Method and device for determining chord length of airfoil profile, storage medium and electronic equipment

Abstract

The embodiment of the invention provides an airfoil chord length determination method and device, a storage medium and electronic equipment, and the method comprises the steps: determining the airfoil chord length of a fan blade in the spanwise direction based on a first initial gradient; performing blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard or not; under the condition that the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, determining an airfoil chord length distribution rule of the fan blade according to the first initial gradient, and determining a target function corresponding to the airfoil chord length based on the airfoil chord length distribution rule, the target function is used for indicating the corresponding relation between the spanwise height of the fan blade and the chord length of the airfoil; and determining a target airfoil chord length of the target fan blade in the spanwise direction according to the target function.

Description

Technical Field

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

[0002] In the field of wind power generation, the design of wind turbine blades is the key to achieving efficient energy conversion. The geometric shape of the blades, especially the distribution of the chord length of the airfoil, is directly related to the aerodynamic performance, noise level and structural load of the wind turbine at different wind speeds. The design of traditional wind turbine blades, whether horizontal or vertical, is often based on standard airfoils, and the chord length distribution in the span direction of the blade is relatively simple or follows simple geometric rules, such as linear changes. Although this design meets the basic needs of wind power generation to a certain extent, it exposes obvious performance limitations when faced with complex and changeable natural wind field environments.

[0003] In vertical axis wind turbines, the chord length distribution of blades is particularly important for improving the wind-catching efficiency of blades and reducing structural loads. Traditional vertical axis blades mostly use a single airfoil or straight wing section distribution. This design results in low aerodynamic efficiency of blades at different wind speeds and is prone to excessive loads under strong wind conditions, affecting the stability and life of the wind turbine.

[0004] With regard to the problem in the prior art that the airfoil chord length distribution of the wind turbine blade cannot be flexibly determined, no effective solution has been proposed so far.

[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 method and device for determining the chord length of an airfoil, a storage medium, and an electronic device, so as to at least solve the problem in the prior art that the chord length distribution of the airfoil of a wind turbine blade cannot be flexibly determined.

[0007] According to one embodiment of the present application, a method for determining an airfoil chord length is provided, comprising: determining the airfoil chord length of a fan blade along a spanwise direction based on a first initial gradient; performing blade performance simulation calculations on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard; when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, determining a distribution law of the airfoil chord length of the fan blade according to the first initial gradient, and determining a target function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the target function is used to indicate the correspondence between the spanwise height and the airfoil chord length of the fan blade; and determining a target airfoil chord length of a target fan blade along the spanwise direction according to the target function.

[0008] In an exemplary embodiment, determining the airfoil chord length of a wind blade along the span direction based on a first initial gradient includes: determining a first chord length range of the airfoil chord length of each sample fan blade in a sample fan blade set; determining a first average chord length corresponding to the sample fan blade set based on the first chord length range; determining a first wind wheel solidity corresponding to the sample fan blade set based on the first average chord length; and determining the first initial gradient based on the first average chord length when the first wind wheel solidity meets a preset wind wheel solidity.

[0009] In an exemplary embodiment, determining the objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law includes: determining a first data point of the spanwise height of the fan blade and a second data point of the airfoil chord length corresponding to the first initial gradient; fitting the first data point and the second data point through an optimization algorithm to obtain a first function; determining the correlation coefficient between the fitted data point and the actual data point based on the first function, wherein the fitted data point is the data point of the spanwise height and the data point of the airfoil chord length corresponding to the first function, and the actual data point is the first data point and the second data point; when the correlation coefficient is greater than or equal to a preset threshold, determining the first function as the objective function.

[0010] In an exemplary embodiment, after determining whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the method further includes: determining whether the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard; determining the distribution law of the airfoil chord length of the fan blade according to the first initial gradient when it is determined that the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness; determining the airfoil chord length of the fan blade along the span direction according to the first gradient when it is determined that the angle of attack smoothness of the fan blade corresponding to the first initial gradient does not meet the preset angle of attack smoothness, wherein the first gradient is the gradient after adjusting the first initial gradient.

[0011] In an exemplary embodiment, before determining the airfoil chord length of the fan blade along the span direction according to the first gradient, the method further includes: obtaining an airfoil chord length parameter optimization table of the fan blade, wherein the airfoil chord length parameter optimization table is used to indicate information on changes in aerodynamic performance and structural performance of the blade during adjustment of the airfoil chord length of the fan blade; and adjusting the first initial gradient according to the airfoil chord length parameter optimization table to obtain the first gradient.

