Optimization method and device for middle airfoil profile of wind power blade and storage medium

Abstract

The invention discloses an optimization method and device for a middle airfoil of a wind power blade and a storage medium, and the method comprises the steps: determining an airfoil independent variable of the middle airfoil, and enabling the airfoil independent variable to be obtained through the conversion of the geometric characteristic parameters of the middle airfoil through a geometric parameterization method; initial aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil profile independent variables and the constraint conditions are obtained, and the low-precision airfoil profile of the wind power blade is determined according to the initial aerodynamic parameters and the airfoil profile independent variables; determining an analysis result of aerodynamic performance analysis on the low-precision airfoil profile; and under the condition that the analysis result is determined to indicate that the aerodynamic performance of the low-precision airfoil is not enough to support normal power generation of the wind power blade, performing high-precision optimization on the low-precision airfoil to obtain a high-precision airfoil of the wind power blade. By adopting the technical scheme, the problem of how to optimize the middle airfoil profile of the wind power blade to improve the aerodynamic performance of the wind power blade is solved.

Description

Technical Field

[0001] The present application relates to the field of wind turbine blade optimization design, and more specifically, to a method, device and storage medium for optimizing the middle airfoil of a wind turbine blade. Background Art

[0002] With the continuous development of wind power generation technology, the weight of large wind turbine blades above 100 meters will affect the manufacturing cost of the blades and the efficiency of wind power generation. Therefore, designing a lightweight and high-performance blade middle airfoil has become the key to wind turbine blade design. The current airfoil design method is aimed at the design of the middle airfoil of the blade, and it is necessary to use software with different software interfaces and software interfaces. In addition, due to the long running time and calculation time of the software, the calculation efficiency is not high, which leads to low aerodynamic performance of the wind turbine blade. Therefore, in the related art, there is a problem of how to optimize the middle airfoil of the wind turbine blade to improve the aerodynamic performance of the wind turbine blade.

[0003] With regard to the problem of how to optimize the middle airfoil of a wind turbine blade to improve the aerodynamic performance of the wind turbine blade in the related art, 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 a method, device and storage medium for optimizing the middle airfoil of a wind turbine blade, so as to at least solve the problem of how to optimize the middle airfoil of a wind turbine blade to improve the aerodynamic performance of the wind turbine blade.

[0006] According to one aspect of an embodiment of the present application, a method for optimizing a middle airfoil of a wind turbine blade is provided, comprising: determining airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by converting geometric characteristic parameters of the middle airfoil using a geometric parameterization method; obtaining initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraints, and determining a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables; determining an analysis result of an aerodynamic performance analysis of the low-precision airfoil; and when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, performing high-precision optimization on the low-precision airfoil to obtain a high-precision airfoil of the wind turbine blade.

[0007] In an exemplary embodiment, the constraint condition is that the value of the aerodynamic parameter of the middle airfoil satisfies a first interval, and the value of the airfoil independent variable of the middle airfoil satisfies a second interval, and the initial aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variables and the constraint condition are obtained, including: automatically adjusting the current value of the airfoil independent variable according to the interval value of the second interval, and obtaining the current aerodynamic parameters calculated by the aerodynamic performance analysis software based on the current value; screening out the aerodynamic parameters belonging to the first interval from multiple current aerodynamic parameters, and determining the aerodynamic parameters belonging to the first interval as the initial aerodynamic parameters.

[0008] In an exemplary embodiment, determining the analysis result of the aerodynamic performance analysis of the low-precision airfoil includes: using the aerodynamic performance analysis software to calculate the test aerodynamic parameters of the low-precision airfoil at the test angle of attack, wherein the test aerodynamic parameters include at least one of the following: stall angle of attack, lift coefficient, drag coefficient, lift-to-drag ratio; generating the analysis result based on the comparison result of the test aerodynamic parameters and the test threshold.

