Method and device for determining tip airfoil profile of wind power blade and storage medium
By weighted fusion and iterative optimization of the pointed airfoil of the wind power blade, the problem that the airfoil in the prior art cannot take into account both aerodynamic performance and structural efficiency, and more efficient and stable wind power generation is achieved.
Patent Information
- Application Number
- CN202411996238.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-31
- Publication Date
- 2025-04-25
AI Technical Summary
The pointed airfoils of existing wind power blades cannot take into account the aerodynamic performance and structural efficiency of the airfoil.
The pointed airfoil is determined by selecting reference airfoils of different thicknesses from the preset standard airfoils, performing weighted fusion, and obtaining target geometric coordinates that meet the aerodynamic performance constraints and have the sum of the maximum moment of inertia through iterative optimization.
The design flexibility and aerodynamic performance of the tip airfoil of the wind power blade are achieved, while ensuring the structural strength and stability of the blades, improving the efficiency and stability of wind power generation.
Smart Images
Figure CN119885489A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of wind turbine blade airfoil optimization, and in particular, to a method, device and storage medium for determining a tip airfoil of a wind turbine blade. Background Art
[0002] At present, with the acceleration of the transformation of the global energy structure, wind energy, as a renewable clean energy, has become an important part of the energy field because of its cleanness, pollution-free and abundant resources. The nacelle of the wind turbine is located at the top of the tower and is usually composed of impellers, transmission systems, generators, control cabinets and other components. Among them, the impeller is responsible for converting wind energy into mechanical energy. As one of the key components of a wind turbine, the blades need to meet the aerodynamic and other performance requirements of the blades. The reason why the blades can capture wind energy and convert it into mechanical energy lies in the blade airfoil design, that is, the leading and trailing edge shapes of the blades, among which the tip airfoil of the blade is the key factor. The tip airfoil design of the blade needs to balance many design goals to ensure efficient power generation of the wind turbine. However, the current tip airfoil design of the blade only considers the aerodynamic performance of the airfoil and does not have good structural efficiency. Therefore, in the related art, the tip airfoil of the blade cannot take into account both the aerodynamic performance and structural efficiency of the airfoil.
[0003] With regard to the problem in the related art that the tip airfoil of the blade cannot take into account both the aerodynamic performance and the structural efficiency of the airfoil, 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 determining the tip airfoil of a wind turbine blade, so as to at least solve the problem that the tip airfoil of the blade cannot take into account both the aerodynamic performance and the structural efficiency of the airfoil.
[0006] According to one aspect of an embodiment of the present application, a method for determining a tip airfoil of a wind turbine blade is provided, comprising: selecting a first reference airfoil and a second reference airfoil from preset standard airfoils, respectively, wherein the airfoil relative thickness of the first reference airfoil is less than the airfoil relative thickness of the second reference airfoil; determining a first trailing edge geometric coordinate of the first reference airfoil in a first reference system, and determining a second trailing edge geometric coordinate of the second reference airfoil in a second reference system; obtaining geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; obtaining target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia by iteratively optimizing the geometric coordinates to be optimized, and determining the tip airfoil corresponding to the target geometric coordinates.
[0007] In an exemplary embodiment, determining a first trailing edge geometric coordinate of the first reference airfoil in a first reference system includes: dividing the first reference airfoil into a leading edge portion and a trailing edge portion according to a first maximum thickness position of the first reference airfoil; establishing the first reference system by taking the first maximum thickness position as an origin, a direction along a chord direction of the first reference airfoil pointing to the trailing edge portion as an X-axis direction of the first reference system, and a direction perpendicular to the X-axis direction of the first reference system as a Y-axis direction of the first reference system; and determining the first trailing edge geometric coordinate based on the geometric coordinates of the trailing edge portion corresponding to the first reference system.
[0008] In an exemplary embodiment, the geometric coordinates to be optimized are obtained after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates, including: for the first vertical coordinate value of the first trailing edge geometric coordinate and the second vertical coordinate value of the second trailing edge geometric coordinate, the first vertical coordinate value and the second vertical coordinate value are linearly combined by using a weighting coefficient to obtain the geometric coordinates to be optimized after the weighted fusion.
[0009] In an exemplary embodiment, before linearly combining the first vertical coordinate value and the second vertical coordinate value by using a weighting coefficient, the method further includes: determining a maximum thickness ratio between an airfoil relative thickness of the first reference airfoil and an airfoil relative thickness of the second reference airfoil; scaling the second vertical coordinate value based on the maximum thickness ratio to obtain a third vertical coordinate value, and updating the second vertical coordinate value using the third vertical coordinate value.
[0010] In an exemplary embodiment, the target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia are obtained by iteratively optimizing the geometric coordinates to be optimized, including: automatically adjusting the weighting coefficients in the geometric coordinates to be optimized to obtain adjusted geometric coordinates, calculating the sum of moments of inertia corresponding to the adjusted geometric coordinates, and using aerodynamic performance analysis software to calculate the aerodynamic parameters of the wind turbine blade when it works based on the adjusted geometric coordinates; iteratively calculating the sum of aerodynamic parameters and moments of inertia based on a genetic optimization algorithm until the target geometric coordinates are obtained.
[0011] In an exemplary embodiment, after determining the first trailing edge geometric coordinates of the first reference airfoil in the first reference system and determining the second trailing edge geometric coordinates of the second reference airfoil in the second reference system, the method further includes: standardizing the coordinate data of the first trailing edge geometric coordinates and the coordinate data of the second trailing edge geometric coordinates to obtain first standardized trailing edge geometric coordinates and second standardized trailing edge geometric coordinates; smoothing the first standardized trailing edge geometric coordinates and the second standardized trailing edge geometric coordinates respectively to obtain smoothed first trailing edge geometric coordinates and smoothed second trailing edge geometric coordinates; replacing the first trailing edge geometric coordinates with the smoothed first trailing edge geometric coordinates, and replacing the smoothed second trailing edge geometric coordinates with the smoothed second trailing edge geometric coordinates.
