Aerofoil profile aerodynamic characteristic data correction method and device and storage medium

Abstract

The invention provides a method and device for correcting aerodynamic characteristic data of an airfoil profile and a storage medium, and the method for correcting the aerodynamic characteristic data of the airfoil profile comprises the steps: obtaining original aerodynamic characteristic data and finishing paint aerodynamic characteristic data of a reference airfoil profile, the finishing paint aerodynamic characteristic data is data obtained by carrying out an aerodynamic characteristic experiment on a reference airfoil model covered with finishing paint, and the reference airfoil model is an equal airfoil polishing model with a reference airfoil; fitting the original aerodynamic characteristic data and the finishing paint aerodynamic characteristic data of the reference airfoil profile to obtain corrected parameters; acquiring original aerodynamic characteristic data of the target airfoil; and correcting the original aerodynamic characteristic data of the target airfoil according to the correction parameters to obtain corrected aerodynamic characteristic data of the target airfoil. According to the invention, the influence of the finish paint on the aerodynamic performance of the blade can be determined, the cognition on the running state of the blade and a unit is improved, and the simulation and test consistency of the blade and the whole machine is improved.

Description

Technical Field

[0001] The present disclosure relates to the field of wind power generation, and more particularly, to a method, device, and storage medium for correcting airfoil aerodynamic characteristic data. Background Art

[0002] At present, the single-unit capacity of wind turbines is increasing day by day, and the blades are getting longer and longer. The blade is a crucial component of a wind turbine, and the aerodynamic performance of the blade directly affects the power generation efficiency of the wind turbine. The blade design is based on the Blade Element Momentum Theory (BEM), which is interpolated by several standard airfoils and designed for relative thickness, chord length, and twist angle with several standard airfoils distributed in a certain spanwise direction (the length direction in which the blade extends). Therefore, the aerodynamic performance of the selected standard airfoil determines the aerodynamic performance of the blade, and the aerodynamic characteristic data of the airfoil is important data for measuring the aerodynamic performance of the airfoil. Therefore, to understand the aerodynamic performance of the blade, it is necessary to first understand the aerodynamic characteristic data of the standard airfoil.

[0003] Currently, wind tunnel experiments are a relatively reliable technical means to obtain airfoil aerodynamic characteristic data. However, the airfoil models used in the experiments are all finely polished and processed to ensure the maximum consistency with the theory of the blade shape, while the blades actually applied to wind turbines are also covered with topcoats. It is not clear what impact the topcoat will have on the airfoil aerodynamic characteristic data and the blade aerodynamic performance, but there is little research on this in the industry at present. Summary of the Invention

[0004] Therefore, how to understand the aerodynamic characteristic data of the airfoil covered with the topcoat is crucial for clarifying the impact of the topcoat on the blade aerodynamic performance.

[0005] In one general aspect, a method for correcting airfoil aerodynamic characteristic data is provided. The method for correcting airfoil aerodynamic characteristic data includes: obtaining the original aerodynamic characteristic data of a reference airfoil and the topcoat aerodynamic characteristic data, where the topcoat aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with the topcoat, and the reference airfoil model is an equal-airfoil polished model having the reference airfoil; performing a fitting process on the original aerodynamic characteristic data of the reference airfoil and the topcoat aerodynamic characteristic data to obtain a correction parameter; obtaining the original aerodynamic characteristic data of a target airfoil; and performing a correction process on the original aerodynamic characteristic data of the target airfoil according to the correction parameter to obtain the corrected aerodynamic characteristic data of the target airfoil.

[0006] Optionally, the aerodynamic characteristic data of the topcoat is the aerodynamic characteristic data of the reference airfoil covered with the target roughness topcoat; the topcoat roughness of the target airfoil is within a target roughness range, and the target roughness range is related to the target roughness.

[0007] Optionally, the relative thickness of the target airfoil is within a target relative thickness range, and the target relative thickness range is related to the relative thickness of the reference airfoil.

[0008] Optionally, the method for correcting the aerodynamic characteristic data of the airfoil further includes: obtaining a plurality of roughness sampling values of the blade to be measured, where the blade to be measured is a blade designed based on the reference airfoil and covered with a topcoat; performing statistical processing on the plurality of roughness sampling values to obtain the target roughness.

[0009] Optionally, obtaining the aerodynamic characteristic data of the topcoat of the reference airfoil includes: obtaining at least one first experimental aerodynamic characteristic data and at least one second experimental aerodynamic characteristic data, where the first experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness less than the target roughness, and the second experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness greater than the target roughness; performing interpolation processing on the at least one first experimental aerodynamic characteristic data and the at least one second experimental aerodynamic characteristic data according to the target roughness to obtain the aerodynamic characteristic data of the topcoat.

[0010] Optionally, the reference airfoil model covered with the topcoat is a model obtained by covering the surface of the reference airfoil model with the topcoat according to reference process parameters, and the reference process parameters are the process parameters used when the blade to be measured is processed with the topcoat, and the blade to be measured is a blade designed based on the reference airfoil; the target roughness is obtained by querying process-roughness comparison information based on the reference process parameters, and the process-roughness comparison information is used to record process parameters and the corresponding topcoat roughness, and / or, the target roughness is obtained by measuring the reference airfoil model covered with the topcoat.

[0011] Optionally, a separable protective film is provided between the reference airfoil model and the topcoat, and the surface roughness error of the separable protective film relative to the surface roughness of the reference airfoil model is less than an error threshold.