[0009] In an exemplary embodiment, the analysis result is generated based on the comparison result of the test aerodynamic parameter and the test threshold, including: when it is determined that the value of the test aerodynamic parameter is less than the test threshold, determining that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is sufficient to support the normal power generation of the wind turbine blade; when it is determined that the value of the test aerodynamic parameter is greater than the test threshold, determining that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade.

[0010] In an exemplary embodiment, when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain the high-precision airfoil of the wind turbine blade, including: determining the airfoil geometry of the low-precision airfoil according to the airfoil independent variables, and inputting the airfoil geometry into computational fluid dynamics software so that the computational fluid dynamics software generates a low-precision three-dimensional airfoil model, and calculates the lift coefficient of the three-dimensional airfoil model at different angles of attack; and optimizing the low-precision airfoil with high precision according to the magnitude relationship of the lift coefficients at different angles of attack to obtain the high-precision airfoil of the wind turbine blade.

[0011] In an exemplary embodiment, the lift coefficients at different angles of attack include at least a first lift coefficient at a first preset angle of attack and a second lift coefficient at a second preset angle of attack, the first preset angle of attack being greater than the second preset angle of attack, and the low-precision airfoil is optimized with high precision according to the magnitude relationship of the lift coefficients at different angles of attack to obtain a high-precision airfoil for the wind turbine blade, including: when it is determined that the first lift coefficient is less than the second lift coefficient, determining from the constraints a first interval satisfied by the values ​​of the aerodynamic parameters of the middle airfoil, and obtaining a numerical interval corresponding to the values ​​of the stall angle of attack from the first interval, adjusting the minimum value of the numerical interval to the sum of the first preset angle of attack and the adjusted angle of attack, so as to update the constraints; obtaining optimized aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variables and the updated constraints, and determining the high-precision airfoil according to the optimized aerodynamic parameters and the airfoil independent variables.

[0012] According to another aspect of an embodiment of the present application, there is also provided an optimization device for the middle airfoil of a wind turbine blade, comprising: a first determination module, used to determine the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by converting the geometric characteristic parameters of the middle airfoil using a geometric parameterization method; a calculation module, used to obtain initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraints, and determine the low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables; a second determination module, used to determine the analysis result of aerodynamic performance analysis of the low-precision airfoil; an optimization module, used to perform high-precision optimization on the low-precision airfoil to obtain a high-precision airfoil for the wind turbine blade when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade.

[0013] According to another aspect of the embodiment of the present application, a computer-readable storage medium is provided, in which a computer program is stored, wherein the computer program is configured to execute the above-mentioned method for optimizing the middle airfoil of a wind turbine blade when running.

[0014] According to another aspect of an embodiment of the present application, an electronic device is also provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the method for optimizing the middle airfoil of a wind turbine blade through the computer program.

[0015] According to another aspect of the present application, a computer program product is provided, 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 implemented.

[0016] Through the present application, the airfoil independent variables of the middle airfoil are determined, wherein the airfoil independent variables are obtained by converting the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method; initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions are obtained, and a low-precision airfoil of the wind turbine blade is determined according to the initial aerodynamic parameters and the airfoil independent variables; an analysis result of an aerodynamic performance analysis of the low-precision airfoil is determined; and when it is determined that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil of the wind turbine blade. The present application converts the geometric characteristic parameters of the middle airfoil into airfoil independent variables by adopting a geometric parameterization method, and then uses low-precision airfoils for preliminary screening to reduce the consumption of computing resources. The screened airfoils are then optimized with high precision to improve the accuracy of the optimization results. This solves the problem of how to optimize the middle airfoil of a wind turbine blade to improve the aerodynamic performance of the wind turbine blade, and proposes a high-precision middle airfoil for a wind turbine blade, which improves the aerodynamic performance of the wind turbine blade. 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 method for optimizing the middle airfoil of a wind turbine blade according to an embodiment of the present application;

