Thickness determination method and device, storage medium and electronic device

Abstract

The embodiment of the application provides a thickness determination method and device, a storage medium and an electronic device, wherein the method comprises the following steps: determining a plurality of preset relative thicknesses of a target blade, and determining a spanwise position corresponding to each preset relative thickness; determining a spanwise position parameter table corresponding to the target blade according to the correspondence between each preset relative thickness and each spanwise position; and determining each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses. According to the above method, the problem of poor aerodynamic efficiency caused by the fact that the vertical axis blade in the related art is mostly provided with a straight wing section or a twisted wing section can be solved.

Description

Technical Field

[0001] The present application relates to the field of wind turbine blades, and in particular to a thickness determination method and device, a storage medium, and an electronic device. Background Art

[0002] Vertical-axis wind turbine blades are components mounted on the vertical axis of a wind turbine, capturing wind and converting it into mechanical energy. Unlike traditional horizontal-axis wind turbines, vertical-axis wind turbine blades are arranged vertically and typically have multiple blades that can be curved, straight, or fan-shaped. The design of vertical-axis wind turbine blades can be adjusted according to the direction and speed of the wind to maximize wind energy capture efficiency. This design offers several advantages over horizontal-axis wind turbines, including greater stability in changing wind directions, easier maintenance, and better suitability for installation in urban environments.

[0003] Traditional vertical-axis blades, often with straight or twisted sections, have poor aerodynamic efficiency. This design allows wind turbines to effectively capture wind energy regardless of wind direction and convert it into mechanical or electrical energy. This design is relatively simple and stable, but may not be as efficient as some newer horizontal-axis wind turbines.

[0004] Currently, no effective solution has been proposed to the problem of poor aerodynamic efficiency caused by the vertical axis blades in related technologies mostly using straight wing sections or twisted wing sections.

[0005] Therefore, it is necessary to improve the related technology to overcome the above-mentioned defects in the related technology. Summary of the Invention

[0006] The embodiments of the present application provide a thickness determination method and device, a storage medium, and an electronic device to at least solve the problem of poor aerodynamic efficiency caused by the vertical axis blades in the related art mostly using straight wing sections or twisted wing sections.

[0007] According to one embodiment of the present application, a thickness determination method is provided, comprising: determining multiple preset relative thicknesses of a target blade, and determining a spanwise position corresponding to each preset relative thickness; determining a spanwise position parameter table corresponding to the target blade based on a correspondence between each preset relative thickness and each spanwise position; and determining each target relative thickness corresponding to each spanwise position of the target blade based on the spanwise position parameter table and the multiple preset relative thicknesses.

[0008] In an exemplary embodiment, a spanwise position parameter table corresponding to the target blade is determined based on the correspondence between each preset relative thickness and each spanwise position, including: determining a functional relationship between the preset relative thickness corresponding to the target blade and the spanwise position based on the correspondence; determining a polynomial functional relationship corresponding to the preset relative thickness and the spanwise position based on the functional relationship; and determining the spanwise position parameter table based on the polynomial functional relationship.

[0009] In an exemplary embodiment, each target relative thickness corresponding to each spanwise position of the target blade is determined based on the spanwise position parameter table and the multiple preset relative thicknesses, including: constructing a three-dimensional geometric model of the target blade in target simulation software based on the spanwise position parameter table, and presetting environmental parameters corresponding to the target blade; performing a blade smoothness check on the three-dimensional geometric model; when it is determined that the three-dimensional geometric model passes the blade smoothness check, determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, wherein the blade performance includes at least: blade efficiency and blade load; when it is determined that the blade performance meets the target blade performance, determining each preset relative thickness as each target relative thickness corresponding to each spanwise position.

[0010] In an exemplary embodiment, the blade smoothness check is performed on the three-dimensional geometric model, including: determining whether there is an uneven area on the surface of the three-dimensional geometric model, wherein the uneven area is used to indicate a sharp edge area and / or a gap area on the surface of the three-dimensional geometric model; when it is determined that the uneven area exists on the surface of the three-dimensional geometric model, determining that the three-dimensional geometric model has failed the blade smoothness check; when it is determined that the uneven area does not exist on the surface of the three-dimensional geometric model, determining that the three-dimensional geometric model has passed the blade smoothness check.

[0011] In an exemplary embodiment, determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance includes: determining the lift and drag of the three-dimensional geometric model under the environmental parameter conditions; determining a lift-to-drag ratio corresponding to the three-dimensional geometric model based on the lift and the drag, and determining the blade efficiency of the three-dimensional geometric model based on the lift-to-drag ratio; and determining a first load of the three-dimensional geometric model under static conditions, and determining a second load of the three-dimensional geometric model under the environmental parameter conditions; determining a load distribution corresponding to the three-dimensional geometric model based on the first load and the second load, and determining the blade load based on the load distribution; determining whether the blade efficiency meets a preset blade efficiency range, and determining whether the blade load meets a preset blade load range; if it is determined that the blade efficiency meets the blade efficiency range and the blade load meets the blade load range, determining that the blade performance meets the target blade performance; if it is determined that the blade efficiency does not meet the blade efficiency range and / or the blade load does not meet the target blade load, determining that the blade performance does not meet the target blade performance.