[0012] In an exemplary embodiment, after determining whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the method further includes: in a case where the aerodynamic performance of the fan blade corresponding to the first initial gradient does not meet the preset standard, adjusting the chord length range of the airfoil chord length of each sample fan blade in the sample fan blade set to obtain a second chord length range; determining a second average chord length corresponding to the sample fan blade set according to the second chord length range; determining a second wind wheel solidity corresponding to the sample fan blade set according to the second average chord length; in a case where the second wind wheel solidity meets the preset wind wheel solidity, determining a second initial gradient based on the second average chord length, and determining the airfoil chord length of the fan blade along the span direction based on the second initial gradient.

[0013] According to another embodiment of the present application, a device for determining the chord length of an airfoil is provided, comprising: a first determination module, for determining the chord length of an airfoil of a fan blade along a span direction based on a first initial gradient; a simulation module, for performing blade performance simulation calculations on the fan blade corresponding to the first initial gradient, so as to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard; a second determination module, for determining the distribution law of the airfoil chord length of the fan blade according to the first initial gradient when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, and determining an objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the objective function is used to indicate the corresponding relationship between the span height and the airfoil chord length of the fan blade; a third determination module, for determining a target airfoil chord length of a target fan blade along the span direction according to the objective function.

[0014] According to another embodiment of the present application, a computer-readable storage medium is provided, in which a computer program is stored, wherein the computer program is configured to execute the steps of any 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, and when the computer program is executed by a processor, the steps in any of the above method embodiments are implemented.

[0017] Through the present application, the airfoil chord length of the fan blade along the span direction is determined based on the first initial gradient; the blade performance simulation calculation is performed on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard; when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the airfoil chord length distribution law of the fan blade is determined according to the first initial gradient, and the objective function corresponding to the airfoil chord length is determined based on the airfoil chord length distribution law, wherein the objective function is used to indicate the correspondence between the span-wise height and the airfoil chord length of the fan blade; the target airfoil chord length of the target fan blade along the span direction is determined according to the objective function; that is, in an embodiment of the present application, an objective function is used to express the mathematical relationship between the span-wise height and the airfoil chord length, and then the airfoil chord length of the fan blade is determined according to the objective function. Therefore, the problem of being unable to flexibly determine the airfoil chord length distribution of the fan blade can be solved. 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 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.

[0020] Figure 1 It is a hardware structure block diagram of a computer device for determining a method for an airfoil chord length according to an embodiment of the present application;

[0021] Figure 2 is a flow chart (I) of a method for determining the chord length of an airfoil according to an embodiment of the present application;

[0022] Figure 3 is a flow chart (II) of a method for determining the chord length of an airfoil according to an embodiment of the present application;

[0023] Figure 4 is a schematic diagram of the relationship between the spanwise height and the chord length of the airfoil according to an embodiment of the present application;

[0024] Figure 5 It is a structural block diagram of a device for determining the chord length of an airfoil according to an embodiment of the present application. DETAILED DESCRIPTION

[0025] The embodiments of the present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0026] It should be noted that the terms "first", "second", etc. in the specification 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.

[0027] The method embodiments provided in the embodiments of the present application can be executed in a computer device or a similar computing device. Taking running on a computer device as an example, Figure 1 1 is a hardware structure block diagram of a computer device for determining a method for determining the chord length of an airfoil according to an embodiment of the present application. Figure 1 As shown, the computer device may include one or more ( Figure 1 Only one is shown in the figure) a processor 102 (the processor 102 may include but is not limited to a processing device such as a microprocessor MCU or a programmable logic device FPGA) and a memory 104 for storing data, wherein the above-mentioned computer device may also include a transmission device 106 and an input and 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 above-mentioned computer device. Figure 1 More or fewer components as shown, or with Figure 1 Different configurations shown.

[0028] 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 chord length of the airfoil in the embodiment of the present application. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, that is, to implement the above method. The memory 104 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some examples, the memory 104 may further include a memory remotely arranged relative to the processor 102, and these remote memories may be connected to the computer 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.