[0020] Figure 2 is a flow chart of a method for optimizing the middle airfoil of a wind turbine blade according to an embodiment of the present application;

[0021] Figure 3 It is a structural block diagram of a device for optimizing the middle airfoil of a wind turbine blade 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 1 is a hardware structure block diagram of a mobile terminal of a method for optimizing the middle airfoil of a wind turbine blade 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 microprocessor or a processing device such as a programmable logic device (Field Programmable Gate Array, 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 optimization method of the middle airfoil of the wind turbine blade 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 this embodiment, a method for optimizing the airfoil of a middle portion of a wind turbine blade is provided. Figure 2 is a flow chart of a method for optimizing the middle airfoil of a wind turbine blade according to an embodiment of the present application, such as Figure 2 As shown, the process includes the following steps:

[0028] Step S202: determining the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by transforming the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method;

[0029] Optionally, considering setting the geometric parameters of the airfoil as independent variables, the present application adopts a geometric parameterization method to convert key geometric characteristic parameters such as the thickness, camber, and trailing edge shape of the airfoil into adjustable airfoil independent variables.

[0030] Step S204: obtaining initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions, and determining a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables;

[0031] Optionally, for this step, an airfoil simulation model may be generated, the initial aerodynamic parameters and the airfoil independent variables may be input, and the airfoil simulation model may be used to perform aerodynamic performance analysis.

[0032] Step S206: determining the analysis result of the aerodynamic performance analysis of the low-precision airfoil;

[0033] Step S208: When it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil for the wind turbine blade.

[0034] Through the above steps, the airfoil independent variables of the middle airfoil are determined, wherein the airfoil independent variables are obtained by converting the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method; initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions are obtained, and a low-precision airfoil of the wind turbine blade is determined according to the initial aerodynamic parameters and the airfoil independent variables; an analysis result of an aerodynamic performance analysis of the low-precision airfoil is determined; and when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil of the wind turbine blade. The present application converts the geometric characteristic parameters of the middle airfoil into airfoil independent variables by adopting a geometric parameterization method, and then uses low-precision airfoils for preliminary screening to reduce the consumption of computing resources. The screened airfoils are then optimized with high precision to improve the accuracy of the optimization results. This solves the problem of how to optimize the middle airfoil of a wind turbine blade to improve the aerodynamic performance of the wind turbine blade, and proposes a high-precision middle airfoil for a wind turbine blade, which improves the aerodynamic performance of the wind turbine blade.

[0035] In an exemplary embodiment, the constraint condition is that the value of the aerodynamic parameter of the middle airfoil satisfies the first interval, and the value of the airfoil independent variable of the middle airfoil satisfies the second interval. The process of obtaining the initial aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variable and the constraint condition may include: automatically adjusting the current value of the airfoil independent variable according to the interval value of the second interval, and obtaining the current aerodynamic parameters calculated by the aerodynamic performance analysis software based on the current value; screening out the aerodynamic parameters belonging to the first interval from multiple current aerodynamic parameters, and determining the aerodynamic parameters belonging to the first interval as the initial aerodynamic parameters. This embodiment can more accurately control the direction of airfoil optimization by dynamically adjusting the value range of the airfoil independent variable, thereby reducing the waste of resources caused by blind optimization.

[0036] In an exemplary embodiment, the step of determining the analysis result of the aerodynamic performance analysis of the low-precision airfoil may include the following implementation process: using the aerodynamic performance analysis software to calculate the test aerodynamic parameters of the low-precision airfoil at the test angle of attack, wherein the test aerodynamic parameters include at least one of the following: stall angle of attack, lift coefficient, drag coefficient, lift-to-drag ratio; generating the analysis result based on the comparison result of the test aerodynamic parameters and the test threshold. This embodiment is suitable for the preliminary screening stage of wind turbine blade design, and can quickly evaluate the aerodynamic performance of the airfoil in the preliminary screening stage without the need for high-precision calculations of all airfoils, thereby improving the evaluation efficiency of the airfoil.