[0012] In an exemplary embodiment, after determining that the three-dimensional geometric model passes the blade smoothness check and determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, the method further includes: when it is determined that the blade performance does not meet the target blade performance, determining a first relative thickness from the multiple preset relative thicknesses according to the spanwise position parameter table; modifying the first relative thickness and updating the spanwise position parameter table according to the modified first relative thickness; determining each target relative thickness corresponding to each spanwise position of the target blade according to the updated spanwise position parameter table and multiple second relative thicknesses, wherein the multiple second relative thicknesses include: the modified first relative thickness and other relative thicknesses from the multiple preset relative thicknesses except the first relative thickness.

[0013] According to another embodiment of the present application, a thickness determination device is provided, including: a first determination module, used to determine multiple preset relative thicknesses of a target blade, and determine the spanwise position corresponding to each preset relative thickness; a second determination module, used to determine a spanwise position parameter table corresponding to the target blade based on the correspondence between each preset relative thickness and each spanwise position; and a third determination module, used to determine each target relative thickness corresponding to each spanwise position of the target blade based on the spanwise position parameter table and the multiple preset relative thicknesses.

[0014] According to another embodiment of the present application, a computer-readable storage medium is provided, in which a computer program is stored. The computer program is configured to execute the steps of any one of the above method embodiments when run.

[0015] According to another embodiment of the present application, an electronic device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0016] According to another embodiment of the present application, a computer program product is provided, including a computer program, which implements the steps of any of the above method embodiments when executed by a processor.

[0017] Through the embodiments of the present application, multiple preset relative thicknesses of the target blade are determined, and the spanwise position corresponding to each preset relative thickness is determined; a spanwise position parameter table corresponding to the target blade is determined based on the correspondence between each preset relative thickness and each spanwise position; and each target relative thickness corresponding to each spanwise position of the target blade is determined based on the spanwise position parameter table and the multiple preset thicknesses. In other words, the embodiments of the present application determine a spanwise position parameter table corresponding to the target blade through the correspondence between each preset relative thickness and each spanwise position; and then determine each target relative thickness based on the spanwise position parameter table and the multiple preset relative thicknesses. Through the embodiments of the present application, the problem of poor aerodynamic efficiency caused by the vertical-axis blades in the related art mostly using straight wing sections or twisted wing sections can be solved, thereby improving the aerodynamic efficiency of the target blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] 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.

[0019] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] Figure 1 This is a hardware structure block diagram of a computer terminal device for a thickness determination method according to an embodiment of the present application;

[0021] Figure 2 is a flow chart of a method for determining thickness according to an embodiment of the present application;

[0022] Figure 3This is a flow chart of a wind turbine blade with gradually varying thickness according to an optional embodiment of the present application;

[0023] Figure 4 This is a schematic diagram of a gradient change of blade relative thickness and blade span according to an optional embodiment of the present application;

[0024] Figure 5 is a schematic diagram of a wind turbine blade with gradually varying thickness according to an optional embodiment of the present application;

[0025] Figure 6 is a partial schematic diagram of a blade according to an optional embodiment of the present application;

[0026] Figure 7 4 is a structural block diagram of a thickness determination device according to an embodiment of the present application. DETAILED DESCRIPTION

[0027] The embodiments of the present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0028] It should be noted that the terms "first", "second", etc. in the description and claims of this application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence.

[0029] The method embodiments provided in the embodiments of the present application can be executed in a computer terminal device or a similar computing device. Taking running on a computer terminal device as an example, Figure 1 This is a hardware structure block diagram of a computer terminal device for a thickness determination method according to an embodiment of the present application. Figure 1 As shown, the computer terminal device may include one or more ( Figure 1 Only one is shown) a processor 102 (the processor 102 may include but is not limited to a microprocessor MCU or a programmable logic device FPGA and other processing devices) and a memory 104 for storing data, wherein the above-mentioned computer terminal device may also include a transmission device 106 for communication functions and an input and output device 108. It will 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 above-mentioned computer terminal device. For example, the computer terminal device may also include Figure 1 More or fewer components than shown, or with Figure 1 Different configurations shown.

[0030] 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 thickness determination method in the embodiment of the present application. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, that is, implementing 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 located relative to the processor 102, and these remote memories can be connected to the computer terminal device 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.

[0031] The transmission device 106 is used to receive or send data via a network. Specific examples of the aforementioned network may include a wireless network provided by a communication provider of a computer terminal device. In one embodiment, the transmission device 106 includes a network interface controller (NIC), which can be connected to other network devices via a base station to enable communication with the Internet. In another embodiment, the transmission device 106 may be a radio frequency (RF) module, which is used to communicate with the Internet wirelessly.

[0032] In this embodiment, a method for determining thickness is provided. Figure 2 is a flow chart of a method for determining thickness according to an embodiment of the present application, such as Figure 2 As shown, the process includes the following steps:

[0033] Step S202, determining a plurality of preset relative thicknesses of the target blade, and determining a spanwise position corresponding to each preset relative thickness;

[0034] Step S204, determining a spanwise position parameter table corresponding to the target blade according to the correspondence between each preset relative thickness and each spanwise position;

[0035] Step S206 : determining each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses.

