of various relative thicknesses;

[0059] Optionally, in the early stage of airfoil distribution design, an airfoil set is constructed, and the set includes a plurality of airfoils with different relative thicknesses.

[0060] It should be noted that the construction of the airfoil set provides a wealth of options for the subsequent airfoil selection, ensuring that the characteristics of various airfoils can be fully considered during the design process, so as to find the airfoil that best suits the target blade performance requirements.

[0061] Step S32: Based on the airfoil set, determine the airfoil distribution of the target blade that meets the power generation requirement and the load requirement, wherein the airfoils in the airfoil distribution are the airfoils in the airfoil set.

[0062] Optionally, based on the airfoil set constructed in step S31, start screening airfoil distribution solutions that can meet the power generation requirements and load requirements of the target blade. This process involves detailed aerodynamic performance and structural efficiency analysis of each airfoil in the airfoil set, and through comparison and optimization, determine the combined distribution of one or more airfoils in combination with the specific operating environment and expected performance indicators of the target blade, so that the blade meets or exceeds the design requirements in both power generation and load.

[0063] It should be noted that this step makes full use of the diversity of the airfoil set and combines it with the actual needs of the target blade to achieve a customized design of the airfoil distribution, ensuring the optimization and feasibility of the design results.

[0064] It should be noted that selecting the most suitable airfoil in the airfoil set achieves dual optimization of the blade's structural efficiency and aerodynamic efficiency, which not only enhances the blade's carrying capacity, but also maintains the blade's power generation efficiency, thereby improving the overall performance of the wind power generation system.

[0065] In an exemplary embodiment, determining the optimal operating lift-to-drag ratio of each of the N types of airfoils based on the airfoil distribution of the target blade can be achieved by the following steps: determining the optimal operating lift-to-drag ratio of each of the N types of airfoils based on the airfoil distribution of the target blade through a wind turbine simulation tool.

[0066] Optionally, first, based on the airfoil distribution of the target blade, a digital model of the blade is established in a wind turbine simulation tool (such as Bladed). This model contains all geometric parameters, material properties and expected operating environment conditions of the blade, such as wind speed range, wind direction change, etc., to ensure the accuracy and reliability of the simulation results; after the model is established, a series of operating conditions need to be set, including but not limited to parameters such as the rotation speed of the blade, wind field characteristics, and rated power of the generator. These conditions are set based on the power generation requirements and load requirements of the target blade to ensure that the simulation results can reflect the performance of the blade in actual operation; then, the wind turbine simulation tool is started for simulation analysis. The tool will simulate the operation of the blade under the set conditions, calculate the lift and drag of each airfoil at different angles of attack, and thus obtain the lift-to-drag ratio of each airfoil. By analyzing the data under a variety of operating conditions, the optimal operating lift-to-drag ratio of each airfoil can be found, that is, the lift-to-drag ratio with the smallest load on the blade while maintaining a high power generation efficiency.

[0067] It should be noted that the simulation tool can provide aerodynamic performance data of blades in complex operating environments, accurately evaluate the optimal operating lift-to-drag ratio of each airfoil, and provide a scientific basis for the replacement of airfoils. Moreover, iterative design using simulation tools can quickly locate optimization space and achieve a dual improvement in structural efficiency and aerodynamic efficiency by comparing the lift-to-drag ratios of different airfoils, thereby reducing the design cycle and improving design efficiency.

[0068] Obviously, the embodiments described above are only some embodiments of the present application, not all embodiments. In order to better understand the above method, the above process is described below in conjunction with the embodiments, but it is not intended to limit the technical solutions of the embodiments of the present application, specifically:

[0069] 1. Select a family of standard airfoils (the airfoils of the above-mentioned target blades), with thicknesses ranging from 40% to 12%, etc. The relative thicknesses of the standard airfoils are generally 40%, 35%, 30%, 25%, 21%, 18%, and 12%. Determine the maximum lift-to-drag ratio (the ratio of the lift coefficient (Cl) to the drag coefficient (CD), i.e. Cl / CD) and the corresponding angle of attack of each standard airfoil;

[0070] 2. Use traditional design methods to obtain an airfoil thickness distribution curve that meets the power generation and load requirements;

[0071] 3. Use bladed software to analyze the optimal operating angle of attack and optimal operating lift-to-drag ratio of each standard airfoil during optimal operation;

[0072] 4. Compare the optimal operating lift-to-drag ratio of the 12% standard airfoil with the maximum lift-to-drag ratio of the 18% relative thickness standard airfoil. If the maximum lift-to-drag ratio of the 18% relative thickness standard airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the 12% standard airfoil, replace all sections with a relative thickness lower than 18% with 18% thickness airfoils.

[0073] 5. Similarly, compare the optimal operating lift-drag ratio of the 18% standard airfoil with the maximum lift-drag ratio of the 21% relative thickness standard airfoil. If the maximum lift-drag ratio of the 21% relative thickness standard airfoil is greater than or equal to the optimal operating lift-drag ratio of the 18% standard airfoil, then replace all sections with a relative thickness lower than 21% with 21% thickness airfoils.

[0074] 6. This process is repeated in this way until the 40% thickness airfoil is reached, and finally an airfoil distribution with a greater relative thickness is obtained.

[0075] 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.

[0076] In this embodiment, a blade optimization device is also provided, which is used to implement the above-mentioned embodiments and preferred implementation modes, 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 for 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.