[0037] In an exemplary embodiment, for the process of generating the analysis result according to the comparison result of the test aerodynamic parameter and the test threshold, the proposed steps include: when it is determined that the value of the test aerodynamic parameter is less than the test threshold, determining that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is sufficient to support the normal power generation of the wind turbine blade; when it is determined that the value of the test aerodynamic parameter is greater than the test threshold, determining that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade. This embodiment is also applicable to the preliminary screening stage of wind turbine blade design. By setting a reasonable test threshold, airfoils with aerodynamic performance that meets the requirements can be effectively screened out, reducing the workload of subsequent high-precision optimization.

[0038] In an exemplary embodiment, when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain the high-precision airfoil of the wind turbine blade, including: determining the airfoil geometry of the low-precision airfoil according to the airfoil independent variable, and inputting the airfoil geometry into the computational fluid dynamics software so that the computational fluid dynamics software generates a low-precision three-dimensional airfoil model, and calculates the lift coefficient of the three-dimensional airfoil model at different angles of attack; according to the magnitude relationship of the lift coefficient at different angles of attack, the low-precision airfoil is optimized with high precision to obtain the high-precision airfoil of the wind turbine blade. This method is suitable for the final optimization stage of wind turbine blade design, and combines aerodynamic performance analysis software and computational fluid dynamics software to improve the optimization accuracy of the aerodynamic performance of the airfoil.

[0039] In an exemplary embodiment, the lift coefficients at different angles of attack include at least a first lift coefficient at a first preset angle of attack and a second lift coefficient at a second preset angle of attack, the first preset angle of attack being greater than the second preset angle of attack, and the low-precision airfoil is optimized with high precision according to the magnitude relationship of the lift coefficients at different angles of attack to obtain a high-precision airfoil for the wind turbine blade. The process may include: when it is determined that the first lift coefficient is less than the second lift coefficient, determining from the constraints a first interval satisfied by the values ​​of the aerodynamic parameters of the middle airfoil, and obtaining a numerical interval corresponding to the values ​​of the stall angle of attack from the first interval, adjusting the minimum value of the numerical interval to the sum of the first preset angle of attack and the adjusted angle of attack, so as to update the constraints; obtaining optimized aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variables and the updated constraints, and determining the high-precision airfoil according to the optimized aerodynamic parameters and the airfoil independent variables. This method can more flexibly control the direction of airfoil optimization by dynamically adjusting the constraints, thereby obtaining a high-precision airfoil with better aerodynamic performance, effectively improving the power generation efficiency and operating stability of wind turbine blades, and providing strong technical support for the development of the wind power industry.

[0040] 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:

[0041] In an optional embodiment, a two-stage optimization design framework of the airfoil is adopted. First, the airfoil is preliminarily designed by parameterizing geometric variables; second, a high-precision CFD analysis is performed on the preliminarily designed airfoil to ensure that its performance meets the requirements.

[0042] Optionally, the airfoil optimization process is described in combination with the following content.

[0043] Step 1: Low-precision optimization design.

[0044] In the first-level optimization design framework, Xfoil or Rfoil software is used to analyze the aerodynamic performance with the geometric parameterized variables of the airfoil as independent variables. At the same time, the target aerodynamic performance of the blade (such as the maximum lift-to-drag ratio and the stall angle of attack not exceeding the set value) and the target structural performance (not exceeding the set moment of inertia) are considered as constraints, and a low-precision optimization design method is established through an intelligent optimization algorithm to obtain a low-precision airfoil.

[0045] The stall angle of attack is set as a target aerodynamic performance constraint at a value between 15 and 20 degrees, and the lift coefficient is set as a target aerodynamic performance constraint at a value between 1.2 and 1.5.

[0046] Among them, Xfoil and Rfoil are commonly used aerodynamic performance analysis software, which can quickly calculate aerodynamic parameters such as the lift coefficient, drag coefficient, and lift-to-drag ratio of the airfoil at different angles of attack.