[0012] According to another aspect of the embodiment of the present application, there is also provided a device for determining the tip airfoil of a wind turbine blade, comprising: a selection module for selecting a first reference airfoil and a second reference airfoil from preset standard airfoils, respectively, wherein the airfoil relative thickness of the first reference airfoil is less than the airfoil relative thickness of the second reference airfoil; a determination module for determining the first trailing edge geometric coordinates of the first reference airfoil in the first reference system, and determining the second trailing edge geometric coordinates of the second reference airfoil in the second reference system; an acquisition module for acquiring the geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; an optimization module for iteratively optimizing the geometric coordinates to be optimized, obtaining target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia, and determining the tip airfoil corresponding to the target geometric coordinates. According to another aspect of the embodiment of the present application, there is also provided a computer-readable storage medium, in which a computer program is stored, wherein the computer program is configured to execute the above-mentioned method for determining the tip airfoil of a wind turbine blade when running.
[0013] According to another aspect of an embodiment of the present application, an electronic device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the method for determining the tip airfoil of the wind turbine blade through the computer program.
[0014] 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.
[0015] Through the present application, a first reference airfoil and a second reference airfoil are respectively selected from preset standard airfoils, wherein the relative airfoil thickness of the first reference airfoil is less than the relative airfoil thickness of the second reference airfoil; the first trailing edge geometric coordinates of the first reference airfoil in the first reference system are determined, and the second trailing edge geometric coordinates of the second reference airfoil in the second reference system are determined; the geometric coordinates to be optimized are obtained after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; the target geometric coordinates that meet aerodynamic performance constraints and have the maximum sum of moments of inertia are obtained by iteratively optimizing the geometric coordinates to be optimized, and the tip airfoil corresponding to the target geometric coordinates is determined. This solution effectively improves the design flexibility and aerodynamic performance of the tip of the wind turbine blade by selecting reference airfoils of different thicknesses for weighted fusion, and then determines the tip airfoil that meets aerodynamic performance constraints and has the maximum sum of moments of inertia through iterative optimization, while ensuring the structural strength and stability of the blade. By automatically adjusting the weighting coefficients and combining with the genetic optimization algorithm, the optimal airfoil can be found quickly and accurately, which significantly improves the design efficiency and blade performance, and provides new ideas and methods for the optimal design of wind turbine blades, thereby solving the problem that the tip airfoil of the blade cannot take into account both the aerodynamic performance and structural efficiency of the airfoil, and realizing a tip airfoil that takes into account both the aerodynamic performance and structural efficiency of the airfoil, thereby improving the efficiency and stability of wind power generation. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] 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.
[0017] 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.
[0018] Figure 1 This is a hardware structure block diagram of a mobile terminal for a method for determining a tip airfoil of a wind turbine blade according to an embodiment of the present application;
[0019] Figure 2 is a flow chart of a method for determining a tip airfoil of a wind turbine blade according to an embodiment of the present application;
[0020] Figure 3 It is a structural block diagram of a device for determining the tip airfoil of a wind turbine blade according to an embodiment of the present application. DETAILED DESCRIPTION
[0021] 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.
[0022] 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.
[0023] 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 for determining a tip 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.
[0024] 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 determining the tip 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 a combination thereof.
[0025] 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.
[0026] In this embodiment, a method for determining the tip airfoil of a wind turbine blade is provided. Figure 2 is a flow chart of a method for determining a tip 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:
[0027] Step S202: selecting a first reference airfoil and a second reference airfoil from preset standard airfoils, respectively, wherein the airfoil relative thickness of the first reference airfoil is smaller than the airfoil relative thickness of the second reference airfoil;
[0028] Step S204: determining a first trailing edge geometric coordinate of the first reference airfoil in a first reference system, and determining a second trailing edge geometric coordinate of the second reference airfoil in a second reference system;
[0029] Step S206: obtaining geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates;
[0030] In this step, the characteristics of airfoils of different thicknesses are utilized, and a weighted fusion method is used to provide a wider range of options for the design of the tip airfoil of the wind turbine blade, thereby improving its aerodynamic efficiency while ensuring the structural strength of the blade.
[0031] Step S208: obtaining target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia by iteratively optimizing the geometric coordinates to be optimized, and determining a tip airfoil corresponding to the target geometric coordinates.
[0032] Optionally, in step S208, the weighted coefficients required for weighted fusion can be automatically adjusted and iteratively calculated to find the airfoil geometry design that satisfies the maximum sum of moments of inertia under the aerodynamic performance constraints. Specifically, the sum of the moments of inertia of the X-axis and the Y-axis and the aerodynamic parameters of the airfoil can be recalculated after each adjustment of the geometric coordinates of the airfoil. Through multiple iterations, the intelligent optimization algorithm gradually approaches the optimal solution, and finally obtains the airfoil design that achieves the best balance between aerodynamic performance and structural performance.