[0036] Through the above steps, multiple preset relative thicknesses of the target blade are determined, and the spanwise position corresponding to each preset relative thickness is determined; a spanwise position parameter table corresponding to the target blade is determined based on the corresponding relationship between each preset relative thickness and each spanwise position; and each target relative thickness corresponding to each spanwise position of the target blade is determined based on the spanwise position parameter table and the multiple preset thicknesses. In other words, the embodiment of the present application determines the spanwise position parameter table corresponding to the target blade through the corresponding relationship between each preset relative thickness and each spanwise position; and then determines each target relative thickness based on the spanwise position parameter table and the multiple preset relative thicknesses. Through the embodiment of the present application, the problem of poor aerodynamic efficiency caused by the vertical axis blades in the related art mostly using straight wing sections or twisted wing sections can be solved, thereby improving the aerodynamic efficiency of the target blade.

[0037] Optionally, the above-mentioned step S204 of determining the spanwise position parameter table corresponding to the target blade according to the correspondence between each preset relative thickness and each spanwise position includes: determining the functional relationship between the preset relative thickness corresponding to the target blade and the spanwise position according to the correspondence; determining a polynomial functional relationship expression corresponding to the preset relative thickness and the spanwise position according to the functional relationship; and determining the spanwise position parameter table according to the polynomial functional relationship expression.

[0038] It is understandable that the key parameters in blade design can be determined based on the relationship between the preset blade relative thickness and the blade spanwise position, specifically:

[0039] The spanwise position parameter table corresponding to the target blade is determined based on the correspondence between each preset relative thickness and each spanwise position: Based on a series of preset relative thickness values, these values ​​are set according to the requirements of blade performance optimization. For example, in order to improve blade efficiency and reduce load, the relative thickness of the blade root may be set to be larger, while the relative thickness of the tip may be set to be smaller. The designer also needs to set the spanwise position of the blade, that is, the various measurement points of the blade from the root to the tip. Now, these preset relative thickness values ​​need to be matched with the spanwise position of the blade to create a parameter table. This parameter table will list the relative thickness values ​​at each position on the blade, as well as possible other geometric parameters such as chord length, airfoil, etc.

[0040] Determining the functional relationship between the preset relative thickness and spanwise position: Once the relationship between relative thickness and spanwise position is established, the next step is to find a mathematical relationship, or functional relationship, between these data. Designers may observe a trend in relative thickness as spanwise position changes. For example, they may find that relative thickness decreases linearly or nonlinearly with increasing spanwise position. This step requires fitting the data to find a function that best describes this trend. This function can be a simple linear function or a more complex polynomial function, depending on the distribution and complexity of the data.

[0041] Determine the polynomial function relationship: If the functional relationship between the preset relative thickness and spanwise position is nonlinear, a polynomial function will be fit to the data. Statistical or machine learning methods, such as the least squares method, will be used to determine the coefficients of the polynomial function to ensure that the function best describes the relationship between the preset relative thickness and spanwise position.

[0042] Determine a spanwise position parameter table based on a polynomial function: Apply the determined polynomial function to each spanwise position on the blade to generate a detailed spanwise position parameter table. This parameter table contains the relative thickness values ​​and spanwise coordinates for each location on the blade. This parameter table can be used to guide the 3D modeling of the blade, ensuring that the geometry at each location meets the design requirements.

[0043] The entire process involves data analysis, mathematical modeling and parameter optimization, aiming to determine the geometric parameters of the blade through scientific methods to optimize blade performance.

[0044] Optionally, the above-mentioned step S206 determines each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the multiple preset relative thicknesses, including: constructing a three-dimensional geometric model of the target blade in the target simulation software according to the spanwise position parameter table, and presetting the environmental parameters corresponding to the target blade; performing a blade smoothness check on the three-dimensional geometric model; when it is determined that the three-dimensional geometric model passes the blade smoothness check, determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, wherein the blade performance includes at least: blade efficiency and blade load; when it is determined that the blade performance meets the target blade performance, determining each preset relative thickness as each target relative thickness corresponding to each spanwise position.

[0045] It will be appreciated that determining each target relative thickness corresponding to each spanwise position of the target blade based on the spanwise position parameter table and the plurality of preset relative thicknesses involves determining the target relative thickness of the blade at each spanwise position based on the design parameters (e.g., airfoil, chord length, angle of attack, etc.) in the spanwise position parameter table and the preset relative thickness distribution. Typically, this is achieved using a mathematical model (e.g., a quadratic function) or an optimization algorithm to ensure that the blade thickness varies gradually along the spanwise direction to optimize aerodynamic performance.

[0046] A 3D geometric model of the target blade is constructed in the target simulation software based on the spanwise position parameter table. Environmental parameters corresponding to the target blade are preset. Within the simulation software, a 3D model of the blade is created based on the parameter table data. This includes the blade's shape, dimensions, and geometric characteristics. The environmental parameters used in the simulation, such as wind speed, direction, temperature, and air pressure, are then set to reflect the actual blade's operating conditions.