[0047] Step 2: Preliminary performance evaluation.

[0048] Perform aerodynamic performance analysis on the low-precision airfoil obtained in step 1, and calculate the stall angle of attack As and lift coefficient CLs. Among them, "stall angle of attack As0" is the maximum angle of attack before the airfoil reaches the stall state.

[0049] After obtaining the initially optimized low-precision airfoil, further aerodynamic performance analysis is performed to confirm its stall angle of attack As and lift coefficient CLs at a specific angle of attack, as well as other key aerodynamic parameters within the design range, providing a basis for subsequent high-precision analysis. That is, the calculation results of parameters such as stall angle of attack As and lift coefficient CLs will be used to determine whether the airfoil needs to be further optimized and to adjust the optimization strategy.

[0050] The purpose of the above-mentioned first-level design framework is to perform rapid iterative optimization through aerodynamic performance analysis software to screen out airfoils that meet the preliminary aerodynamic and structural performance requirements.

[0051] Step 3, in the second-level optimization design framework, use CFD software (Computational FluidDynamics) to perform high-precision modeling and performance analysis on the low-precision airfoil obtained in the first stage, and calculate the lift coefficient CL_As_0 and the lift coefficient CL_As_-1 of the airfoil at the angle of attack As-1 degrees.

[0052] It is understood that the angle of attack is defined as the angle between the air flow direction and the chord line of the airfoil (the straight line connecting the leading edge and the trailing edge of the airfoil). When referring to "angle of attack As and As-1 degree", As refers to a specific angle of attack value, while As-1 degree refers to an angle of attack value 1 degree less than As. When discussing the angle of attack As and As-1 degree, we are actually comparing the lift coefficient of the airfoil at two very close angles of attack.

[0053] The specific steps are as follows:

[0054] 1. Modeling: First, the airfoil geometry obtained from the first-level optimization design is input into the CFD software to generate a three-dimensional model. The model must accurately reflect the geometric details of the airfoil, including the leading edge, trailing edge and the overall profile of the airfoil.

[0055] 2. Meshing: Meshing the airfoil model is the basis of CFD analysis. The quality of the mesh directly affects the accuracy and efficiency of the calculation. The leading and trailing edge areas of the airfoil will be divided more finely to capture the characteristics of the fluid boundary layer.

[0056] 3. Set boundary conditions and physical models: define the properties of the fluid (such as air) and the simulated environmental conditions (such as velocity, temperature and pressure). Select a suitable turbulence model (turbulence model based on the Reynolds-averaged Navier-Stokes equations) and boundary conditions to simulate the fluid dynamics behavior of the airfoil at different angles of attack.

[0057] 4. Run CFD analysis: Use CFD software to perform calculations, simulate the flow of air over the airfoil, analyze the flow field characteristics of the airfoil at angles of attack As and As-1 degrees, and calculate the corresponding lift coefficients CL_As_0 and CL_As_-1.

[0058] 5. Result analysis: Compare the lift coefficients CL_As_0 and CL_As_-1 at angles of attack As and As-1 degrees to evaluate the aerodynamic performance of the airfoil.

[0059] If the lift coefficient CL_As_0 (the lift coefficient at angle of attack As) is greater than or equal to CL_As_-1 (the lift coefficient at angle of attack As-1 degree), this indicates that the lift coefficient of the airfoil does not decrease with increasing angle of attack, but instead remains stable or increases slightly until or above the stall angle of attack As. Near the stall angle of attack, the lift of the airfoil usually drops sharply, which is caused by the separation of the airflow on the airfoil surface.

[0060] However, if CL_As_0≥CL_As_-1 holds true, this means that when the airfoil is close to the stall angle of attack, the change trend of its lift coefficient is in line with the design expectations, which is the ideal state of the airfoil design. This means that between the two angles of attack As and As-1 degrees, the airfoil has good performance and has not entered the stall state. That is, when the angle of attack increases from As-1 degrees to As, the lift coefficient of the airfoil does not show the expected significant decrease, which indicates that the airfoil has strong performance stability within this angle of attack range.