[0012] Optionally, according to the different roughness of the blade surface, the blade surface conditions include a clean condition and a rough condition. The clean condition corresponds to a polished surface without topcoat coverage, and the rough condition corresponds to a surface that makes the airfoil flow reach a fully turbulent state. The original aerodynamic characteristic data includes the clean aerodynamic characteristic data under the clean condition; the correction parameters include at least one of a fusion ratio and a correction amount. Among them, the original aerodynamic characteristic data also includes the rough aerodynamic characteristic data under the rough condition. The fusion ratio is used to fuse the clean aerodynamic characteristic data and the rough aerodynamic characteristic data of the reference airfoil so that the fused result approximates the topcoat aerodynamic characteristic data. The correction amount includes at least one of an absolute correction value and a correction ratio, and the correction amount is used to correct the clean aerodynamic characteristic data of the reference airfoil so that the corrected result approximates the topcoat aerodynamic characteristic data.

[0013] In another general aspect, a method for determining blade aerodynamic performance data is provided. The method for determining blade aerodynamic performance data includes: obtaining a basic airfoil used in the design stage of a target blade and the corrected aerodynamic characteristic data of the basic airfoil; determining the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil, where the corrected aerodynamic characteristic data of the basic airfoil is obtained by the method for correcting aerodynamic characteristic data of an airfoil according to the embodiments of the present disclosure.

[0014] In another general aspect, a device for correcting aerodynamic characteristic data of an airfoil is provided. The device for correcting aerodynamic characteristic data of an airfoil includes: a reference obtaining unit configured to obtain the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data of a reference airfoil, where the topcoat aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with a topcoat, and the reference airfoil model is an equal airfoil polished model having the reference airfoil; a fitting unit configured to perform a fitting process on the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data of the reference airfoil to obtain correction parameters; a target obtaining unit configured to obtain the original aerodynamic characteristic data of a target airfoil; and a correction unit configured to correct the original aerodynamic characteristic data of the target airfoil according to the correction parameters to obtain the corrected aerodynamic characteristic data of the target airfoil.

[0015] Optionally, the topcoat aerodynamic characteristic data is the aerodynamic characteristic data of the reference airfoil when covered with a target roughness topcoat; the topcoat roughness of the target airfoil is within a target roughness range, and the target roughness range is related to the target roughness.

[0016] Optionally, the relative thickness of the target airfoil is within a target relative thickness range, and the target relative thickness range is related to the relative thickness of the reference airfoil.

[0017] Optionally, the correction device for the airfoil aerodynamic characteristic data further includes: a sampling unit configured to obtain a plurality of roughness sampling values of a blade to be measured, where the blade to be measured is a blade designed based on the reference airfoil and covered with topcoat; and a statistical unit configured to perform statistical processing on the plurality of roughness sampling values to obtain the target roughness.

[0018] Optionally, the reference acquisition unit is further configured to: obtain at least one first experimental aerodynamic characteristic data and at least one second experimental aerodynamic characteristic data, where the first experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness less than the target roughness, and the second experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness greater than the target roughness; and perform interpolation processing on the at least one first experimental aerodynamic characteristic data and the at least one second experimental aerodynamic characteristic data according to the target roughness to obtain the topcoat aerodynamic characteristic data.

[0019] Optionally, the reference airfoil model covered with topcoat is a model obtained by covering the surface of the reference airfoil model with topcoat according to reference process parameters, where the reference process parameters are the process parameters used when the blade to be measured is processed with topcoat, and the blade to be measured is a blade designed based on the reference airfoil; the target roughness is obtained by querying process-roughness control information based on the reference process parameters, where the process-roughness control information is used to record process parameters and corresponding topcoat roughnesses, and / or the target roughness is obtained by measuring the reference airfoil model covered with topcoat.

[0020] Optionally, a separable protective film is provided between the reference airfoil model and the topcoat, and the surface roughness of the separable protective film has an error less than an error threshold relative to the surface roughness of the reference airfoil model.

[0021] Optionally, according to the different roughness of the blade surface, the blade surface conditions include a clean condition and a rough condition. The clean condition corresponds to a polished surface without a topcoat, and the rough condition corresponds to a surface that enables the airfoil flow to reach a fully turbulent state. The original aerodynamic characteristic data includes the clean aerodynamic characteristic data under the clean condition; the correction parameter includes at least one of a fusion ratio and a correction amount. Among them, the original aerodynamic characteristic data also includes the rough aerodynamic characteristic data under the rough condition. The fusion ratio is used to fuse the clean aerodynamic characteristic data and the rough aerodynamic characteristic data of the reference airfoil so that the fused result approaches the topcoat aerodynamic characteristic data. The correction amount includes at least one of an absolute correction value and a correction ratio, and the correction amount is used to correct the clean aerodynamic characteristic data of the reference airfoil so that the corrected result approaches the topcoat aerodynamic characteristic data.

[0022] In another general aspect, there is provided an apparatus for determining blade aerodynamic performance data. The apparatus for determining blade aerodynamic performance data includes: an acquisition unit configured to acquire a basic airfoil used in the design stage of a target blade and corrected aerodynamic characteristic data of the basic airfoil; a determination unit configured to determine the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil, where the corrected aerodynamic characteristic data of the basic airfoil is obtained by a method for correcting aerodynamic characteristic data of an airfoil according to an embodiment of the present disclosure.