[0047] The three-dimensional geometric model is subjected to a blade smoothness check. After the three-dimensional model is established, a smoothness check is performed to ensure that the blade surface is smooth without sudden changes and the airfoil transition is natural.

[0048] If the 3D geometric model passes the blade smoothness check, the blade performance of the 3D geometric model under the specified environmental parameters is determined to meet the target blade performance. After the model passes the smoothness check, the blade performance under the specified environmental parameters is evaluated through CFD and FEA simulations. This includes blade efficiency (such as lift-to-drag ratio or power coefficient) and blade loads (such as maximum stress, bending moment, and torque). The simulation results are compared with the target performance indicators to determine whether the design meets the requirements.

[0049] If the blade performance is determined to meet the target blade performance, each preset relative thickness is determined as the target relative thickness corresponding to each spanwise position. If the simulation shows that the blade performance meets or exceeds the design target, the preset relative thickness distribution is confirmed as the optimal design parameter. This means that the preset relative thickness value at each spanwise position will be used as the final designed blade thickness.

[0050] The above technical solution aims to use mathematical models and simulation technology to find a blade design that meets aerodynamic efficiency requirements while remaining within structural load limits. This process ensures that the blade is not only theoretically optimized but also delivers excellent performance and reliability in practical applications. Through repeated adjustments and optimization, the ideal blade design parameters can be gradually approached, ultimately resulting in a high-performance wind turbine blade.

[0051] Wherein, performing a blade smoothness check on the three-dimensional geometric model includes: determining whether there is an uneven area on the surface of the three-dimensional geometric model, wherein the uneven area is used to indicate a sharp edge area and / or a gap area on the surface of the three-dimensional geometric model; when it is determined that the uneven area exists on the surface of the three-dimensional geometric model, determining that the three-dimensional geometric model fails the blade smoothness check; when it is determined that the uneven area does not exist on the surface of the three-dimensional geometric model, determining that the three-dimensional geometric model passes the blade smoothness check.

[0052] Understandably, blade smoothness inspection is a crucial verification step in wind turbine blade design, ensuring that the blade's 3D geometry meets aerodynamic and structural design requirements for surface smoothness. Specifically, the 3D geometry model's surface quality is examined to identify any uneven areas. When inspecting blade smoothness, the surface quality of the 3D model must be reviewed to identify any uneven or discontinuous areas. These areas may include sharp edges, protrusions, depressions, or gaps. In actual blades, these features can cause airflow separation, vortices, or structural stress concentrations, reducing blade efficiency and increasing structural loads. Inspection methods may include: Visual inspection: Using the CAD software's rendering function, observe the blade surface from multiple angles to identify any obvious surface defects. Curvature analysis: Calculating the curvature of the model surface to check for continuity. Discontinuities or excessive curvature variations may indicate uneven surfaces. Mesh inspection: Analyzing the surface mesh used for simulation to ensure it is smooth and free of distorted or overlapping elements, which helps improve simulation accuracy.

[0053] If the 3D geometric model is found to have uneven surfaces, the blade smoothness check is determined to have failed. If the above inspection reveals uneven surfaces on the blade model, such as sharp edges or gaps, the 3D geometric model is considered to have failed the blade smoothness check. This means the model needs to be modified to eliminate surface defects and ensure the blade design is aerodynamically and structurally optimal.

[0054] If the 3D geometric model's surface is confirmed to have no uneven areas, the model is considered to have passed the blade smoothness inspection. Conversely, if the surface inspection results show no uneven areas, that is, the surface is smooth, the airfoil transition is natural, and there are no sharp edges or gaps, then the 3D geometric model can be considered to have passed the blade smoothness inspection. This indicates that the blade design meets the standard requirements for aerodynamic performance and structural integrity and can proceed to further performance evaluation or enter the manufacturing stage.

[0055] The blade smoothness check ensures that the 3D geometry model meets design requirements in terms of surface quality and geometric continuity. This is crucial for improving the blade's aerodynamic efficiency, reducing structural loads, and extending its service life. If the model fails the check, the designer must modify it until satisfactory smoothness is achieved before proceeding to the next stage of performance simulation and verification. This process may require multiple iterations until the design reaches its final optimized state.

[0056] Wherein, determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance includes: determining the lift and drag of the three-dimensional geometric model under the environmental parameter conditions; determining the lift-to-drag ratio corresponding to the three-dimensional geometric model based on the lift and the drag, and determining the blade efficiency of the three-dimensional geometric model based on the lift-to-drag ratio; and determining a first load of the three-dimensional geometric model under static conditions, and determining a second load of the three-dimensional geometric model under the environmental parameter conditions; determining a load distribution corresponding to the three-dimensional geometric model based on the first load and the second load, and determining the blade load based on the load distribution; determining whether the blade efficiency meets a preset blade efficiency range, and determining whether the blade load meets a preset blade load range; if it is determined that the blade efficiency meets the blade efficiency range and the blade load meets the blade load range, determining that the blade performance meets the target blade performance; if it is determined that the blade efficiency does not meet the blade efficiency range and / or the blade load does not meet the target blade load, determining that the blade performance does not meet the target blade performance.