[0061] Through the above two-level design framework, while ensuring design efficiency, the airfoil performance can be carefully optimized using high-precision CFD analysis to ensure that the designed airfoil is both light and has excellent aerodynamic performance and structure.

[0062] Step 4, performance verification and iteration: If the lift coefficient CL_As_0 is greater than or equal to CL_As_-1, the airfoil design is completed and output; otherwise, adjust the stall angle constraint (As≥As+1) and repeat steps 2 to 4.

[0063] Through the above method, the efficiency of wind turbine blade design is significantly improved, unnecessary design iterations are reduced, and the optimization of the aerodynamic performance of the airfoil is ensured, so that the wind turbine blades can better capture wind energy in actual operation, increase power generation, and reduce the cost of wind power generation. By applying the above method in actual scenarios and optimizing the airfoil in the middle of the wind turbine blade, the overall performance of the wind turbine generator set can be effectively improved, its service life can be extended, maintenance costs can be reduced, and the sustainable development of the wind power industry can be promoted, which is of great significance for reducing global carbon emissions and promoting the widespread use of green energy.

[0064] 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.

[0065] In this embodiment, a device for optimizing the middle airfoil of a wind turbine blade is also provided, and the device 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 be a combination of software and / or hardware that implements 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.

[0066] Figure 3 This is a structural block diagram of a device for optimizing the middle airfoil of a wind turbine blade according to an embodiment of the present application, the device comprising:

[0067] A first determination module 32 is used to determine the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by converting the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method;

[0068] A calculation module 34 is used to obtain initial aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions, and determine a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables;

[0069] A second determination module 36 is used to determine the analysis result of the aerodynamic performance analysis of the low-precision airfoil;

[0070] The optimization module 38 is used to perform high-precision optimization on the low-precision airfoil to obtain a high-precision airfoil for the wind turbine blade when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade.

[0071] By means of the above-mentioned device, the airfoil independent variables of the middle airfoil are determined, wherein the airfoil independent variables are obtained by converting the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method; initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions are obtained, and a low-precision airfoil of the wind turbine blade is determined according to the initial aerodynamic parameters and the airfoil independent variables; an analysis result of an aerodynamic performance analysis of the low-precision airfoil is determined; and when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil of the wind turbine blade. The present application converts the geometric characteristic parameters of the middle airfoil into airfoil independent variables by adopting a geometric parameterization method, and then uses low-precision airfoils for preliminary screening to reduce the consumption of computing resources. The screened airfoils are then optimized with high precision to improve the accuracy of the optimization results. This solves the problem of how to optimize the middle airfoil of a wind turbine blade to improve the aerodynamic performance of the wind turbine blade, and proposes a high-precision middle airfoil for a wind turbine blade, which improves the aerodynamic performance of the wind turbine blade.

[0072] In an exemplary embodiment, the constraint condition is that the value of the aerodynamic parameter of the middle airfoil satisfies a first interval, and the value of the airfoil independent variable of the middle airfoil satisfies a second interval. The calculation module is also used to: automatically adjust the current value of the airfoil independent variable according to the interval value of the second interval, and obtain the current aerodynamic parameter calculated by the aerodynamic performance analysis software based on the current value; filter out the aerodynamic parameters belonging to the first interval from multiple current aerodynamic parameters, and determine the aerodynamic parameters belonging to the first interval as the initial aerodynamic parameters.

[0073] In an exemplary embodiment, the second determination module is also used to: use the aerodynamic performance analysis software to calculate the test aerodynamic parameters of the low-precision airfoil at the test angle of attack, wherein the test aerodynamic parameters include at least one of the following: stall angle of attack, lift coefficient, drag coefficient, lift-to-drag ratio; and generate the analysis result based on the comparison result of the test aerodynamic parameters and the test threshold.