[0023] In another general aspect, there is provided a computer-readable storage medium. When instructions in the computer-readable storage medium are run by at least one processor, the at least one processor is caused to execute a method for correcting aerodynamic characteristic data of an airfoil or a method for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0024] In another general aspect, there is provided a computer device including: at least one processor; at least one memory storing computer-executable instructions, where when the computer-executable instructions are run by the at least one processor, the at least one processor is caused to execute a method for correcting aerodynamic characteristic data of an airfoil or a method for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0025] The present disclosure provides a method and device for correcting airfoil aerodynamic characteristic data, a method and device for determining blade aerodynamic performance data, a computer-readable storage medium, and a computer device. By conducting aerodynamic characteristic experiments on a reference airfoil model covered with topcoat, the corresponding aerodynamic characteristic data of the reference airfoil considering the influence of the topcoat can be obtained. Thus, by combining the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data, correction parameters can be determined, which can more clearly reflect the influence of the topcoat on the airfoil aerodynamic characteristics. On this basis, by using the correction parameters to correct the original aerodynamic characteristic data of the target airfoil, it is possible to infer the aerodynamic characteristic data of other airfoils (i.e., the target airfoil) after covering with the topcoat with a small number of experiments (i.e., experiments on the reference airfoil), as the corrected aerodynamic characteristic data, making the corrected aerodynamic characteristic data of the airfoil more in line with the actual operating conditions, helping to clarify the influence of the topcoat on the blade aerodynamic performance, improving the understanding of the operating states of the blade and the unit, and improving the consistency of the simulation and testing of the blade and the whole machine.

[0026] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Through the following description of the embodiments in conjunction with the drawings, the above and other objects and features of the present invention will become clearer. In the drawings:

[0028] Figure 1 is an aerodynamic characteristic curve showing the variation of lift coefficient with angle of attack;

[0029] Figure 2 is an aerodynamic characteristic curve showing the variation of drag coefficient with angle of attack;

[0030] Figure 3 is an aerodynamic characteristic curve showing the variation of pitching moment coefficient with angle of attack;

[0031] Figure 4 is an aerodynamic characteristic curve showing the variation of lift-to-drag ratio with angle of attack;

[0032] Figure 5 is a flowchart showing the method for correcting airfoil aerodynamic characteristic data according to an embodiment of the present disclosure;

[0033] Figure 6 is a clean aerodynamic characteristic curve and a topcoat aerodynamic characteristic curve showing the variation of lift coefficient with angle of attack according to a specific embodiment of the present disclosure;

[0034] Figure 7 is a clean aerodynamic characteristic curve and a topcoat aerodynamic characteristic curve showing the variation of lift coefficient with drag coefficient according to a specific embodiment of the present disclosure;

[0035] Figure 8 shows the clean aerodynamic characteristic curve and the painted aerodynamic characteristic curve of the pitching moment coefficient varying with the angle of attack according to a specific embodiment of the present disclosure;

[0036] Figure 9 shows the clean aerodynamic characteristic curve and the painted aerodynamic characteristic curve of the lift - to - drag ratio varying with the angle of attack according to a specific embodiment of the present disclosure;

[0037] Figure 10 is a flowchart showing a method for determining blade aerodynamic performance data according to an embodiment of the present disclosure;

[0038] Figure 11 is a block diagram showing a device for correcting airfoil aerodynamic characteristic data according to an embodiment of the present disclosure;

[0039] Figure 12 is a block diagram showing a device for determining blade aerodynamic performance data according to an embodiment of the present disclosure;

[0040] Figure 13 is a block diagram showing a computer device according to an embodiment of the present disclosure. Detailed Embodiments

[0041] The following detailed embodiments are provided to assist the reader in obtaining a comprehensive understanding of the methods, devices, and / or systems described herein. However, after understanding the disclosure of the present application, various changes, modifications, and equivalents of the methods, devices, and / or systems described herein will be apparent. For example, the order of operations described herein is merely exemplary and is not limited to those set forth herein. Rather, it may be changed as will be apparent after understanding the disclosure of the present application, except for operations that must occur in a specific order. Additionally, descriptions of features known in the art may be omitted for greater clarity and conciseness.

[0042] The features described herein may be implemented in different forms and should not be construed as limited to the examples described herein. On the contrary, the examples described herein are provided only to illustrate some of the many feasible ways of implementing the methods, devices, and / or systems described herein, which will be apparent after understanding the disclosure of the present application.

[0043] As used herein, the term "and / or" includes any one of the associated listed items and any combination of any two or more thereof.

[0044] Although terms such as "first", "second", and "third" may be used herein to describe various components, elements, regions, layers, or sections, these components, elements, regions, layers, or sections should not be limited by these terms. Instead, these terms are only used to distinguish one component, element, region, layer, or section from another. Thus, a first component, first element, first region, first layer, or first section described in the examples herein may also be referred to as a second component, second element, second region, second layer, or second section without departing from the teachings of the examples.

[0045] In the specification, when an element (such as a layer, region, or substrate) is described as "on" another element, "connected to" or "coupled to" another element, the element can be directly "on" the other element, directly "connected to" or "coupled to" the other element, or there can be one or more other elements intervening therebetween. In contrast, when an element is described as "directly on" another element, "directly connected to" or "directly coupled to" another element, there can be no other elements intervening therebetween.