[0029] The transmission device 106 is used to receive or send data via a network. The above-mentioned network specific examples may include a wireless network provided by a communication provider of a computer device. 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.

[0030] In this embodiment, a method for determining the chord length of an airfoil is provided, which is applied to the above-mentioned computer device. Figure 2 is a flow chart (I) of a method for determining the chord length of an airfoil according to an embodiment of the present application, such as Figure 2 As shown, the process includes the following steps:

[0031] Step S202, determining the airfoil chord length of the fan blade along the span direction based on the first initial gradient;

[0032] In this step, the chord length distribution of the blade along the span direction (ie, the length direction of the blade) is preliminarily set by the first initial gradient. The chord length of the airfoil refers to the distance from the leading edge to the trailing edge of the blade airfoil.

[0033] Step S204, performing blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard;

[0034] After the first initial gradient is determined, the performance of the blade designed based on this gradient is evaluated through simulation calculation. Simulation calculation is a testing method in a virtual environment that can simulate the aerodynamic performance of the blade under different wind speeds and wind directions, such as key parameters such as lift, drag, torque, and power output. It can then be preliminarily determined whether the blade design can meet the expected performance requirements, such as whether it can maintain a high energy capture rate at low wind speeds, or maintain a low structural load at high wind speeds.

[0035] Step S206, when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, determining the airfoil chord length distribution law of the fan blade according to the first initial gradient, and determining the objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the objective function is used to indicate the corresponding relationship between the spanwise height of the fan blade and the airfoil chord length;

[0036] If the performance of the blade in step S204 meets the preset performance criteria, the successful model will be further analyzed to determine a more accurate chord length distribution law. This law will be expressed by an objective function, which is a mathematical relationship between spanwise height and airfoil chord length. It can describe the optimal law of blade chord length changing with height.

[0037] Step S208: determining a target airfoil chord length of a target wind turbine blade along a span direction according to the target function.

[0038] Through the above steps, the airfoil chord length of the fan blade along the span direction is determined based on the first initial gradient; the blade performance simulation calculation is performed on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard; when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the airfoil chord length distribution law of the fan blade is determined according to the first initial gradient, and the objective function corresponding to the airfoil chord length is determined based on the airfoil chord length distribution law, wherein the objective function is used to indicate the correspondence between the span height and the airfoil chord length of the fan blade; the target airfoil chord length of the target fan blade along the span direction is determined according to the objective function; that is, in an embodiment of the present application, an objective function is used to express the mathematical relationship between the span height and the airfoil chord length, and then the airfoil chord length of the fan blade is determined according to the objective function. Therefore, the problem of being unable to flexibly determine the airfoil chord length distribution of the fan blade can be solved.

[0039] In an exemplary embodiment, determining the airfoil chord length of a wind blade along the span direction based on a first initial gradient includes: determining a first chord length range of the airfoil chord length of each sample fan blade in a sample fan blade set; determining a first average chord length corresponding to the sample fan blade set based on the first chord length range; determining a first wind wheel solidity corresponding to the sample fan blade set based on the first average chord length; and determining the first initial gradient based on the first average chord length when the first wind wheel solidity meets a preset wind wheel solidity.

[0040] In an exemplary embodiment, a detailed method for determining the chord length of an airfoil of a wind turbine blade along a span direction based on a first initial gradient is defined as follows:

[0041] First, a blade set is selected from existing samples or designs. This set contains multiple representative blade samples. For each sample, the range of variation of its airfoil chord length is determined, that is, the first chord length range. The chord length range is determined based on the geometric characteristics of the blade, material properties, and expected working environment, such as changes in wind speed and wind direction.

[0042] After determining the chord length range for each sample, the average chord length of these samples is calculated. The calculation of the average chord length helps quantify the chord length distribution of the blade collection, thereby better understanding the average thickness and width of the blade in the span direction.

[0043] The rotor solidity describes the ratio of the blades covering the rotor surface area, which directly affects the efficiency and structural load of the wind turbine in the process of capturing wind. Based on the calculated first average chord length, the rotor solidity of the blade set is further determined. The calculation formula of the rotor solidity is usually the average chord length of all blades divided by the rotor diameter.

[0044] According to the calculation result of the wind rotor solidity, whether the wind rotor solidity meets the preset wind rotor solidity, if it meets the requirement, the first initial gradient is determined based on the first average chord length; if it does not meet the requirement, the chord length range of each sample is adjusted to redetermine the average chord length, and the first initial gradient is determined based on the redetermined average chord length.