[0074] In an exemplary embodiment, the second determination module is further used to: when it is determined that the value of the test aerodynamic parameter is less than the test threshold, determine that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is sufficient to support the normal power generation of the wind turbine blade; when it is determined that the value of the test aerodynamic parameter is greater than the test threshold, determine that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade.

[0075] In an exemplary embodiment, the optimization module is also used to: determine the airfoil geometry of the low-precision airfoil based on the airfoil independent variables, and input the airfoil geometry into the computational fluid dynamics software so that the computational fluid dynamics software generates a low-precision three-dimensional airfoil model, and calculates the lift coefficient of the three-dimensional airfoil model at different angles of attack; perform high-precision optimization on the low-precision airfoil based on the size relationship of the lift coefficients at different angles of attack to obtain the high-precision airfoil of the wind turbine blade.

[0076] In an exemplary embodiment, the lift coefficients at different angles of attack include at least a first lift coefficient at a first preset angle of attack and a second lift coefficient at a second preset angle of attack, the first preset angle of attack being greater than the second preset angle of attack, and the optimization module is further used to: when it is determined that the first lift coefficient is less than the second lift coefficient, determine from the constraints a first interval satisfied by the values ​​of the aerodynamic parameters of the middle airfoil, and obtain from the first interval a numerical interval corresponding to the values ​​of the stall angle of attack, and adjust the minimum value of the numerical interval to the sum of the first preset angle of attack and the adjusted angle of attack to update the constraints; obtain optimized aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variables and the updated constraints, and determine the high-precision airfoil based on the optimized aerodynamic parameters and the airfoil independent variables.

[0077] 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.

[0078] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:

[0079] S1, determining the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by transforming the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method;

[0080] S2, obtaining initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions, and determining a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables;

[0081] S3, determining an analysis result of an aerodynamic performance analysis of the low-precision airfoil;

[0082] S4, when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil for the wind turbine blade.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:

[0087] S1, determining the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by transforming the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method;

[0088] S2, obtaining initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions, and determining a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables;

[0089] S3, determining an analysis result of an aerodynamic performance analysis of the low-precision airfoil;

[0090] S4, when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil for the wind turbine blade.

[0091] 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.

[0092] An embodiment of the present application further provides a computer program product, which includes a computer program. When the computer program is executed by a processor, the steps in any one of the above method embodiments are implemented.

[0093] An embodiment of the present application further provides another computer program product, including a non-volatile computer-readable storage medium, wherein the non-volatile computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps in any of the above method embodiments are implemented.

[0094] An embodiment of the present application also provides a computer program, which includes computer instructions, which are stored in a computer-readable storage medium; a processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device performs the steps in any one of the above method embodiments.

[0095] 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.

[0096] 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.

[0097] 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 optimizing the middle airfoil of a wind turbine blade, characterized in that: include: Determining the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by transforming the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method; Acquire initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions, and determine a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables; Determining an analysis result of an aerodynamic performance analysis of the low-precision airfoil; When it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain a high-precision airfoil for the wind turbine blade.

2. The method for optimizing the middle airfoil of a wind turbine blade according to claim 1, characterized in that: The constraint condition is that the value of the aerodynamic parameter of the middle airfoil satisfies the first interval, and the value of the airfoil independent variable of the middle airfoil satisfies the second interval, and the initial aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variable and the constraint condition are obtained, including: Automatically adjusting the current value of the airfoil independent variable according to the interval value of the second interval, and obtaining the current aerodynamic parameters calculated by the aerodynamic performance analysis software based on the current value; A pneumatic parameter belonging to the first interval is selected from a plurality of current aerodynamic parameters, and the aerodynamic parameter belonging to the first interval is determined as the initial aerodynamic parameter.