[0046] The terms used herein are only for describing various examples and are not intended to limit the disclosure. Unless the context clearly indicates otherwise, the singular forms are also intended to include the plural forms. The terms "comprising", "including", and "having" specify the presence of the stated features, quantities, operations, components, elements, and / or combinations thereof, but do not preclude the presence or addition of one or more other features, quantities, operations, components, elements, and / or combinations thereof.

[0047] Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure pertains after understanding this disclosure. Unless explicitly defined herein, terms (such as those defined in a general dictionary) should be interpreted as having a meaning consistent with their meaning in the context of the relevant art and this disclosure, and should not be interpreted in an idealized or overly formal manner.

[0048] Furthermore, in the description of the examples, when a detailed description of related structures or functions that are considered well-known would cause an ambiguous interpretation of the disclosure, such detailed descriptions will be omitted.

[0049] The aerodynamic design of the blade is the selection of different design standard airfoils by the designer and the selection of the design lift point. Through the blade element momentum theory, the aerodynamic shape parameters such as the lift coefficient, relative thickness, chord length, twist angle, pre-bending, and sweep of the blade in the spanwise direction are designed. The standard airfoils used in blade design can be airfoils publicly available in the industry, such as the NACA (National Advisory Committee for Aeronautics) airfoil series and the DU (Delft University) airfoil series (a set of special airfoil families for wind turbine blades designed by Delft University), or airfoils self-designed by blade developers. The former often comes with publicly available aerodynamic characteristic data, while the latter is privately owned by blade developers. However, in either case, wind tunnel experiments remain a technical means to obtain accurate and reliable aerodynamic characteristic data of airfoils.

[0050] In experiments, a two-dimensional airfoil model with the airfoil shape is usually fabricated and the aerodynamic characteristic data of the airfoil is obtained through pressure measurement or force measurement techniques. Specifically, in the experiment, the values of some specific aerodynamic parameters under different oncoming flow conditions are measured. These aerodynamic parameters include but are not limited to the lift coefficient CL (Lift Coefficient), drag coefficient Cd (Drag Coefficient), pitching moment coefficient Cm (Moment Coefficient), and lift-to-drag ratio K (CL / Cd). The curves of these aerodynamic parameters varying with the angle of attack (ALPHA) (such as Figures 1 to 4 ) or the curves with each other as the x and y axes are called the aerodynamic characteristic curves of the airfoil and can be used as the aerodynamic characteristic data of the airfoil to participate in the aerodynamic performance calculation of the blade (the aerodynamic performance of the blade is often represented by parameters such as load and power coefficient). In other words, the aerodynamic performance of the blade is directly related to the aerodynamic characteristic curves presented by the standard airfoil.

[0051] The airfoil models used in experiments are usually fabricated from metal or carbon fiber materials and the surfaces are finely polished and treated to ensure the maximum consistency with the theory in terms of shape. The material system of the actual blade currently consists of a glass fiber + epoxy resin + core material + surface paint system. In particular, the surface of the blade is not as smooth as the surface of the airfoil model used in wind tunnel experiments, but rather presents a surface with a certain roughness similar to orange peel due to the characteristics of the paint. However, when the blade surface presents such a state, whether the aerodynamic characteristics of the airfoil will change compared to the aerodynamic characteristics of the airfoil model in the wind tunnel experiment, and if so, how much the change is, and how much impact it has on the whole machine? These issues have been studied very little in the domestic industry and even worldwide, but they are problems that must be faced when dealing with the performance consistency of the blade and the whole machine.

[0052] The following will be combined with Figures 1 to 13A method and apparatus for correcting airfoil aerodynamic characteristic data, a method and apparatus for determining blade aerodynamic performance data, a computer-readable storage medium, and a computer device provided by embodiments of the present disclosure are introduced.

[0053] An embodiment of one aspect of the present disclosure provides a method for correcting airfoil aerodynamic characteristic data. Figure 5 It is a flowchart showing a method for correcting airfoil aerodynamic characteristic data according to an embodiment of the present disclosure.

[0054] Referring to Figure 5 , in step S501, obtain the original aerodynamic characteristic data and paint aerodynamic characteristic data of the reference airfoil.

[0055] The paint aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with paint. As an example, the aerodynamic characteristic experiment is a wind tunnel experiment, and the aerodynamic characteristic data of an airfoil is obtained through pressure measurement or force measurement techniques. Specifically, the directly measured data in the experiment is the aforementioned aerodynamic parameters, and the obtained aerodynamic characteristic data is an aerodynamic characteristic curve. The reference airfoil model is an equal airfoil polished model with a reference airfoil, that is, a two-dimensional airfoil model with the shape of the reference airfoil, which is a commonly used blade form in existing wind tunnel experiments.

[0056] The original aerodynamic characteristic data is the existing aerodynamic characteristic data of the reference airfoil, and can also be obtained through a wind tunnel experiment. Specifically, according to the different surface roughness of the airfoil model, the surface conditions of the airfoil model include a clean condition and a rough condition. The clean condition corresponds to a polished surface without paint coverage, and the reference airfoil model belongs to the clean condition. The rough condition corresponds to a surface that makes the airfoil flow reach a fully turbulent state. The clean condition and the rough condition are two extreme conditions of the airfoil model surface without destroying the shape. The original aerodynamic characteristic data includes at least the clean aerodynamic characteristic data under the clean condition, which is also the airfoil aerodynamic characteristic data commonly used in the prior art when calculating blade performance. In addition, according to actual scheme requirements, the original aerodynamic characteristic data may further include the rough aerodynamic characteristic data under the rough condition.