[0033] Through the above steps, a first reference airfoil and a second reference airfoil are respectively selected from the preset standard airfoils, wherein the relative airfoil thickness of the first reference airfoil is less than the relative airfoil thickness of the second reference airfoil; the first trailing edge geometric coordinates of the first reference airfoil in the first reference system are determined, and the second trailing edge geometric coordinates of the second reference airfoil in the second reference system are determined; the geometric coordinates to be optimized are obtained after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; the target geometric coordinates that meet the aerodynamic performance constraints and have the maximum sum of moments of inertia are obtained by iteratively optimizing the geometric coordinates to be optimized, and the tip airfoil corresponding to the target geometric coordinates is determined. This scheme effectively improves the design flexibility and aerodynamic performance of the tip of the wind turbine blade by selecting reference airfoils of different thicknesses for weighted fusion, and then determines the tip airfoil that meets the aerodynamic performance constraints and has the maximum sum of moments of inertia through iterative optimization, while ensuring the structural strength and stability of the blade. By automatically adjusting the weighting coefficients and combining with the genetic optimization algorithm, the optimal airfoil can be found quickly and accurately, which significantly improves the design efficiency and blade performance, and provides new ideas and methods for the optimal design of wind turbine blades, thereby solving the problem that the tip airfoil of the blade cannot take into account both the aerodynamic performance and structural efficiency of the airfoil, and realizing a tip airfoil that takes into account both the aerodynamic performance and structural efficiency of the airfoil, thereby improving the efficiency and stability of wind power generation.
[0034] Furthermore, the present application can also flexibly adjust airfoil parameters according to different wind field conditions and operating requirements to achieve customized optimization of blade performance, further improving the market competitiveness and economic benefits of wind turbine blades.
[0035] In an exemplary embodiment, the process of determining the first trailing edge geometric coordinates of the first reference airfoil in the first reference system specifically includes: dividing the first reference airfoil into a leading edge portion and a trailing edge portion according to the first maximum thickness position of the first reference airfoil; establishing the first reference system by taking the first maximum thickness position as the origin, the direction along the chord direction of the first reference airfoil pointing to the trailing edge portion as the X-axis direction of the first reference system, and the direction perpendicular to the X-axis direction of the first reference system as the Y-axis direction of the first reference system; determining the first trailing edge geometric coordinates based on the geometric coordinates of the trailing edge portion corresponding to the first reference system. Based on this process, it is ensured that the geometric characteristics of the airfoil are accurately captured, laying the foundation for subsequent airfoil fusion and optimization.
[0036] Optionally, determining the second trailing edge geometric coordinates of the second reference airfoil in the second reference system may include: dividing the second reference airfoil into a leading edge portion and a trailing edge portion according to the second maximum thickness position; establishing the second reference system by taking the second maximum thickness position of the second reference airfoil as the origin, the direction along the chord direction of the second reference airfoil pointing to the trailing edge portion as the X-axis direction of the second reference system, and the direction perpendicular to the X-axis direction of the second reference system as the Y-axis direction of the second reference system; and determining the second trailing edge geometric coordinates based on the geometric coordinates of the trailing edge portion corresponding to the second reference system.
[0037] In an exemplary embodiment, the step of obtaining the geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates may include: for the first vertical coordinate value of the first trailing edge geometric coordinate and the second vertical coordinate value of the second trailing edge geometric coordinate, linearly combining the first vertical coordinate value and the second vertical coordinate value by using a weighting coefficient to obtain the weighted fused geometric coordinates to be optimized. This embodiment uses weighted fusion technology to flexibly combine the characteristics of different airfoils, providing a new idea for the innovative design of the tip airfoil of a wind turbine blade.
[0038] In an exemplary embodiment, before linearly combining the first vertical coordinate value and the second vertical coordinate value by using a weighting coefficient, a maximum thickness ratio between the airfoil relative thickness of the first reference airfoil and the airfoil relative thickness of the second reference airfoil may be determined; the second vertical coordinate value may be scaled based on the maximum thickness ratio to obtain a third vertical coordinate value, and the second vertical coordinate value may be updated using the third vertical coordinate value. By adjusting the airfoil thickness ratio, this embodiment may more accurately control the geometry of the airfoil, thereby better matching specific aerodynamic requirements in the design.
[0039] In an exemplary embodiment, the process of iteratively optimizing the geometric coordinates to be optimized to obtain target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia includes: automatically adjusting the weighting coefficients in the geometric coordinates to be optimized to obtain adjusted geometric coordinates, calculating the sum of moments of inertia corresponding to the adjusted geometric coordinates, and using aerodynamic performance analysis software to calculate the aerodynamic parameters of the wind turbine blade when it is working based on the adjusted geometric coordinates; iteratively calculating the sum of aerodynamic parameters and moments of inertia based on a genetic optimization algorithm until the target geometric coordinates are obtained. This embodiment can efficiently explore the airfoil design space and find the optimal balance point between aerodynamic and structural performance by combining iterative optimization with a genetic algorithm.
[0040] Optionally, the process of how to find the target geometric coordinates that satisfy the aerodynamic performance constraints and have the maximum sum of moments of inertia can be described by the following content. Exemplarily, in a simplified airfoil optimization design scenario, two sets of airfoil coordinates are set, representing airfoils of two different thicknesses: one is a relatively thin airfoil (WingThin), and the other is a relatively thick airfoil (WingThick). By mixing the second half of the two airfoils, a new airfoil is designed that has the maximum sum of structural moments of inertia while maintaining certain aerodynamic performance.
[0041] First, the coordinate data is preprocessed to ensure that the coordinate points of WingThin and WingThick are the same in the X direction and have been scaled according to the maximum thickness ratio R.
[0042] The weighting coefficient C1 is used to mix the coordinate points of the second half of WingThin and WingThick to obtain the coordinate points of the second half of the target airfoil (corresponding to the designed airfoil).
[0043] Use aerodynamic analysis software (such as XFOIL or RFOIL) to evaluate the aerodynamic performance of the mixed target airfoil. If the drag and lift ratio of the target airfoil at a specific angle of attack does not meet the aerodynamic performance constraints, it is necessary to adjust the value of C1, re-perform coordinate mixing and aerodynamic performance verification until an airfoil design that meets the constraints is found.