[0057] It is understood that it is possible to evaluate whether the performance of a three-dimensional geometric model (i.e., a wind turbine blade) under specific environmental parameter conditions meets the design objectives, specifically:

[0058] Determine the lift and drag of the three-dimensional geometric model under the conditions of the environmental parameters: analyze the aerodynamic performance of the blade under different wind speeds, wind directions and atmospheric conditions through CFD (Computational Fluid Dynamics) simulation.

[0059] A lift-to-drag ratio corresponding to the three-dimensional geometric model is determined based on the lift and drag, and the blade efficiency of the three-dimensional geometric model is determined based on the lift-to-drag ratio. The lift-to-drag ratio is the ratio of lift to drag and reflects the aerodynamic efficiency of the blade. A higher lift-to-drag ratio indicates higher blade efficiency. After calculating the lift-to-drag ratio, it is compared with the expected blade efficiency range in the design objectives to assess whether the blade design achieves the expected aerodynamic performance.

[0060] Determine a first load on the three-dimensional geometric model under static conditions, and determine a second load on the three-dimensional geometric model under the environmental parameters. The first load refers to the load generated by the blade's inherent structure under static conditions, such as gravity. The second load refers to the external force applied to the blade under dynamic conditions, such as wind. Static and dynamic load analyses are performed using FEA (finite element analysis) software to assess the safety and stability of the blade structure.

[0061] Determine the load distribution corresponding to the 3D geometric model based on the first and second loads, and then determine the blade load based on the load distribution. Analyze the load distribution on the blade under static and dynamic conditions to determine the magnitude and direction of the loads acting on various parts of the blade. The load distribution diagram reveals how the load varies at different locations on the blade, which is key to assessing blade structural strength and optimizing its design.

[0062] Determine whether the blade efficiency meets the preset blade efficiency range and determine whether the blade load meets the preset blade load range: Compare the calculated blade efficiency and load with the efficiency and load ranges set in the design objectives to evaluate whether the design meets or exceeds the expected performance indicators. The efficiency and load ranges are set based on the blade's intended use and safety standards.

[0063] When it is determined that the blade efficiency meets the blade efficiency range and the blade load meets the target blade load, it is determined that the blade performance meets the target blade performance: if the blade efficiency and load both meet the design targets, it is proved that the blade design has met the expectations in terms of aerodynamic performance and structural strength, and therefore the blade performance meets the target blade performance.

[0064] When it is determined that the blade efficiency does not meet the blade efficiency range and / or the blade load does not meet the target blade load, it is determined that the blade performance does not meet the target blade performance: conversely, if any one of the blade efficiency or load indicators does not meet the design target, it indicates that there are deficiencies in some aspects of the blade design and further optimization or adjustment is required.

[0065] This technical solution systematically evaluates the performance of blade designs under varying environmental parameters, ensuring both aerodynamic efficiency and structural safety. If design deficiencies are identified, the design phase can be re-designed, with adjustments to geometric parameters or material properties, followed by further simulation and performance evaluation until satisfactory blade performance is achieved.

[0066] Wherein, when it is determined that the three-dimensional geometric model passes the blade smoothness inspection, after determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, the method further includes: when it is determined that the blade performance does not meet the target blade performance, determining a first relative thickness from the multiple preset relative thicknesses according to the spanwise position parameter table; modifying the first relative thickness, and updating the spanwise position parameter table according to the modified first relative thickness; determining each target relative thickness corresponding to each spanwise position of the target blade according to the updated spanwise position parameter table and multiple second relative thicknesses, wherein the multiple second relative thicknesses include: the modified first relative thickness and other relative thicknesses from the multiple preset relative thicknesses except the first relative thickness.

[0067] It is understandable that during the blade design optimization process, when the preliminary designed 3D geometric model does not meet the performance target, iterative design and parameter adjustment can be performed, specifically:

[0068] If the 3D geometric model passes the blade fairing check, the blade performance under the environmental parameters is determined to meet the target blade performance. After confirming that the blade model has no geometric defects (i.e., passes the fairing check), the next step is to evaluate whether the blade performance under the set environmental conditions meets the design objectives. If the blade performance does not meet the target performance, i.e., the blade efficiency is lower than expected or the blade load exceeds the safe range, the designer needs to modify and optimize the model.

[0069] If it is determined that the blade performance does not meet the target blade performance, a first relative thickness is determined from the plurality of preset relative thicknesses according to the spanwise position parameter table. When the blade performance does not meet the target, a parameter needs to be selected for adjustment. The first relative thickness mentioned here generally refers to the thickness at a specific spanwise position of the blade, which may be a key point in the design that is considered to have a significant impact on the blade performance.

[0070] Modify the first relative thickness and update the spanwise position parameter table based on the modified first relative thickness: After modifying the first relative thickness, the designer needs to update the parameter table to ensure that all relevant geometric parameters (such as chord length, airfoil, etc.) match the modified first relative thickness. This may involve adjusting the coefficients in the polynomial function relationship to reflect the new relative thickness distribution.