[0057] In step S502, perform a fitting process on the original aerodynamic characteristic data and the paint aerodynamic characteristic data of the reference airfoil to obtain a correction parameter.

[0058] The correction parameter can represent the conversion relationship between the original aerodynamic characteristic data and the paint aerodynamic characteristic data.

[0059] Optionally, the correction parameter includes at least one of a fusion ratio and a correction amount, and the two respectively correspond to a correction method. For the fusion ratio, the original aerodynamic characteristic data includes both clean aerodynamic characteristic data and rough aerodynamic characteristic data. The fusion ratio is used to fuse the clean aerodynamic characteristic data and the rough aerodynamic characteristic data of the reference airfoil so that the fused result approximates the aerodynamic characteristic data of the topcoat, thereby enabling the determination of the aerodynamic characteristic data of the topcoat state (i.e., the state where the corresponding airfoil is covered with the topcoat) between the two by combining the aerodynamic characteristic data under two extreme working conditions, which helps to ensure the reliability of the correction result. For the correction amount, the original aerodynamic characteristic data includes clean aerodynamic characteristic data, and the correction amount includes at least one of an absolute correction value and a correction ratio. The correction amount is used to correct the clean aerodynamic characteristic data of the reference airfoil so that the corrected result approximates the aerodynamic characteristic data of the topcoat, thereby enabling the correction to be achieved with a small amount of original data, which helps to reduce the data dependence in the correction process.

[0060] It should be noted that, as Figures 1 to 4 shown, the aerodynamic characteristic curve is often not a curve with a constant change law, and there are some points where the change law changes suddenly. Based on this, the correction parameter may not be a value that remains constant for any abscissa value, but can take different values in segments according to the actual situation to fully ensure the accuracy of the correction result.

[0061] In step S503, the original aerodynamic characteristic data of the target airfoil is obtained.

[0062] The target airfoil is the airfoil whose aerodynamic characteristic data needs to be corrected.

[0063] In step S504, the original aerodynamic characteristic data of the target airfoil is corrected according to the correction parameter to obtain the corrected aerodynamic characteristic data of the target airfoil.

[0064] The corrected aerodynamic characteristic data is the aerodynamic characteristic data of the target airfoil covered with the topcoat inferred.

[0065] According to the method for correcting airfoil aerodynamic characteristic data of an exemplary embodiment of the present disclosure, by conducting aerodynamic characteristic experiments on a reference airfoil model covered with topcoat, the topcoat aerodynamic characteristic data of the corresponding reference airfoil considering the influence of the topcoat can be obtained. Thus, by combining the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data, correction parameters can be determined, which can more clearly reflect the influence of the topcoat on the airfoil aerodynamic characteristics. On this basis, by using the correction parameters to correct the original aerodynamic characteristic data of the target airfoil, the aerodynamic characteristic data of other airfoils (i.e., the target airfoil) after covering the topcoat can be inferred using a small number of experiments (i.e., the experiments for the reference airfoil) as the corrected aerodynamic characteristic data, making the corrected aerodynamic characteristic data of the airfoil more in line with the actual operating conditions, helping to clarify the influence of the topcoat on the blade aerodynamic performance, improving the understanding of the operating states of the blades and the unit, and improving the consistency of the simulation and testing of the blades and the whole machine.

[0066] Next, a further introduction is made to the method for correcting airfoil aerodynamic characteristic data of an exemplary embodiment of the present disclosure.

[0067] Regarding the relationship between the reference airfoil and the target airfoil, that is, for a specific reference airfoil, which other airfoils can be used as the target airfoil and use the correction parameters of the reference airfoil to correct their own aerodynamic characteristic data. It can be understood that this relationship describes the generalization range of the correction parameters of the reference airfoil, that is, to which other airfoils the correction parameters of the reference airfoil can be generalized and applied. By reasonably determining this relationship, the reliability of the correction result for the target airfoil can be improved.

[0068] Optionally, the reference airfoil and the target airfoil belong to the same airfoil family. An airfoil family refers to a group of airfoils with similar geometric characteristics and aerodynamic characteristics. These airfoils are generally developed from the same basic design and are generated by changing certain design parameters (such as relative thickness, camber, bending position, etc.). Different airfoils within the same airfoil family have similar aerodynamic characteristics, making the generalization between these airfoils more reliable.