[0044] For the mixed target airfoil, the moments of inertia IX and IY about the X-axis and Y-axis are calculated. The calculation of the moment of inertia involves the position of the airfoil geometric coordinate points and the material density distribution, where it is assumed that the material density is uniformly distributed on the airfoil.
[0045] Construct an objective function, which represents the sum of IX and IY, and set it as objective function G(C1).
[0046] Using intelligent optimization algorithms (such as genetic algorithms, particle swarm algorithms, or gradient descent methods, etc.), the goal is to maximize G(C1) while ensuring that the target airfoil meets the aerodynamic performance constraints. The algorithm iteratively adjusts the value of C1 until it finds C1 that maximizes G(C1) and satisfies the aerodynamic performance constraints.
[0047] Assume that there are two coordinate points of the rear half of the airfoil:
[0048] The coordinate points of WingThin are (0.5, 0.02), (0.7, 0.015), (0.9, 0.008).
[0049] The coordinate points of WingThick (after scaling) are (0.5, 0.025), (0.7, 0.018), (0.9, 0.01).
[0050] Assume C1 = 0.6, and calculate the coordinates of the target airfoil after mixing:
[0051] y'1=0.02*0.6+0.025*(1-0.6)=0.021.
[0052] y'2=0.015*0.6+0.018*(1-0.6)=0.0162.
[0053] y'3=0.008*0.6+0.01*(1-0.6)=0.0088.
[0054] The coordinate points of the second half of the target airfoil are (0.5, 0.021), (0.7, 0.0162), and (0.9, 0.0088).
[0055] Next, the aerodynamic performance of the target airfoil is compared with the required aerodynamic performance constraints. If the constraints are met, the inertia moment about the X-axis and Y-axis is calculated, and the sum of the inertia moments of the X-axis and Y-axis is used as the value of the objective function G(C1). If the aerodynamic performance constraints are not met, the value of C1 needs to be adjusted, and the above process is repeated until a C1 value is found so that the target airfoil can meet the aerodynamic performance requirements and the sum of the structural inertia moments is maximized.
[0056] Through the above process, we can finally find a set of coordinate points of the second half of the airfoil. The airfoil shape formed by these points not only meets the expectations in aerodynamic performance, but also optimizes the structural performance, that is, the target geometric coordinates with the maximum sum of moments of inertia. This is exactly the balance point pursued in airfoil design optimization. Through the iterative calculation of the intelligent optimization algorithm, this optimal design point can be effectively found.
[0057] In an exemplary embodiment, after determining the first trailing edge geometric coordinates of the first reference airfoil in the first reference system and determining the second trailing edge geometric coordinates of the second reference airfoil in the second reference system, the coordinate data of the first trailing edge geometric coordinates and the coordinate data of the second trailing edge geometric coordinates can be standardized to obtain first standardized trailing edge geometric coordinates and second standardized trailing edge geometric coordinates; the first standardized trailing edge geometric coordinates and the second standardized trailing edge geometric coordinates are respectively smoothed to obtain smoothed first trailing edge geometric coordinates and smoothed second trailing edge geometric coordinates; the first trailing edge geometric coordinates are replaced with the smoothed first trailing edge geometric coordinates, and the smoothed second trailing edge geometric coordinates are replaced with the smoothed second trailing edge geometric coordinates. Standardization and smoothing can eliminate irregularities in airfoil data, improve the accuracy and stability of airfoil design, and are suitable for wind turbine blade design that requires high-quality airfoil data.
[0058] Optionally, in one embodiment, taking a 21% thickness airfoil as a first reference airfoil and a 25% thickness airfoil as a second reference airfoil as an example, the geometric coordinates of the 21% thickness airfoil and the geometric coordinates of the 25% thickness airfoil are preprocessed, and the preprocessing process includes:
[0059] Coordinate standardization: First, the coordinate data of the 21% thickness airfoil and the 25% thickness airfoil need to be standardized so that they are based on the same reference, such as setting the leading edge point of the airfoil as the origin of the coordinate system, or setting the chord length of the airfoil as the unit length. Such standardization can eliminate the deviation caused by different coordinate system selections and ensure the consistency of scaling and fusion operations.
[0060] Data cleaning: Check the integrity of the coordinate data to ensure that there are no missing values or outliers. In actual engineering design, the original data may contain some measurement errors or inconsistencies. The purpose of data cleaning is to remove these erroneous data and maintain the continuity and smoothness of the airfoil profile.
[0061] Format uniformity: Ensure that the format of coordinate data is uniform, for example, all coordinate data should be stored in the same data type and precision. This step helps avoid errors caused by mismatched data formats during calculations.
[0062] Numerical adjustment: Before performing the scaling operation, the coordinate values may need to be appropriately adjusted, such as multiplying the coordinate values of the 25% thickness airfoil by the scaling factor R to ensure geometric compatibility with the 21% thickness airfoil. At the same time, the coordinate values are adjusted according to the weighting coefficient C1 to linearly blend the geometric features of the two airfoils.
[0063] Geometric verification: During the preprocessing process, the geometric characteristics of the airfoil also need to be initially verified, such as checking whether the maximum thickness position, leading edge and trailing edge shapes of the airfoil are as expected. This helps ensure that the aerodynamic and structural performance targets of the airfoil will not deviate due to errors in the initial data during the subsequent optimization process.
[0064] Data smoothing: To ensure the smoothness of the airfoil shape, the preprocessing step may include smoothing the coordinate data, using curve fitting or filtering methods to remove high-frequency noise, making the airfoil profile smoother, which is beneficial for subsequent aerodynamic analysis and structural optimization.