[0045] Finally, based on the determined first initial gradient and average chord length, the airfoil chord length distribution along the blade span (i.e., blade length direction) will be calculated. This will enable accurate design of the blade geometry. The optimized airfoil chord length distribution will better adapt to the wind farm environment, improve the aerodynamic efficiency of the blade, reduce the structural load, and ensure the stable operation of the wind turbine.

[0046] The embodiment of the present application systematically analyzes the chord length range, average chord length and rotor solidity of the blade set, gradually refines to determine the initial gradient, and finally calculates the optimal airfoil chord length distribution of the blade along the span direction based on the gradient. This can not only improve the accuracy and efficiency of blade design, but also ensure the performance and safety of the wind turbine in actual operation.

[0047] In an exemplary embodiment, determining the objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law includes: determining a first data point of the spanwise height of the fan blade and a second data point of the airfoil chord length corresponding to the first initial gradient; fitting the first data point and the second data point through an optimization algorithm to obtain a first function; determining the correlation coefficient between the fitted data point and the actual data point based on the first function, wherein the fitted data point is the data point of the spanwise height and the data point of the airfoil chord length corresponding to the first function, and the actual data point is the first data point and the second data point; when the correlation coefficient is greater than or equal to a preset threshold, determining the first function as the objective function.

[0048] In the preparation stage of the optimization algorithm, a series of data points about the spanwise height of the blade (the first data point) and the corresponding airfoil chord length data points (the second data point) are first collected, representing the actual values ​​of the spanwise height and airfoil chord length of each part of the blade.

[0049] The optimization algorithm is an advanced tool for dealing with complex mathematical models and multivariable problems. It can learn from the data and fit the optimal mathematical expression. In this step, the optimization algorithm is applied to fit the collected spanwise height data points and airfoil chord length data points to determine a function (first function) that can best describe the mathematical relationship between the two. The fitting process will use the algorithm's iteration and optimization capabilities to screen and determine the function expression that best reflects the data pattern from a variety of possible function forms.

[0050] After the first function is determined, the degree of fit between the function and the actual data is evaluated. This step is achieved by calculating the correlation coefficient between the fitted data points and the actual data points. The correlation coefficient (usually expressed as R 2 ) is a statistic used to measure the correlation between the data points and the fitted model. 2 The closer the value is to 1, the better the fit between the model and the data, and the closer the distribution of the data points is to the points predicted by the model. By calculating the correlation coefficient, the fitting effect and prediction performance of the first function can be objectively evaluated.

[0051] The preset threshold is a criterion established during the design process to determine whether the fitting function meets the performance requirements. If the calculated correlation coefficient is greater than or equal to the preset threshold, it means that the first function is sufficiently accurate and effective in describing the relationship between the spanwise height of the blade and the chord length of the airfoil, so it can be determined as the target function.

[0052] The embodiment of the present application ensures the scientificity and reliability of the objective function by optimizing the algorithm and calculating the correlation coefficient, which can not only provide a more accurate and efficient design solution for wind turbine blades, but also promote the development of wind power generation technology, improve energy conversion efficiency, and reduce operation and maintenance costs.

[0053] In an exemplary embodiment, after determining whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the method further includes: determining whether the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard; determining the distribution law of the airfoil chord length of the fan blade according to the first initial gradient when it is determined that the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness; determining the airfoil chord length of the fan blade along the span direction according to the first gradient when it is determined that the angle of attack smoothness of the fan blade corresponding to the first initial gradient does not meet the preset angle of attack smoothness, wherein the first gradient is the gradient after adjusting the first initial gradient.

[0054] In the preliminary design stage, the airfoil chord length distribution of the blade has been determined through the first initial gradient, and preliminary performance simulation calculations have been performed on it. This verifies whether the design has achieved the preset performance indicators, such as power generation efficiency, noise level, structural strength, etc. If the performance meets the preset standards, it means that the preliminary design has theoretically achieved good aerodynamic performance and structural stability.