[0069] Optionally, the aerodynamic characteristic data of the topcoat is the aerodynamic characteristic data of the reference airfoil with the target roughness topcoat; the topcoat roughness of the target airfoil is within the target roughness range, and the target roughness range is related to the target roughness. The influence of the topcoat on the aerodynamic characteristics of the airfoil likely stems from the change in roughness. By using the topcoat roughness as a parameter to describe the relationship between the reference airfoil and the target airfoil, generalizing the correction parameter of the reference airfoil to the airfoil with the topcoat roughness within the target roughness range helps ensure the effectiveness of this generalization, thereby enhancing the reliability of the correction result for the target airfoil. It should be understood that the target roughness is also within the target roughness range, that is, the topcoat roughness of the reference airfoil and the target airfoil should be relatively close. As for the specific determination of the target roughness range, depending on the different requirements for the accuracy of the correction result, experiments with different topcoat roughnesses can be conducted on the reference airfoil, and then a reasonable target roughness range can be determined by comparing the values of the correction parameters corresponding to different topcoat roughnesses. As an example, first obtain the surface roughness, that is, the topcoat roughness, of the blades produced by different manufacturers in the industry and reaching the factory state, and then statistically obtain the roughness range that can enclose most or all of the blades on the market. Then, conduct experiments on the two endpoint values of this roughness range (that is, use the two endpoint values of the roughness range as the target roughness respectively, conduct aerodynamic characteristic experiments, and perform step S501 and step S502 of the present disclosure). If the experimental results show that the correction parameters of the two are close, for example, the ratio of the smaller correction parameter to the larger correction parameter is greater than or equal to the set ratio (such as 0.95), it is considered that the topcoat roughness does not affect the aerodynamic characteristic data. From the perspective of the topcoat roughness, the correction parameter of the reference airfoil can be generalized to any airfoil with other topcoat roughnesses. However, if the correction parameters of the two are significantly different, for example, the ratio of the smaller correction parameter to the larger correction parameter is less than the set ratio, it is considered that the topcoat roughness affects the aerodynamic characteristic data. The roughness range can be simply divided into two segments as two target roughness ranges, and the target roughnesses corresponding to these two target roughness ranges are the two corresponding endpoint values of the original roughness range respectively. Of course, other roughnesses can also be selected in the original roughness range for experiments, and the corresponding correction parameters can be determined. According to whether the roughnesses that have been experimented and their corresponding correction parameters are close, the original roughness range can be divided to obtain several target roughness ranges. At this time, the more roughnesses the experiment is directed at, the higher the division accuracy of the target roughness range can be improved, but it also means a higher cost. In practice, the experiment can be reasonably designed in combination with the actual situation, and the present disclosure does not limit this.

[0070] Optionally, the relative thickness of the target airfoil is within a target relative thickness range, and the target relative thickness range is related to the relative thickness of the reference airfoil. The thickness of an airfoil refers to the maximum dimension of the airfoil in the direction perpendicular to the chord direction, the chord direction refers to the direction where the chord line of the airfoil is located, the chord line is the connection line between the leading edge and the trailing edge of the airfoil, and the length of the chord line is called the chord length. To achieve dimensionlessization, the ratio of the thickness of the airfoil to the chord length is usually used to represent the relative thickness of the airfoil. The relative thickness of the airfoil often also has an obvious impact on its aerodynamic characteristics. By using the relative thickness of the airfoil as a parameter to describe the relationship between the reference airfoil and the target airfoil, and generalizing the correction parameters of the reference airfoil to airfoils with relative thickness within the target relative thickness range, it helps to ensure the effectiveness of this generalization, and further improve the reliability of the correction results for the target airfoil. Similar to the topcoat roughness, the relative thickness of the reference airfoil is also within the target relative thickness range, that is, the relative thickness of the reference airfoil and the target airfoil should be relatively close, and the target relative thickness range can be specifically designed and experimented reasonably according to the actual situation to determine.

[0071] It should be understood that only the topcoat roughness can be used as a parameter to describe the relationship between the reference airfoil and the target airfoil, or only the relative thickness of the airfoil can be used as a parameter to describe the relationship between the reference airfoil and the target airfoil, or both the topcoat roughness and the relative thickness of the airfoil can be used simultaneously as parameters to describe the relationship between the reference airfoil and the target airfoil to increase the dimension of the description. In addition, roughness can usually be specifically described by different parameters such as arithmetic mean roughness Ra, ten-point height average Rz, root mean square roughness Rq, total height Rt, profile roughness curve length Rc, mean interval roughness Rsm, relative material ratio Rmr, total profile unevenness Pt, slope of the material ratio curve Pmr, etc. Therefore, at least one of these parameters can also be selected as the topcoat roughness.

[0072] Optionally, after obtaining the correction parameters of airfoils with different relative thicknesses within the same airfoil family (hereinafter referred to as the first airfoil family) under multiple different target roughnesses through experiments or further combined with the correction method of the present disclosure, if it is necessary to correct a target airfoil in a second airfoil family based on a reference airfoil in the second airfoil family, the correction parameters of the first airfoil family can also be used as a reference. That is, step S504 includes: determining the correction parameters of the target airfoil in the second airfoil family according to the correction parameters of the first airfoil family and the correction parameters of the reference airfoil in the second airfoil family; correcting the original aerodynamic characteristic data of the target airfoil in the second airfoil family according to the correction parameters of the target airfoil in the second airfoil family to obtain the corrected aerodynamic characteristic data of the target airfoil in the second airfoil family. In other words, based on the correction parameters of the first airfoil family, first correct the correction parameters of the reference airfoil in the second airfoil family to obtain the correction parameters of the target airfoil in the second airfoil family, and then correct the aerodynamic characteristic data accordingly, which can further expand the scope of promotion of the correction parameters, reduce the experimental amount of the second airfoil family, and help save costs. For example, if the relative thickness of the reference airfoil in the second airfoil family is 25% and the relative thickness of the target airfoil is 30%, and the topcoat roughness of the two is equal, the correction parameters of the two can be respectively denoted as the second 25% correction parameter (this is a known quantity) and the second 30% correction parameter (this is an unknown quantity), and the correction parameters of two airfoils with relative thicknesses of 25% and 30% and the same topcoat roughness in the first airfoil family are taken and respectively denoted as the first 25% correction parameter and the first 30% correction parameter (both are known quantities), and then an equation is established where the ratio of the first 25% correction parameter to the first 30% correction parameter is equal to the ratio of the second 25% correction parameter to the second 30% correction parameter, so that the second 30% correction parameter can be calculated.