[0065] Establish the consistency of coordinate system: Make sure the coordinate system of 21% thickness airfoil and 25% thickness airfoil is consistent, for example, the X axis should be along the chord direction of the airfoil, and the Y axis should be perpendicular to the chord direction. This step is critical to ensure the accuracy of the calculation of the moment of inertia.
[0066] Through the above preprocessing steps, the coordinate data of the 21% thickness airfoil and the 25% thickness airfoil can be ensured to maintain consistency and accuracy in operations such as scaling and blending, reducing the complexity of subsequent calculations, thereby obtaining more reliable results in the airfoil optimization design process.
[0067] 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:
[0068] In an optional embodiment, the present application describes the process of airfoil optimization through the following steps.
[0069] 1) Select a 21% thickness standard airfoil (corresponding to the first reference airfoil), divide the airfoil into two parts, front and rear, according to the chord-wise position of the maximum thickness, and mark the geometric coordinates of the rear half of the airfoil as (x21i, y21i).
[0070] 2) Establish an XOY coordinate system (corresponding to the first reference system) with the chordwise position of the maximum thickness as the origin, where the X-axis points to the trailing edge along the chordwise direction of the airfoil, and the Y-axis is perpendicular to the X-axis;
[0071] The chord-wise position of maximum thickness describes the maximum thickness position from the chord length direction of the airfoil. The chord line is the straight line connecting the leading edge and the trailing edge of the airfoil, and the chord-wise position refers to the position in the direction of the chord line. Therefore, the "chord-wise position of maximum thickness" specifically refers to the position of the point on the chord line where the thickness reaches the maximum value, that is, the maximum thickness position.
[0072] In the reference coordinate system corresponding to the airfoil, a dimensionless parameter ranging from 0 to 1 is selected to represent the maximum thickness position, such as 0.3 or 0.4, which means that the maximum thickness position is at 30% or 40% of the chord length from the leading edge of the airfoil.
[0073] The X-axis points to the trailing edge along the chord direction of the airfoil (that is, the length direction of the airfoil), which makes it easier to describe the shape changes of the airfoil along the chord line. Especially when adjusting the leading and trailing edge shapes of the airfoil, setting the direction of the X-axis to be consistent with the chord line makes the design more intuitive.
[0074] The Y-axis is perpendicular to the X-axis and points to the suction surface, which is the upper surface of the airfoil. During flight or rotation, the wind acts on the suction surface, generating lift and also affecting the structure of the airfoil. The design of the Y-axis toward the suction surface helps to quantify the geometric characteristics of the airfoil in this direction, such as thickness distribution, curvature, etc., so as to better optimize its aerodynamic and structural performance.
[0075] By setting such a coordinate system, the geometric parameters of the airfoil, such as thickness and curvature, can be analyzed more accurately, and these parameters can be used to optimize the structural efficiency, ensuring that while improving the aerodynamic performance, the structural strength and weight of the airfoil are also taken into account, so as to achieve a lighter, stronger and more efficient wind turbine blade design.
[0076] 3) The optimization design is carried out with the goal of maximizing the sum of the moment of inertia of the airfoil geometric coordinates about the X-axis and the moment of inertia about the Y-axis in order to improve the structural efficiency of the airfoil.
[0077] 4) Select a standard airfoil with a relatively larger thickness as the 25% thickness standard airfoil (corresponding to the second reference airfoil). To ensure geometric compatibility, airfoils with the same airfoil family number are preferred, such as the 25% thickness standard airfoil;
[0078] 5) Also using the chord position of the maximum thickness as the dividing line, the 25% thickness airfoil is divided into two parts, front and rear, and the XOY coordinate system (corresponding to the second reference system) is established with the chord position of the maximum thickness as the origin, and the coordinate point (x25i, y25i) of the rear half of the airfoil is selected, and the coordinate point (x25i, y25i) is scaled according to the maximum thickness ratio R of the design airfoil (relative thickness 21%) and the 25% thickness airfoil, to obtain the new coordinate (x25i, y25i*R);
[0079] Among them, the coordinate systems of the 21% thickness airfoil and the 25% thickness airfoil need to be calibrated for consistency, for example, the X axis should be along the chord direction of the airfoil, and the Y axis should be perpendicular to the chord direction. This step improves the calculation accuracy of the moment of inertia.
[0080] Among them, the moment of inertia reflects the structural stiffness of the airfoil, which is specifically manifested as the ability of the airfoil to resist bending and torsion. For a given airfoil, the moment of inertia I is related to the geometric distribution of the airfoil in a certain axial direction. For example, the moment of inertia IX about the X-axis describes the ability of the airfoil to resist bending along the chord direction (i.e., the X-axis direction), while the moment of inertia IY about the Y-axis reflects the ability of the airfoil to resist bending perpendicular to the chord direction (i.e., the Y-axis direction). The larger the moment of inertia, the stronger the airfoil's ability to resist deformation and the higher the structural stiffness. In addition, the thickness distribution of the airfoil, the curvature of the airfoil curve, and the geometric center position of the airfoil will affect the magnitude of the moment of inertia. For example, if the thickness distribution of the airfoil in the chord direction is more uniform, or there is a higher material distribution near the maximum thickness of the airfoil, this will result in a larger moment of inertia, thereby increasing the structural stiffness of the airfoil.
[0081] When designing an airfoil, it is necessary to find a balance between aerodynamic performance and structural performance. The optimization design with the goal of maximizing the sum of the moment of inertia of the airfoil geometric coordinates about the X-axis and the moment of inertia about the Y-axis means that the design process not only considers the aerodynamic efficiency and structural strength of the airfoil. This optimization strategy aims to make the airfoil have the best structural stability and the smallest possible weight while meeting the aerodynamic performance requirements.