3. The method for optimizing the middle airfoil of a wind turbine blade according to claim 1, characterized in that: Determining the analysis result of the aerodynamic performance analysis of the low-precision airfoil, including: Using the aerodynamic performance analysis software to calculate the test aerodynamic parameters of the low-precision airfoil at the test angle of attack, wherein the test aerodynamic parameters include at least one of the following: stall angle of attack, lift coefficient, drag coefficient, lift-to-drag ratio; The analysis result is generated according to the comparison result between the test aerodynamic parameter and the test threshold.

4. The method for optimizing the middle airfoil of a wind turbine blade according to claim 3, characterized in that: Generating the analysis result according to the comparison result between the test aerodynamic parameter and the test threshold value includes: In the case where it is determined that the value of the test aerodynamic parameter is less than the test threshold, determining that the analysis result is used to indicate that the aerodynamic performance of the low-precision airfoil is sufficient to support the wind turbine blade to generate electricity normally; When it is determined that the value of the test aerodynamic parameter is greater than the test threshold, the analysis result is determined to indicate that the aerodynamic performance of the low-precision airfoil is insufficient to support normal power generation of the wind turbine blade.

5. The method for optimizing the middle airfoil of a wind turbine blade according to claim 1, characterized in that: When it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade, the low-precision airfoil is optimized with high precision to obtain the high-precision airfoil of the wind turbine blade, including: The airfoil geometry of the low-precision airfoil is determined according to the airfoil independent variables, and the airfoil geometry is input into computational fluid dynamics software so that the computational fluid dynamics software generates a low-precision three-dimensional airfoil model and calculates the lift coefficient of the three-dimensional airfoil model at different angles of attack; the low-precision airfoil is optimized with high precision according to the magnitude relationship of the lift coefficients at different angles of attack to obtain a high-precision airfoil for the wind turbine blade.

6. The method for optimizing the middle airfoil of a wind turbine blade according to claim 5, characterized in that: The lift coefficients at different attack angles at least include a first lift coefficient at a first preset attack angle and a second lift coefficient at a second preset attack angle, the first preset attack angle is greater than the second preset attack angle, and the low-precision airfoil is optimized with high precision according to the magnitude relationship of the lift coefficients at different attack angles to obtain the high-precision airfoil of the wind turbine blade, including: In the case where it is determined that the first lift coefficient is less than the second lift coefficient, a first interval satisfied by the value of the aerodynamic parameter of the middle airfoil is determined from the constraint condition, and a numerical interval corresponding to the value of the stall angle of attack is obtained from the first interval, and a minimum value of the numerical interval is adjusted to the sum of the first preset angle of attack and the adjusted angle of attack, so as to update the constraint condition; The optimized aerodynamic parameters calculated by the aerodynamic performance analysis software based on the airfoil independent variables and the updated constraint conditions are obtained, and the high-precision airfoil is determined according to the optimized aerodynamic parameters and the airfoil independent variables.

7. A device for optimizing the airfoil of a wind turbine blade in the middle, characterized in that: include: A first determination module is used to determine the airfoil independent variables of the middle airfoil, wherein the airfoil independent variables are obtained by transforming the geometric characteristic parameters of the middle airfoil by adopting a geometric parameterization method; A calculation module, used to obtain initial aerodynamic parameters calculated by aerodynamic performance analysis software based on the airfoil independent variables and constraint conditions, and determine a low-precision airfoil of the wind turbine blade according to the initial aerodynamic parameters and the airfoil independent variables; The second determination module is used to determine the analysis result of the aerodynamic performance analysis of the low-precision airfoil; the optimization module is used to perform high-precision optimization on the low-precision airfoil to obtain the high-precision airfoil of the wind turbine blade when it is determined that the analysis result indicates that the aerodynamic performance of the low-precision airfoil is insufficient to support the normal power generation of the wind turbine blade.

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 steps of the method according to any one of claims 1 to 6 are implemented.

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