[0071] Each target relative thickness corresponding to each spanwise position of the target blade is determined based on the updated spanwise position parameter table and a plurality of second relative thicknesses, wherein the plurality of second relative thicknesses include: the modified first relative thickness and other relative thicknesses of the plurality of preset relative thicknesses except the first relative thickness. After updating the parameter table, the designer recalculates the relative thickness distribution of the blade to ensure that the geometry of the entire blade matches the modified parameters. The plurality of second relative thicknesses refers to the thickness distribution of the entire blade along the spanwise direction after the first relative thickness is adjusted, including the adjusted first relative thickness and the relative thicknesses at other positions that have not been modified.

[0072] Based on the results of the blade performance evaluation, key parameters can be selected for adjustment, and the model can then be rebuilt to evaluate smoothness and performance. This process may require multiple iterations until the blade performance meets the design requirements. In this way, the blade design can be systematically optimized to ensure that the blade is not only geometrically smooth but also optimal in terms of aerodynamic efficiency and structural loads.

[0073] In order to better understand the process of the above-mentioned thickness determination method, the implementation method flow of the above-mentioned thickness determination is described below in combination with an optional embodiment, but it is not used to limit the technical solution of the embodiment of the present application.

[0074] In order to solve the problem of blade aerodynamic efficiency, Figure 5 is a schematic diagram of a wind turbine blade with gradually varying thickness according to an optional embodiment of the present application. Figure 6 is a partial schematic diagram of a blade according to an optional embodiment of the present application, such as Figure 5 、 Figure 6 As shown, an optional embodiment of the present application proposes a vertical axis fan blade using a combination of airfoils of different relative thicknesses, which can significantly improve the aerodynamic efficiency of the blade and reduce the blade load.

[0075] Figure 3 This is a flow chart of a wind turbine blade with a gradient thickness according to an optional embodiment of the present application. Figure 3 As shown:

[0076] Step S301, seven standard airfoils are given;

[0077] Step S302 , determining the relative thicknesses of the airfoil as 100%C, 40%C, 35%C, 30%C, 25%C, 21%C, and 16%C.

[0078] Step S303, preliminarily setting the spanwise positions of seven standard airfoils;

[0079] Step S304, constructing an airfoil spanwise position parameter table;

[0080] Step S305, blade performance simulation calculation;

[0081] Step S306, determining whether the relative thickness of the blade is optimal;

[0082] If it is determined to be optimal, step S307 is executed; if it is determined not to be optimal, step S304 is executed again;

[0083] Step S307, blade geometric smoothness inspection;

[0084] Step S308, determining again whether the relative thickness of the blade is optimal;

[0085] If it is determined to be optimal, step S309 is executed; if it is determined not to be optimal, step S304 is executed again;

[0086] The relative thickness of the airfoil decreases as the blade span increases, the relative thickness is large at the blade root, and the relative thickness is small at the outer blade span.

[0087] Step S309, re-performing blade performance simulation;

[0088] Step S310, outputting the optimal blade geometry;

[0089] Step S311, determining the airfoil relative thickness distribution;

[0090] Step S312: polynomial fitting to obtain an optimal distribution curve.

[0091] Figure 4 : is a schematic diagram of a blade relative thickness and blade length gradient change according to an optional embodiment of the present application, such as Figure 4 As shown in Figure 1, the optimal distribution curve is obtained by fitting a polynomial function relationship.

[0092] 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 the necessary general hardware platform, and of course it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this 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 enabling a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods described in each embodiment of the present application.

[0093] In this embodiment, a device for determining thickness is also provided, which is used to implement the above-mentioned embodiments and preferred embodiments. Details already described are omitted for clarity. As used below, the term "module" may refer to 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, implementation using hardware, or a combination of software and hardware, is also possible and contemplated.

[0094] Figure 7 is a structural block diagram of a device for determining thickness according to an embodiment of the present application, such as Figure 7 As shown, the device includes:

[0095] A first determining module 72 is configured to determine a plurality of preset relative thicknesses of a target blade and determine a spanwise position corresponding to each preset relative thickness;

[0096] A second determining module 74 is configured to determine a spanwise position parameter table corresponding to the target blade according to a correspondence between each preset relative thickness and each spanwise position;

[0097] The third determining module 76 is configured to determine each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses.

[0098] Through the above-mentioned device, multiple preset relative thicknesses of the target blade are determined, and the spanwise position corresponding to each preset relative thickness is determined; based on the corresponding relationship between each preset relative thickness and each spanwise position, a spanwise position parameter table corresponding to the target blade is determined; and based on the spanwise position parameter table and the multiple preset thicknesses, each target relative thickness corresponding to each spanwise position of the target blade is determined. In other words, the embodiment of the present application determines the spanwise position parameter table corresponding to the target blade through the corresponding relationship between each preset relative thickness and each spanwise position; and then determines each target relative thickness based on the spanwise position parameter table and the multiple preset relative thicknesses. Through the embodiment of the present application, the problem of poor aerodynamic efficiency caused by the vertical axis blades in the related art mostly using straight wing sections or twisted wing sections can be solved, thereby improving the aerodynamic efficiency of the target blade.