[0073] For the embodiment in which the topcoat roughness is used as a parameter to describe the relationship between the reference airfoil and the target airfoil, it is necessary to clarify the value of the target roughness in this experiment to clarify the target roughness range and reproduce the target roughness in the aerodynamic characteristic experiment, that is, to make the topcoat roughness of the reference airfoil model covered with the topcoat equal to the target roughness.

[0074] In this regard, in some embodiments, the method for correcting airfoil aerodynamic characteristic data according to the exemplary embodiments of the present disclosure further includes: obtaining a plurality of roughness sampling values of the blade to be measured, where the blade to be measured is a blade designed based on a reference airfoil and covered with a topcoat; performing statistical processing on the plurality of roughness sampling values to obtain a target roughness. By actually measuring the roughness sampling values of the blade to be measured designed and processed based on the reference airfoil and statistically obtaining the target roughness, it can be ensured that the target roughness can indeed be applied to the reference airfoil, ensuring the practicality of the experimental results. As an example, a plurality of scattered spanwise positions can be selected along the span of the blade to be measured for roughness collection, and for each spanwise position, collection can be performed only for a specific area, for example, only for the position area within 40% of the chord length from the leading edge in the chordwise direction, because this part of the area has the most obvious influence on the aerodynamic performance of the blade, so as to improve the collection efficiency of the roughness sampling values. As an example, performing statistical processing on the plurality of roughness sampling values is to convert the plurality of roughness sampling values into a value sufficient to represent the roughness condition of the topcoat of the blade to be measured, that is, the target roughness. Therefore, this statistical processing can be a processing of calculating statistical values (such as average value, median, mode, etc.), and data cleaning can also be performed before calculating the statistical values to filter out significantly abnormal roughness sampling values. Statistical processing belongs to the existing technology of data processing and will not be elaborated here. It should be understood that the statistical processing of roughness here is to convert the plurality of roughness sampling values of the same blade (i.e., the blade to be measured) into one value to clarify the roughness condition of the blade, while the operation of statistically obtaining the roughness range in the previous text is to collect the surface roughnesses of various existing blades in the industry to determine the value range to which these roughnesses belong. The two are completely different processes.

[0075] Optionally, the operation of obtaining the topcoat aerodynamic characteristic data of the reference airfoil in step S501 includes: obtaining at least one first experimental aerodynamic characteristic data and at least one second experimental aerodynamic characteristic data, where the first experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness less than the target roughness, and the second experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness greater than the target roughness; performing interpolation processing on the at least one first experimental aerodynamic characteristic data and the at least one second experimental aerodynamic characteristic data according to the target roughness to obtain the topcoat aerodynamic characteristic data. By obtaining the experimental data of different roughnesses on both sides of the target roughness and then interpolating to obtain the data of the target roughness as the topcoat aerodynamic characteristic data, it is not necessary to strictly reproduce the target roughness during the experiment, which helps to reduce the experimental difficulty and improve the feasibility of the experiment.

[0076] As an example, for an embodiment that uses at least two specific parameters to describe the roughness of the topcoat, two experimental data can be obtained for the values of each specific parameter respectively and interpolation processing can be performed to obtain the aerodynamic characteristic data corresponding to each specific parameter. Then, statistical processing can be performed on the aerodynamic characteristic data obtained through this interpolation processing, and the statistical result can be used as the aerodynamic characteristic data of the topcoat. For example, in the case where two specific parameters, namely the arithmetic mean roughness Ra and the average ten-point height Rz, are used simultaneously, the aerodynamic characteristic data corresponding to the arithmetic mean roughness Ra and the aerodynamic characteristic data corresponding to the average ten-point height Rz can be obtained respectively. Statistical processing can be performed on these two aerodynamic characteristic data, such as but not limited to calculating the average value or weighted summation, and then the statistical result can be used as the aerodynamic characteristic data of the topcoat.

[0077] For the interpolation processing of each specific parameter, as an example, when performing interpolation processing, the weights of the experimental data can be determined according to the magnitude relationship between the value of the specific parameter and the parameter values on its left and right sides in the experiment. For example, for the target value Ra1 of the arithmetic mean roughness Ra and the two parameter values Ra2 and Ra3 on its left and right sides, the values of α and β in the equation Ra1 = αRa2 + βRa3 can be determined. Furthermore, with α and β as weights, the experimental data can be weighted and summed to obtain the aerodynamic characteristic data corresponding to the specific parameter Ra1. In addition, for the points or regions where the trend of the aerodynamic characteristic curve undergoes a sudden change, the weight values can also be locally adjusted to improve the rationality of the interpolated aerodynamic characteristic data, and thus improve its accuracy.