[0082] It can be understood that the process of using the weighting coefficient C1 and the coordinate points (x21i, y21i) and (x25i, y21iR) of two airfoils with different thicknesses to obtain the geometric coordinates of the designed airfoil is actually a mixed design of the airfoil shape. In simple terms, it is to combine the shape features of the second half of the two airfoils together through linear combination, in order to obtain a new airfoil with good aerodynamic performance and structural efficiency.
[0083] Optionally, for example, based on the weighting coefficient C1, the geometric coordinates of the second half of the designed airfoil (x'i, y'i) = (x21i, y21i*C1+y25i*R*(1-C1)) are obtained, wherein the weighting coefficient C1 belongs to [0, 1], and after optimization, it can belong to [0.5, 0.9].
[0084] For example, according to the value of C1, (x'i, y'i) can have many different forms. For example:
[0085] If C1 = 0, then y'i will be exactly equal to the scaled y coordinate of the 25% thickness airfoil, i.e. y'i = y25_iR. This means that the shape of the rear half of the designed airfoil will completely adopt the rear half of the 25% thickness airfoil, which has a higher structural moment of inertia, but the aerodynamic performance may be affected.
[0086] If C1 = 1, then y'i will be exactly equal to the y coordinate of the 21% thickness airfoil, that is, y'i = y21_i. This means that the shape of the rear half of the designed airfoil will completely retain the rear half of the 21% thickness airfoil, which has better aerodynamic performance but may have lower structural efficiency.
[0087] If C1 takes a value between 0 and 1, for example C1 = 0.5, then y'i will be equal to the average of the y coordinates of the rear halves of the two airfoils, that is, y'i = 0.5 (y21_i) + 0.5 (y25_iR). The shape of the rear half of the airfoil designed in this way will be a compromise, trying to find a balance between aerodynamic performance and structural efficiency.
[0088] Assume x211 = 0.2, y211 = 0.021 (i.e. at 20% position on the chord line, the thickness of the 21% thickness airfoil is 2.1% of the chord length); at the same time, assume x251 = 0.2, y251 = 0.025, and the scaling ratio R = 0.85 (i.e. the thickness of the 25% thickness airfoil at the same position is 2.5% of the chord length, which is 2.125% after scaling);
[0089] If the weighting coefficient C1 is 0.7, the geometric coordinates of the designed airfoil calculated according to the above formula are: (0.2, 0.022375). This means that at the 20% position on the chord line, the thickness of the designed airfoil is about 2.2375% of the chord length, which is a thickness value between the 21% thickness airfoil and the scaled 25% thickness airfoil. By adjusting C1, the new coordinates of each point on the rear half of the airfoil can be obtained, and finally the complete geometric shape of the designed airfoil is formed. This design method achieves the best balance between aerodynamic performance and structural efficiency by mixing the characteristics of two airfoils with different thicknesses.
[0090] Based on the above, this application proposes a new airfoil geometry by weighted mixing of the coordinates of the second half of a 21% thick airfoil and a 25% thick airfoil. This airfoil attempts to improve structural efficiency while maintaining certain aerodynamic performance. Considering that the goal of airfoil design is to maximize the sum of the moment of inertia about the X-axis and the moment of inertia about the Y-axis, this application achieves this by selecting and adjusting C1. The weighting coefficient C1 determines the contribution of the second half of the two airfoils in the mixing process. C1 also affects the thickness distribution, curvature and other structural properties of the final airfoil. By selecting a suitable C1, the airfoil's ability to resist bending and torsion can be improved while meeting aerodynamic performance requirements, reducing material usage and reducing blade weight.
[0091] 6) Taking the target aerodynamic performance of the blade as a constraint, use aerodynamic performance analysis software such as RFOIL or XFOIL to calculate the aerodynamic parameters of the airfoil and analyze the aerodynamic performance.
[0092] Furthermore, after determining the optimization target and constraints (target aerodynamic performance of the blade), the intelligent optimization algorithm is used to calculate the optimal aerodynamic parameters including C1, etc. By automatically adjusting C1 and iteratively calculating, the airfoil geometry design that satisfies the maximum sum of moments of inertia under the aerodynamic performance constraints is found.
[0093] It is understandable that this process can have multiple optimization objectives in order to find the best balance between aerodynamic efficiency, structural efficiency and weight. For example, during the optimization process, after each adjustment of the geometric parameters of the airfoil, the sum of the moments of inertia of the X-axis and Y-axis and the aerodynamic parameters of the airfoil are recalculated. Through multiple iterations, the intelligent optimization algorithm gradually approaches the optimal solution, and finally obtains the airfoil design that achieves the best balance between aerodynamic performance and structural performance.
[0094] In summary, obtaining mixed geometric coordinates based on the coordinate points of the second half of the airfoil and the weighted coefficient C1 is a specific means to achieve airfoil optimization design, and taking the weighted coefficient C1 as the independent variable of the intelligent optimization algorithm, taking the maximum sum of moments of inertia as the goal, and optimizing with aerodynamic performance as the constraint is a strategy adopted in the entire design process to simultaneously improve aerodynamic performance and structural efficiency. These two work together to achieve the design goal.
[0095] 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.
[0096] In this embodiment, a device for determining the tip 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.