[0077] Figure 3 : is a structural block diagram of a blade optimization device according to an embodiment of the present application, the device comprising:

[0078] A first determination module 302 is used to determine the airfoil distribution of the target blade, wherein the airfoil distribution is used to indicate the distribution of N airfoils in the target blade and the relative thickness of each of the N airfoils, where N is an integer greater than or equal to 2;

[0079] A second determination module 304 is used to determine the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil;

[0080] The optimization module 306 is used to optimize the airfoil of the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

[0081] The above-mentioned device determines the optimal operating lift-to-drag ratio of each airfoil by determining the distribution of multiple airfoils of the target blade and the relative thickness of each airfoil, and then optimizes the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each airfoil. Since the airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of the airfoil, the problem of not being able to optimize the airfoil of the blade is solved.

[0082] In an exemplary embodiment, the optimization module 306 is further configured to determine whether the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil, when there are a first airfoil and a second airfoil in the N types of airfoils and the relative thickness of the first airfoil is greater than the relative thickness of the second airfoil; and replace the second airfoil in the target blade with the first airfoil, when the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil.

[0083] In an exemplary embodiment, the optimization module 306 is further configured to replace a target airfoil in the target blade with the first airfoil, wherein the target airfoil is an airfoil in the target blade whose relative thickness is smaller than that of the second airfoil.

[0084] In an exemplary embodiment, the first determination module 302 is further configured to obtain a power generation requirement and a load requirement of the target blade; and determine an airfoil distribution of the target blade that meets the power generation requirement and the load requirement.

[0085] In an exemplary embodiment, the first determination module 302 is also used to obtain an airfoil set, wherein the airfoil set has airfoils with a plurality of different relative thicknesses; based on the airfoil set, determine the airfoil distribution of the target blade that meets the power generation requirement and the load requirement, wherein the airfoil in the airfoil distribution is the airfoil in the airfoil set.

[0086] In an exemplary embodiment, the second determination module 304 is further configured to determine the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blades through a wind turbine simulation tool.

[0087] 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.

[0088] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:

[0089] S1, determining the airfoil distribution of the target blade, wherein the airfoil distribution is used to indicate the distribution of N airfoils in the target blade and the relative thickness of each of the N airfoils, where N is an integer greater than or equal to 2;

[0090] S2, determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil;

[0091] S3, optimizing the airfoil of the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

[0092] 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.

[0093] 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.

[0094] 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.

[0095] 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.

[0096] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:

[0097] S1, determining the airfoil distribution of the target blade, wherein the airfoil distribution is used to indicate the distribution of N airfoils in the target blade and the relative thickness of each of the N airfoils, where N is an integer greater than or equal to 2;

[0098] S2, determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil;

[0099] S3, optimizing the airfoil of the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

[0100] 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.

[0101] 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.

[0102] 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.

[0103] 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 blade optimization method, characterized in that: include: Determine the airfoil distribution of the target blade, wherein the airfoil distribution is used to indicate the distribution of N airfoils in the target blade and the relative thickness of each of the N airfoils, where N is an integer greater than or equal to 2; Determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil; The airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

2. The method according to claim 1, characterized in that The airfoil of the target blade is optimized according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils, comprising: When there are a first airfoil and a second airfoil in the N airfoils, and the relative thickness of the first airfoil is greater than the relative thickness of the second airfoil, determining whether the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil; When the maximum operating lift-to-drag ratio of the first airfoil is greater than or equal to the optimal operating lift-to-drag ratio of the second airfoil, the second airfoil in the target blade is replaced with the first airfoil.

3. The method according to claim 2, characterized in that After replacing the second airfoil in the target blade with the first airfoil, the method further includes: A target airfoil in the target blade is replaced with the first airfoil, wherein the target airfoil is an airfoil in the target blade whose relative thickness is smaller than that of the second airfoil.

4. The method according to claim 1, characterized in that: Determine the airfoil distribution of the target blade, including: Obtaining power generation requirements and load requirements of the target blade; The airfoil distribution of the target blade that meets the power generation requirement and the load requirement is determined.

5. The method according to claim 4, characterized in that Determining the airfoil distribution of the target blade that meets the power generation requirement and the load requirement, the method further includes: Acquire an airfoil set, wherein the airfoil set includes airfoils of multiple different relative thicknesses; Based on the airfoil set, an airfoil distribution of the target blade that meets the power generation requirement and the load requirement is determined, wherein the airfoils in the airfoil distribution are the airfoils in the airfoil set.

6. The method according to claim 1, characterized in that Determining the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade includes: The optimal operating lift-to-drag ratio of each of the N airfoils is determined according to the airfoil distribution of the target blades through a wind turbine simulation tool.

7. A blade optimization device, characterized in that: include: A first determination module is used to determine the airfoil distribution of the target blade, wherein the airfoil distribution is used to indicate the distribution of N airfoils in the target blade and the relative thickness of each of the N airfoils, where N is an integer greater than or equal to 2; A second determination module is used to determine the optimal operating lift-to-drag ratio of each of the N airfoils according to the airfoil distribution of the target blade, wherein the optimal operating lift-to-drag ratio is the operating lift-to-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil; The optimization module is used to optimize the airfoil of the target blade according to the optimal operating lift-to-drag ratio and the maximum operating lift-to-drag ratio of each of the N airfoils.

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.

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