[0055] Angle of attack smoothness is a key factor in blade design. It is related to the degree of match between the blade and the wind direction during rotation, as well as the attachment and separation of the airflow on the blade surface. Blades with good smoothness can reduce aerodynamic drag and improve energy capture efficiency, while reducing structural loads and extending blade life. Therefore, after the performance is up to standard, the angle of attack smoothness of the blade needs to be further checked. If the angle of attack smoothness of the blade meets the preset standard, it means that the design also performs well in aerodynamic performance, and the working state of the blade at different wind speeds and wind directions will be more stable and efficient.

[0056] If the blade's angle of attack smoothness also meets the preset criteria, the blade's airfoil chord length distribution law will be determined based on the first initial gradient. This law will be used as the basis for subsequent design optimization, which describes how the blade's airfoil chord length changes with height along the span direction (i.e., from the root to the tip).

[0057] If the angle of attack smoothness of the blade does not meet the preset requirements when the performance meets the standards, the first initial gradient will be adjusted to form a new gradient parameter (first gradient), and the airfoil chord length distribution of the blade along the span direction will be recalculated based on this adjusted gradient. This process may be repeated until the angle of attack smoothness of the blade meets the preset standards. The purpose of adjusting the gradient parameters is to optimize the aerodynamic characteristics of the blade so that the blade can better match the changes in wind direction during rotation, thereby improving overall performance.

[0058] Through this series of steps, it is ensured that the wind turbine blade design not only meets the theoretical performance standards, but also maintains good angle of attack smoothness in practical applications, thereby achieving comprehensive optimization of the blade design.

[0059] In an exemplary embodiment, before determining the airfoil chord length of the fan blade along the span direction according to the first gradient, the method further includes: obtaining an airfoil chord length parameter optimization table of the fan blade, wherein the airfoil chord length parameter optimization table is used to indicate information on changes in aerodynamic performance and structural performance of the blade during adjustment of the airfoil chord length of the fan blade; and adjusting the first initial gradient according to the airfoil chord length parameter optimization table to obtain the first gradient.

[0060] The airfoil chord length parameter optimization table is constructed based on a large number of blade design cases and simulation data. It records the changing trends and specific values ​​of the blade's aerodynamic and structural performance during the process of adjusting the blade's airfoil chord length. Aerodynamic performance mainly includes lift coefficient, drag coefficient, torque coefficient, and power coefficient, while structural performance involves blade stress distribution, fatigue life, vibration characteristics, etc. This optimization table is equivalent to a database that contains a comprehensive evaluation of blade performance under different gradient changes.

[0061] After obtaining the optimization table, the data in it is used to adjust the first initial gradient of the preliminary design. This adjustment process is based on the relationship between blade performance and gradient changes in the optimization table. By consulting the specific values ​​in the table, we can understand how the aerodynamic and structural performance of the blade changes under different gradient settings, so as to adjust the gradient parameters in a targeted manner to pursue better comprehensive performance. The goal of adjusting the gradient is to maximize aerodynamic efficiency and maximize energy conversion while ensuring the stability and durability of the blade structure.

[0062] Through the above analysis and adjustment, an optimized new gradient, namely the first gradient, can be obtained.

[0063] In an exemplary embodiment, after determining whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the method further includes: in a case where the aerodynamic performance of the fan blade corresponding to the first initial gradient does not meet the preset standard, adjusting the chord length range of the airfoil chord length of each sample fan blade in the sample fan blade set to obtain a second chord length range; determining a second average chord length corresponding to the sample fan blade set according to the second chord length range; determining a second wind wheel solidity corresponding to the sample fan blade set according to the second average chord length; in a case where the second wind wheel solidity meets the preset wind wheel solidity, determining a second initial gradient based on the second average chord length, and determining the airfoil chord length of the fan blade along the span direction based on the second initial gradient.

[0064] When the performance of the initially designed blade does not meet the standard, we will return to the basic design parameter, the chord length of the blade airfoil, to re-evaluate and adjust it. This step involves redefining the chord length range of each sample blade in the sample wind turbine blade set, looking for a new chord length interval that may improve performance, thereby obtaining a second chord length range.

[0065] After the second chord length range is determined, the new average chord length of each sample wind turbine blade will be calculated to form the second average chord length. The average chord length is one of the key parameters of blade geometry design and directly affects the aerodynamic performance and structural characteristics of the blade.

[0066] The rotor solidity describes the proportion of the rotor surface area covered by the blades, which has a direct impact on the rotation efficiency and structural load of the blades. Based on the second mean chord length, the rotor solidity will be recalculated to obtain the second rotor solidity to reflect the new characteristics of the adjusted blade design.