[0097] Figure 3 : is a structural block diagram of a device for determining a tip airfoil of a wind turbine blade according to an embodiment of the present application, the device comprising:
[0098] A selection module 32, configured to select a first reference airfoil and a second reference airfoil from preset standard airfoils, respectively, wherein the airfoil relative thickness of the first reference airfoil is smaller than the airfoil relative thickness of the second reference airfoil;
[0099] a determination module 34, configured to determine a first trailing edge geometric coordinate of the first reference airfoil in a first reference system, and to determine a second trailing edge geometric coordinate of the second reference airfoil in a second reference system;
[0100] An acquisition module 36, configured to acquire geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates;
[0101] The optimization module 38 is used to obtain target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia by iteratively optimizing the geometric coordinates to be optimized, and to determine the tip airfoil corresponding to the target geometric coordinates.
[0102] Through the above-mentioned device, a first reference airfoil and a second reference airfoil are respectively selected from preset standard airfoils, wherein the relative airfoil thickness of the first reference airfoil is less than the relative airfoil thickness of the second reference airfoil; the first trailing edge geometric coordinates of the first reference airfoil in the first reference system are determined, and the second trailing edge geometric coordinates of the second reference airfoil in the second reference system are determined; the geometric coordinates to be optimized are obtained after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; the target geometric coordinates that meet the aerodynamic performance constraints and have the maximum sum of moments of inertia are obtained by iteratively optimizing the geometric coordinates to be optimized, and the tip airfoil corresponding to the target geometric coordinates is determined. This scheme effectively improves the design flexibility and aerodynamic performance of the tip of the wind turbine blade by selecting reference airfoils of different thicknesses for weighted fusion, and then determines the tip airfoil that meets the aerodynamic performance constraints and has the maximum sum of moments of inertia through iterative optimization, while ensuring the structural strength and stability of the blade. By automatically adjusting the weighting coefficients and combining with the genetic optimization algorithm, the optimal airfoil can be found quickly and accurately, which significantly improves the design efficiency and blade performance, and provides new ideas and methods for the optimal design of wind turbine blades, thereby solving the problem that the tip airfoil of the blade cannot take into account both the aerodynamic performance and structural efficiency of the airfoil, and realizing a tip airfoil that takes into account both the aerodynamic performance and structural efficiency of the airfoil, thereby improving the efficiency and stability of wind power generation.
[0103] In an exemplary embodiment, the determination module is also used to: divide the first reference airfoil into a leading edge portion and a trailing edge portion according to a first maximum thickness position of the first reference airfoil; establish the first reference system by taking the first maximum thickness position as the origin, the direction along the chord direction of the first reference airfoil pointing to the trailing edge portion as the X-axis direction of the first reference system, and the direction perpendicular to the X-axis direction of the first reference system as the Y-axis direction of the first reference system; and determine the first trailing edge geometric coordinates based on the geometric coordinates of the trailing edge portion corresponding to the first reference system.
[0104] In an exemplary embodiment, the acquisition module is also used to: for the first vertical coordinate value of the first trailing edge geometric coordinate and the second vertical coordinate value of the second trailing edge geometric coordinate, linearly combine the first vertical coordinate value and the second vertical coordinate value by using a weighting coefficient to obtain the weighted fused geometric coordinate to be optimized.
[0105] In an exemplary embodiment, before linearly combining the first vertical coordinate value and the second vertical coordinate value by using a weighting coefficient, the acquisition module is further used to: determine the maximum thickness ratio between the airfoil relative thickness of the first reference airfoil and the airfoil relative thickness of the second reference airfoil; scale the second vertical coordinate value based on the maximum thickness ratio to obtain a third vertical coordinate value, and use the third vertical coordinate value to update the second vertical coordinate value.
[0106] In an exemplary embodiment, the optimization module is also used to: automatically adjust the weighting coefficients in the geometric coordinates to be optimized to obtain the adjusted geometric coordinates, calculate the sum of the moments of inertia corresponding to the adjusted geometric coordinates, and use aerodynamic performance analysis software to calculate the aerodynamic parameters of the wind turbine blade when it works based on the adjusted geometric coordinates; iteratively calculate the sum of the aerodynamic parameters and the moment of inertia based on a genetic optimization algorithm until the target geometric coordinates are obtained.
[0107] In an exemplary embodiment, after determining the first trailing edge geometric coordinates of the first reference airfoil in the first reference system and determining the second trailing edge geometric coordinates of the second reference airfoil in the second reference system, the determination module is further used to: standardize the coordinate data of the first trailing edge geometric coordinates and the coordinate data of the second trailing edge geometric coordinates to obtain first standardized trailing edge geometric coordinates and second standardized trailing edge geometric coordinates; respectively smooth the first standardized trailing edge geometric coordinates and the second standardized trailing edge geometric coordinates to obtain smoothed first trailing edge geometric coordinates and smoothed second trailing edge geometric coordinates; replace the first trailing edge geometric coordinates with the smoothed first trailing edge geometric coordinates, and replace the smoothed second trailing edge geometric coordinates with the smoothed second trailing edge geometric coordinates.
[0108] An embodiment of the present application further provides a computer-readable storage medium, in which a computer program is stored, wherein the computer program is configured to execute the steps of any of the above method embodiments when running.
[0109] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:
[0110] S1, selecting a first reference airfoil and a second reference airfoil respectively from preset standard airfoils, wherein the airfoil relative thickness of the first reference airfoil is smaller than the airfoil relative thickness of the second reference airfoil;
[0111] S2, determining a first trailing edge geometric coordinate of the first reference airfoil in a first reference system, and determining a second trailing edge geometric coordinate of the second reference airfoil in a second reference system;
[0112] S3, obtaining geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates;
[0113] S4, obtaining target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia by iteratively optimizing the geometric coordinates to be optimized, and determining a tip airfoil corresponding to the target geometric coordinates.
[0114] 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.
[0115] 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.
[0116] 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.