[0099] In an exemplary embodiment, the second determination module 74 is further used to determine the functional relationship between the preset relative thickness and the spanwise position corresponding to the target blade based on the corresponding relationship; determine a polynomial functional relationship corresponding to the preset relative thickness and the spanwise position based on the functional relationship; and determine the spanwise position parameter table based on the polynomial functional relationship.

[0100] In an exemplary embodiment, the third determination module 76 is further used to construct a three-dimensional geometric model of the target blade in the target simulation software according to the spanwise position parameter table, and preset the environmental parameters corresponding to the target blade; perform a blade smoothness check on the three-dimensional geometric model; when it is determined that the three-dimensional geometric model passes the blade smoothness check, determine whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, wherein the blade performance includes at least: blade efficiency and blade load; when it is determined that the blade performance meets the target blade performance, determine each preset relative thickness as each target relative thickness corresponding to each spanwise position.

[0101] In an exemplary embodiment, the third determination module 76 is also used to determine whether there is an uneven area on the surface of the three-dimensional geometric model, wherein the uneven area is used to indicate the sharp edge area and / or gap area on the surface of the three-dimensional geometric model; when it is determined that the uneven area exists on the surface of the three-dimensional geometric model, it is determined that the three-dimensional geometric model fails the blade smoothness check; when it is determined that the uneven area does not exist on the surface of the three-dimensional geometric model, it is determined that the three-dimensional geometric model passes the blade smoothness check.

[0102] In an exemplary embodiment, the third determination module 76 is further used to determine the lift and drag of the three-dimensional geometric model under the conditions of the environmental parameters; determine the lift-to-drag ratio corresponding to the three-dimensional geometric model based on the lift and the drag, and determine the blade efficiency of the three-dimensional geometric model based on the lift-to-drag ratio; and determine a first load of the three-dimensional geometric model under static conditions, and determine a second load of the three-dimensional geometric model under the conditions of the environmental parameters; determine a load distribution corresponding to the three-dimensional geometric model based on the first load and the second load, and determine the blade load based on the load distribution; determine whether the blade efficiency meets a preset blade efficiency range, and determine whether the blade load meets a preset blade load range; if it is determined that the blade efficiency meets the blade efficiency range and the blade load meets the blade load range, determine that the blade performance meets the target blade performance; if it is determined that the blade efficiency does not meet the blade efficiency range and / or the blade load does not meet the target blade load, determine that the blade performance does not meet the target blade performance.

[0103] In an exemplary embodiment, the third determination module 76 is further used to, when it is determined that the blade performance does not meet the target blade performance, determine a first relative thickness from the multiple preset relative thicknesses according to the spanwise position parameter table; modify the first relative thickness and update the spanwise position parameter table according to the modified first relative thickness; and determine each target relative thickness corresponding to each spanwise position of the target blade according to the updated spanwise position parameter table and multiple second relative thicknesses, wherein the multiple second relative thicknesses include: the modified first relative thickness and other relative thicknesses from the multiple preset relative thicknesses except the first relative thickness.

[0104] It should be noted that the above modules can be implemented through software or hardware. For the latter, it can be implemented in the following ways, but not limited to: the above modules are all located in the same processor; or the above modules are located in different processors in any combination.

[0105] An embodiment of the present application further provides a computer-readable storage medium, in which a computer program is stored. The computer program is configured to execute the steps of any of the above method embodiments when run.

[0106] Optionally, in this embodiment, the storage medium may be configured to store program codes for executing the following steps:

[0107] S1, determining a plurality of preset relative thicknesses of a target blade, and determining a spanwise position corresponding to each preset relative thickness;

[0108] S2, determining a spanwise position parameter table corresponding to the target blade according to a correspondence between each preset relative thickness and each spanwise position;

[0109] S3 , determining each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses.

[0110] 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.

[0111] An embodiment of the present application further provides an electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0112] 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.

[0113] Optionally, in this embodiment, the processor may be configured to execute the following steps through a computer program:

[0114] S1, determining a plurality of preset relative thicknesses of a target blade, and determining a spanwise position corresponding to each preset relative thickness;

[0115] S2, determining a spanwise position parameter table corresponding to the target blade according to a correspondence between each preset relative thickness and each spanwise position;

[0116] S3 , determining each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses.

[0117] 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.

[0118] An embodiment of the present application further provides another computer program product, comprising 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 of any of the above method embodiments are implemented.

[0119] 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 of any of the above method embodiments.

[0120] Optionally, in this embodiment, the processor may be configured to execute the following steps through a computer program:

[0121] S1, determining a plurality of preset relative thicknesses of a target blade, and determining a spanwise position corresponding to each preset relative thickness;

[0122] S2, determining a spanwise position parameter table corresponding to the target blade according to a correspondence between each preset relative thickness and each spanwise position;

[0123] S3 , determining each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses.

[0124] 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 here.

[0125] Obviously, those skilled in the art should understand that the modules or steps of the present application described above can be implemented using a general-purpose computing device, they can be concentrated on a single computing device, or distributed across a network composed of multiple computing devices, they can be implemented using program code executable by the computing device, and thus, 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 performed in a different order than herein, or they can be fabricated into separate integrated circuit modules, or multiple modules or steps can be fabricated into a single integrated circuit module for implementation. Thus, the present application is not limited to any specific combination of hardware and software.