[0067] After the second wind rotor solidity is determined, it is determined whether the second wind rotor solidity meets the preset wind rotor solidity. If it meets the requirements, a corresponding second initial gradient is determined again based on the second average chord length. This gradient will guide the distribution adjustment of the airfoil chord length in the span direction of the blade to meet the design requirements under the second wind rotor solidity. Based on this new gradient, the airfoil chord length of the wind turbine blade along the span direction will be recalculated and optimized. This process requires performance simulation calculations to be performed again to ensure that the adjusted design can meet the preset performance standards.

[0068] In order to better understand the process of the method for determining the chord length of the above-mentioned airfoil, the implementation method flow of determining the chord length of the above-mentioned airfoil 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.

[0069] In this embodiment, a method for determining the chord length of an airfoil is provided. Figure 3 is a flow chart (II) of a method for determining the chord length of an airfoil according to an embodiment of the present application, such as Figure 3 As shown, the specific steps are as follows:

[0070] Step S301, N standard airfoils are given;

[0071] Wherein, N is a positive integer, for example, 7.

[0072] Step S302: giving spanwise positions of N standard airfoils;

[0073] Step S303: giving a chord length range of each standard airfoil;

[0074] Step S304: calculating the average chord length;

[0075] Step S305: determining the solidity of the wind rotor, wherein the solidity of the wind rotor = average chord length / wind rotor diameter;

[0076] Step S306: the chord length of the airfoil is transitioned from the blade root to the blade tip in a gradient;

[0077] Step S307: establishing an airfoil chord length parameter optimization table;

[0078] Step S308: establishing an airfoil chord length transition rule table;

[0079] Step S309: blade performance simulation calculation;

[0080] Step S310: Determine whether the blade performance meets the preset expectations. If it does, execute step S311; otherwise, execute step S303;

[0081] Step S311: Check the smoothness of the angle of attack to determine whether it is smooth. If it is smooth, execute step S312; otherwise, execute step S306;

[0082] Step S312: determining the airfoil twist angle distribution;

[0083] Step S313: outputting the optimal blade geometry;

[0084] Step S314: polynomial fitting to obtain the optimal distribution curve.

[0085] Among them, the optimal distribution curve is as follows Figure 4 As shown, y is used to indicate the chord length and x is used to indicate the spanwise position.

[0086] 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 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 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.

[0087] In this embodiment, a device for determining the chord length of an airfoil 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 are not 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.

[0088] Figure 5 is a structural block diagram of a device for determining the chord length of an airfoil according to an embodiment of the present application, such as Figure 5 As shown, the device comprises:

[0089] A first determination module 52, configured to determine the airfoil chord length of the fan blade along the span direction based on the first initial gradient;

[0090] A simulation module 54, configured to perform blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard;

[0091] a second determination module 56, configured to determine, when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, a distribution law of the airfoil chord length of the fan blade according to the first initial gradient, and determine an objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the objective function is used to indicate a corresponding relationship between the spanwise height of the fan blade and the airfoil chord length;

[0092] The third determination module 58 is used to determine a target airfoil chord length of a target wind turbine blade along a span direction according to the target function.

[0093] Through the above-mentioned device, the airfoil chord length of the fan blade along the span direction is determined based on the first initial gradient; the blade performance simulation calculation is performed on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard; when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the airfoil chord length distribution law of the fan blade is determined according to the first initial gradient, and the target function corresponding to the airfoil chord length is determined based on the airfoil chord length distribution law, wherein the target function is used to indicate the correspondence between the span-wise height and the airfoil chord length of the fan blade; the target airfoil chord length of the target fan blade along the span direction is determined according to the target function; that is, in an embodiment of the present application, an objective function is used to express the mathematical relationship between the span-wise height and the airfoil chord length, and then the airfoil chord length of the fan blade is determined according to the objective function, thereby solving the problem of being unable to flexibly determine the airfoil chord length distribution of the fan blade.

[0094] In an exemplary embodiment, a first determination module 52 is used to determine a first chord length range of the airfoil chord length of each sample fan blade in a sample fan blade set; determine a first average chord length corresponding to the sample fan blade set based on the first chord length range; determine a first wind wheel solidity corresponding to the sample fan blade set based on the first average chord length; and determine the first initial gradient based on the first average chord length when the first wind wheel solidity meets a preset wind wheel solidity.