[0117] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:
[0118] S1, selecting a first reference airfoil and a second reference airfoil respectively from preset standard airfoils, wherein the airfoil relative thickness of the first reference airfoil is smaller than the airfoil relative thickness of the second reference airfoil;
[0119] S2, determining a first trailing edge geometric coordinate of the first reference airfoil in a first reference system, and determining a second trailing edge geometric coordinate of the second reference airfoil in a second reference system;
[0120] S3, obtaining geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates;
[0121] S4, obtaining target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia by iteratively optimizing the geometric coordinates to be optimized, and determining a tip airfoil corresponding to the target geometric coordinates.
[0122] 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.
[0123] 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.
[0124] 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.
[0125] 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.
[0126] For specific examples in this embodiment, reference may be made to the examples described in the above embodiments and exemplary implementation modes, and this embodiment will not be described in detail herein.
[0127] Obviously, those skilled in the art should understand that the above modules or steps of the present application can be implemented by a general computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, they can be implemented by a program code executable by a computing device, so that they can be stored in a storage device and executed by the computing device, and in some cases, the steps shown or described can be executed in a different order from that herein, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. Thus, the present application is not limited to any specific combination of hardware and software.
[0128] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.
Claims
1. A method for determining the tip airfoil of a wind turbine blade, characterized in that: include: Selecting a first reference airfoil and a second reference airfoil from preset standard airfoils, respectively, wherein the airfoil relative thickness of the first reference airfoil is smaller than the airfoil relative thickness of the second reference airfoil; Determining first trailing edge geometric coordinates of the first reference airfoil in a first reference system, and determining second trailing edge geometric coordinates of the second reference airfoil in a second reference system; Acquire geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; By iteratively optimizing the geometric coordinates to be optimized, target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia are obtained, and the tip airfoil corresponding to the target geometric coordinates is determined.
2. The method according to claim 1, characterized in that Determining a first trailing edge geometric coordinate of the first reference airfoil in a first reference system includes: dividing the first reference airfoil into a leading edge portion and a trailing edge portion according to a first maximum thickness position of the first reference airfoil; The first reference system is established by taking the first maximum thickness position as the origin, taking the direction along the chord direction of the first reference airfoil pointing to the trailing edge portion as the X-axis direction of the first reference system, and taking the direction perpendicular to the X-axis direction of the first reference system as the Y-axis direction of the first reference system; The first trailing edge geometric coordinates are determined based on the geometric coordinates of the trailing edge portion corresponding to the first reference system.
3. The method according to claim 1, characterized in that Obtaining the geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates, including: For the first vertical coordinate value of the first trailing edge geometric coordinate and the second vertical coordinate value of the second trailing edge geometric coordinate, the weighted fusion geometric coordinate to be optimized is obtained by linearly combining the first vertical coordinate value and the second vertical coordinate value using a weighting coefficient.
4. The method according to claim 3, characterized in that Before linearly combining the first vertical coordinate value and the second vertical coordinate value by using a weighting coefficient, the method further includes: determining a maximum thickness ratio between an airfoil relative thickness of the first reference airfoil and an airfoil relative thickness of the second reference airfoil; The second vertical coordinate value is scaled based on the maximum thickness ratio to obtain a third vertical coordinate value, and the second vertical coordinate value is updated using the third vertical coordinate value.
5. The method according to claim 1, characterized in that By iteratively optimizing the geometric coordinates to be optimized, the target geometric coordinates that meet the aerodynamic performance constraint conditions and have the maximum sum of inertia moments are obtained, including: Automatically adjusting the weighted coefficients in the geometric coordinates to be optimized to obtain adjusted geometric coordinates, calculating the sum of the moments of inertia corresponding to the adjusted geometric coordinates, and using aerodynamic performance analysis software to calculate the aerodynamic parameters of the wind turbine blade when it is working based on the adjusted geometric coordinates; The aerodynamic parameters and the sum of the moments of inertia are iteratively calculated based on a genetic optimization algorithm until the target geometric coordinates are obtained.
6. The method according to claim 1, characterized in that After determining the first trailing edge geometric coordinates of the first reference airfoil in the first reference system and determining the second trailing edge geometric coordinates of the second reference airfoil in the second reference system, the method further includes: Standardizing the coordinate data of the first trailing edge geometric coordinates and the coordinate data of the second trailing edge geometric coordinates to obtain first standardized trailing edge geometric coordinates and second standardized trailing edge geometric coordinates; The first standardized trailing edge geometric coordinates and the second standardized trailing edge geometric coordinates are respectively smoothed to obtain smoothed first trailing edge geometric coordinates and smoothed second trailing edge geometric coordinates; the first trailing edge geometric coordinates are replaced with the smoothed first trailing edge geometric coordinates, and the smoothed second trailing edge geometric coordinates are replaced with the smoothed second trailing edge geometric coordinates.
7. A device for determining the tip airfoil of a wind turbine blade, characterized in that: include: A selection module, used for selecting a first reference airfoil and a second reference airfoil from preset standard airfoils, respectively, wherein the airfoil relative thickness of the first reference airfoil is smaller than the airfoil relative thickness of the second reference airfoil; a determination module, configured to determine a first trailing edge geometric coordinate of the first reference airfoil in a first reference system, and to determine a second trailing edge geometric coordinate of the second reference airfoil in a second reference system; An acquisition module, configured to acquire the geometric coordinates to be optimized after weighted fusion of the first trailing edge geometric coordinates and the second trailing edge geometric coordinates; The optimization module is used to obtain target geometric coordinates that meet aerodynamic performance constraints and have a maximum sum of moments of inertia by iteratively optimizing the geometric coordinates to be optimized, and to determine the tip airfoil corresponding to the target geometric coordinates.
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.