[0126] The above description is merely a preferred embodiment of the present application and is not intended to limit the present application. Various modifications and variations are possible for those skilled in the art. Any modifications, equivalent substitutions, improvements, etc. made within the principles of the present application shall be included within the scope of protection of the present application.

Claims

1. A method for determining thickness, characterized in that: include: Determining a plurality of preset relative thicknesses of a target blade, and determining a spanwise position corresponding to each preset relative thickness; Determining a spanwise position parameter table corresponding to the target blade according to a correspondence between each preset relative thickness and each spanwise position; Determine each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses; Wherein, determining the spanwise position parameter table corresponding to the target blade according to the correspondence between each preset relative thickness and each spanwise position includes: Determining a functional relationship between a preset relative thickness and a spanwise position corresponding to the target blade according to the corresponding relationship; Determine a polynomial function relationship between the preset relative thickness and the spanwise position according to the function relationship; The spanwise position parameter table is determined according to the polynomial function relationship.

2. The method according to claim 1, characterized in that Determining each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses includes: Constructing a three-dimensional geometric model of the target blade in target simulation software according to the spanwise position parameter table, and presetting environmental parameters corresponding to the target blade; Performing a blade smoothness inspection on the three-dimensional geometric model; If it is determined that the three-dimensional geometric model passes the blade fairing inspection, determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, wherein the blade performance includes at least: blade efficiency and blade load; When it is determined that the blade performance meets the target blade performance, each preset relative thickness is determined as each target relative thickness corresponding to each spanwise position.

3. The method according to claim 2, characterized in that Performing a blade smoothness check on the three-dimensional geometric model includes: Determining whether there is an uneven area on the surface of the three-dimensional geometric model, wherein the uneven area is used to indicate a sharp edge area and / or a gap area on the surface of the three-dimensional geometric model; In the case where it is determined that the uneven area exists on the surface of the three-dimensional geometric model, determining that the three-dimensional geometric model fails the blade smoothness inspection; If it is determined that the surface of the three-dimensional geometric model does not have the uneven region, it is determined that the three-dimensional geometric model passes the blade smoothness inspection.

4. The method according to claim 2, characterized in that Determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance includes: determining the lift and drag of the three-dimensional geometric model under the conditions of the environmental parameters; determining a lift-to-drag ratio corresponding to the three-dimensional geometric model according to the lift and the drag, and determining a blade efficiency of the three-dimensional geometric model according to the lift-to-drag ratio; and determining a first load of the three-dimensional geometric model under static conditions, and determining a second load of the three-dimensional geometric model under conditions of the environmental parameters; determining a load distribution corresponding to the three-dimensional geometric model according to the first load and the second load, and determining the blade load according to the load distribution; determining whether the blade efficiency meets a preset blade efficiency range, and determining whether the blade load meets a preset blade load range; When it is determined that the blade efficiency meets the blade efficiency range and the blade load meets the blade load range, determining that the blade performance meets the target blade performance; When it is determined that the blade efficiency does not comply with the blade efficiency range and / or the blade load does not comply with the target blade load, it is determined that the blade performance does not comply with the target blade performance.

5. The method according to claim 2, characterized in that When it is determined that the three-dimensional geometric model passes the blade fairness inspection, after determining whether the blade performance of the three-dimensional geometric model under the environmental parameter conditions meets the target blade performance, the method further includes: In a case where it is determined that the blade performance does not meet the target blade performance, determining a first relative thickness from among the plurality of preset relative thicknesses according to the spanwise position parameter table; Modifying the first relative thickness and updating the spanwise position parameter table according to the modified first relative thickness; Each target relative thickness corresponding to each spanwise position of the target blade is determined according to the updated spanwise position parameter table and a plurality of second relative thicknesses, wherein the plurality of second relative thicknesses include: the modified first relative thickness and other relative thicknesses of the plurality of preset relative thicknesses except the first relative thickness.

6. A device for determining thickness, characterized in that: include: A first determining module is configured to determine a plurality of preset relative thicknesses of a target blade and determine a spanwise position corresponding to each preset relative thickness; A second determining module is configured to determine a spanwise position parameter table corresponding to the target blade according to a correspondence between each preset relative thickness and each spanwise position; a third determining module, configured to determine each target relative thickness corresponding to each spanwise position of the target blade according to the spanwise position parameter table and the plurality of preset relative thicknesses; Among them, the second determination module is also used to determine the functional relationship between the preset relative thickness and the spanwise position corresponding to the target blade according to the corresponding relationship; determine the polynomial functional relationship corresponding to the preset relative thickness and the spanwise position according to the functional relationship; and determine the spanwise position parameter table according to the polynomial functional relationship.

7. A computer-readable storage medium, characterized in that: The computer-readable storage medium includes a stored program, wherein the method according to any one of claims 1 to 5 is executed when the program is executed.

8. 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 5 through the computer program.

9. A computer program product comprising a computer program, characterized in that The computer program causes a processor to execute the steps of the method according to any one of claims 1 to 5.

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