[0095] In an exemplary embodiment, the second determination module 56 is used to determine a first data point of the spanwise height of the fan blade and a second data point of the airfoil chord length corresponding to the first initial gradient; fit the first data point and the second data point through an optimization algorithm to obtain a first function; determine the correlation coefficient between the fitted data point and the actual data point according to the first function, wherein the fitted data point is the data point of the spanwise height and the data point of the airfoil chord length corresponding to the first function, and the actual data point is the first data point and the second data point; when the correlation coefficient is greater than or equal to a preset threshold, determine the first function as the objective function.

[0096] In an exemplary embodiment, the second determination module 56 is used to determine whether the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard; when it is determined that the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness, determine the airfoil chord length distribution law of the fan blade according to the first initial gradient; when it is determined that the angle of attack smoothness of the fan blade corresponding to the first initial gradient does not meet the preset angle of attack smoothness, determine the airfoil chord length of the fan blade along the span direction according to the first gradient, wherein the first gradient is the gradient after adjusting the first initial gradient.

[0097] In an exemplary embodiment, a first determination module 52 is used to obtain an airfoil chord length parameter optimization table of the fan blade, wherein the airfoil chord length parameter optimization table is used to indicate change information of the aerodynamic performance and structural performance of the blade during the process of adjusting the airfoil chord length of the fan blade; and the first initial gradient is adjusted according to the airfoil chord length parameter optimization table to obtain the first gradient.

[0098] In an exemplary embodiment, a first determination module 52 is used to adjust the chord length range of the airfoil chord length of each sample fan blade in the sample fan blade set to obtain a second chord length range when the aerodynamic performance of the fan blade corresponding to the first initial gradient does not meet a preset standard; determine a second average chord length corresponding to the sample fan blade set according to the second chord length range; determine a second wind wheel solidity corresponding to the sample fan blade set according to the second average chord length; determine a second initial gradient based on the second average chord length when the second wind wheel solidity meets a preset wind wheel solidity, and determine the airfoil chord length of the fan blade along the span direction based on the second initial gradient.

[0099] It should be noted that the above modules can be implemented by 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.

[0100] 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.

[0101] Optionally, in this embodiment, the storage medium may be configured to store program codes for executing the following steps:

[0102] S1, determining the airfoil chord length of the fan blade along the span direction based on the first initial gradient;

[0103] S2, performing blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard;

[0104] S3, when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, determining a distribution law of the airfoil chord length of the fan blade according to the first initial gradient, and determining a target function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the target function is used to indicate a corresponding relationship between the spanwise height of the fan blade and the airfoil chord length;

[0105] S4, determining a target airfoil chord length of a target fan blade along a spanwise direction according to the target function.

[0106] 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.

[0107] 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.

[0108] 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.

[0109] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:

[0110] S1, determining the airfoil chord length of the fan blade along the span direction based on the first initial gradient;

[0111] S2, performing blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard;

[0112] S3, when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, determining a distribution law of the airfoil chord length of the fan blade according to the first initial gradient, and determining a target function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the target function is used to indicate a corresponding relationship between the spanwise height of the fan blade and the airfoil chord length;

[0113] S4, determining a target airfoil chord length of a target fan blade along a spanwise direction according to the target function.

[0114] 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.

[0115] 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.

[0116] An embodiment of the present application also provides a computer program, which includes computer instructions 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.

[0117] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:

[0118] S1, determining the airfoil chord length of the fan blade along the span direction based on the first initial gradient;

[0119] S2, performing blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard;

[0120] S3, when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, determining a distribution law of the airfoil chord length of the fan blade according to the first initial gradient, and determining a target function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the target function is used to indicate a corresponding relationship between the spanwise height of the fan blade and the airfoil chord length;

[0121] S4, determining a target airfoil chord length of a target fan blade along a spanwise direction according to the target function.

[0122] 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.

[0123] 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.

[0124] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the principles of the present application shall be included in the protection scope of the present application.

Claims

1. A method for determining the chord length of an airfoil, characterized in that: include: Determining an airfoil chord length of the fan blade along the span direction based on the first initial gradient; Performing blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard; When the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, a distribution law of the airfoil chord length of the fan blade is determined according to the first initial gradient, and a target function corresponding to the airfoil chord length is determined based on the airfoil chord length distribution law, wherein the target function is used to indicate a corresponding relationship between the spanwise height of the fan blade and the airfoil chord length; A target airfoil chord length of a target fan blade along a span direction is determined according to the target function.

2. The method according to claim 1, characterized in that: Before determining the airfoil chord length of the wind turbine blade along the span direction based on the first initial gradient, the method further includes: Determine a first chord length range of an airfoil chord length of each sample fan blade in the sample fan blade set; Determine a first average chord length corresponding to the sample fan blade set according to the first chord length range; Determine a first wind wheel solidity corresponding to the sample wind turbine blade set according to the first average chord length; When the first wind rotor solidity meets a preset wind rotor solidity, the first initial gradient is determined based on the first average chord length.

3. The method according to claim 1, characterized in that Determining the objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law includes: Determine a first data point of the spanwise height of the fan blade and a second data point of the airfoil chord length corresponding to the first initial gradient; Fitting the first data point and the second data point by an optimization algorithm to obtain a first function; Determine the correlation coefficient between the fitting data point and the actual data point according to the first function, wherein the fitting data point is the data point of the spanwise height and the data point of the airfoil chord length corresponding to the first function, and the actual data point is the first data point and the second data point; When the correlation coefficient is greater than or equal to a preset threshold, the first function is determined to be the target function.

4. The method according to claim 1, characterized in that: After determining whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, the method further includes: When the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, determining whether the angle of attack smoothness of the fan blade meets the preset angle of attack smoothness; When it is determined that the angle-of-attack smoothness of the fan blade meets the preset angle-of-attack smoothness, determining the airfoil chord length distribution law of the fan blade according to the first initial gradient; When it is determined that the angle of attack smoothness of the fan blade corresponding to the first initial gradient does not meet the preset angle of attack smoothness, the airfoil chord length of the fan blade along the span direction is determined according to the first gradient, wherein the first gradient is the gradient after adjusting the first initial gradient.

5. The method according to claim 4, characterized in that Before determining the airfoil chord length of the fan blade along the span direction according to the first gradient, the method further includes: Obtaining an airfoil chord length parameter optimization table of the fan blade, wherein the airfoil chord length parameter optimization table is used to indicate information on changes in aerodynamic performance and structural performance of the blade during adjustment of the airfoil chord length of the fan blade; The first initial gradient is adjusted according to the airfoil chord length parameter optimization table to obtain the first gradient.

6. The method according to claim 1, characterized in that After determining whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets the preset standard, the method further includes: if the aerodynamic performance of the fan blade corresponding to the first initial gradient does not meet the preset standard, adjusting the chord length range of the airfoil chord length of each sample fan blade in the sample fan blade set to obtain a second chord length range; Determine a second average chord length corresponding to the sample fan blade set according to the second chord length range; Determining a second wind wheel solidity corresponding to the sample wind turbine blade set according to the second average chord length; When the second wind rotor solidity meets the preset wind rotor solidity, a second initial gradient is determined based on the second average chord length, and the airfoil chord length of the wind turbine blade along the span direction is determined based on the second initial gradient.

7. A device for determining the chord length of an airfoil, characterized in that: include: A first determination module, configured to determine an airfoil chord length of the fan blade along a span direction based on a first initial gradient; a simulation module, configured to perform blade performance simulation calculation on the fan blade corresponding to the first initial gradient to determine whether the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard; a second determination module, configured to determine, when the aerodynamic performance of the fan blade corresponding to the first initial gradient meets a preset standard, a distribution law of the airfoil chord length of the fan blade according to the first initial gradient, and determine an objective function corresponding to the airfoil chord length based on the airfoil chord length distribution law, wherein the objective function is used to indicate a corresponding relationship between the spanwise height of the fan blade and the airfoil chord length; The third determination module is used to determine a target airfoil chord length of a target wind turbine blade along a span direction according to the objective function.

8. 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 6 is executed when the program is executed.

9. An electronic device, comprising a memory and a processor, characterized in that: A computer program is stored in the memory, and the processor is configured to execute the method according to any one of claims 1 to 6 through the computer program.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the method according to any one of claims 1 to 6 is implemented.

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