[0078] In some other embodiments, it is not necessary to directly measure the target roughness of the blade to be measured. Instead, the corresponding relationship between the process parameters used in processing the topcoat and the topcoat roughness thus formed is statistically determined in advance and recorded in the process-roughness comparison information, and the target roughness can be determined by information query. As an example, the process parameters include at least one of the paint brand, tool brand (such as the roller brand for roller-coating the topcoat, the tool brand for spraying the topcoat), ambient temperature, ambient humidity, and the number of topcoat layers. Specifically, the process parameters used in processing the topcoat of the blade to be measured can be obtained from the manufacturer of the blade to be measured, denoted as the reference process parameters. The target roughness can be obtained by querying the process-roughness comparison information based on the reference process parameters. Thus, without obtaining the physical object of the blade to be measured or without performing measurement operations, the value of the target roughness can be obtained relatively reliably, improving the convenience of obtaining the target roughness. At this time, the reference airfoil model covered with the topcoat is the model obtained by covering the surface of the reference airfoil model with the topcoat according to the reference process parameters, that is, by clarifying the reference process parameters and then directly applying them to the topcoat processing procedure of the reference airfoil model, to achieve a more direct corresponding relationship between the reference airfoil model and the reference airfoil covered with the topcoat to be tested, realizing the convenient and accurate reproduction of the target roughness in the aerodynamic characteristic experiment. That is, only the airfoil model with the target roughness needs to be used for the experiment, which can reduce the amount of experiments and lower the experimental cost. Correspondingly, since the airfoil model for the experiment reproduces the target roughness, the target roughness can also be obtained by measuring the airfoil model for the experiment, that is, by measuring the reference airfoil model covered with the topcoat, which can further improve the accuracy of the determined value of the target roughness. It should be understood that both of the above two methods can also be used simultaneously to obtain the target roughness. The first method is used as a preliminary confirmation, and the second method is used as a review before the experiment. Usually, they are consistent. If there are differences, the review result shall prevail. If the differences are large, the process-roughness comparison information can be corrected accordingly, which helps to improve the information accuracy.

[0079] In addition, as mentioned above, in order to determine the target roughness range, it is necessary to first count the roughness ranges of most or all of the blades on the market. However, the surface topcoat protection systems for the blades of each blade manufacturer are not uniform. At present, this process is mostly completed by manual rolling or spraying both in China and internationally, and there are differences in the rollers, paint systems, temperature and humidity, etc. used. Therefore, the surface states of the blades after topcoat painting vary greatly. Although the blade manufacturers usually detect the roughness (i.e., the topcoat roughness) of the blades they produce, the measuring tools and the settings of the tool parameters used by different manufacturers often vary, resulting in the roughness directly obtained from the manufacturers not having a unified standard. By first collecting the topcoat process parameters of each manufacturer, then uniformly measuring a large number of topcoat samples obtained according to different process parameters, and counting the process-roughness comparison information, it is possible to study the influence of different sensitive process parameters such as paints, rollers, temperature and humidity on the surface state after topcoat forming. Furthermore, based on the topcoat process parameters of a certain blade, by querying the process-roughness comparison information, the topcoat roughness of the blade under this unified standard can be obtained, thus innovatively using the topcoat process parameters of the blade to uniformly evaluate the topcoat surface state of the blade, which helps to achieve the standardization of data and can flexibly and conveniently obtain the topcoat roughness of newly produced blades. As an example, the topcoat samples used for unified measurement can be the samples provided by the blade manufacturers, and sampling and statistics can be carried out according to the method for obtaining the target roughness introduced above, that is, measuring multiple roughness sampling values for the topcoat samples and then performing statistical processing to convert the multiple roughness sampling values into a statistical value as the topcoat roughness of the topcoat sample; it can also be obtained by coating paint on a flat plate according to the corresponding process parameters without actually measuring the blades, and the present disclosure does not limit this.

[0080] In addition, in some embodiments, optionally, a separable protective film (such as an organic material protective film) is provided between the reference airfoil model and the topcoat, and the error of the surface roughness of the separable protective film relative to the surface roughness of the reference airfoil model is less than the error threshold. By first covering the reference airfoil model with the separable protective film and then covering the topcoat, the topcoat can be conveniently removed by separating the protective film after the experiment is completed, realizing the reuse of the reference airfoil model, which helps to greatly reduce the experimental cost. Of course, the reference airfoil model can also be reused for experiments in other scenarios outside the scenario of the present disclosure, and even the reference airfoil model can be borrowed from experiments in other scenarios to further reduce the usage cost of the reference airfoil model. In addition, compared with the coating, the film structure is easier to control its surface roughness. By making the surface roughness of the separable protective film close to the surface roughness of the reference airfoil model, other roughness introduced can be minimized as much as possible, thus ensuring the effectiveness of the experimental results.

[0081] As an example, pressure measurement holes are usually drilled on the surface of the reference airfoil model for experiments, so as to set the pressure sensor probes for testing. During the experiment, a separable protective film can be first covered on the surface of the reference airfoil model, then holes are drilled at the positions where the separable protective film covers the pressure measurement holes, and the holes and the pressure measurement holes are blocked. After painting, the blocking materials are removed, and an experimental airfoil model covered with a separable protective film and paint and having pressure measurement holes can be obtained.

[0082] Next, in combination with a specific embodiment, a method for correcting airfoil aerodynamic characteristic data according to an exemplary embodiment of the present disclosure will be introduced. The overall logic of this specific embodiment is to use a specific method for measuring the surface paint roughness of the blade to obtain paint roughness data of a certain statistic. Specifically, parameters such as but not limited to arithmetic mean roughness Ra, ten-point height average Rz, root mean square roughness Rq, total height Rt, profile roughness curve length Rc, average spacing roughness Rsm, relative material ratio Rmr, total profile unevenness Pt, and slope of the material ratio curve Pmr can be used; after rolling paint on the surface of the reference airfoil model in a wind tunnel experiment, paint roughness data of a certain statistic is measured, and airfoil aerodynamic characteristic data under different oncoming flow states is measured. Through roughness data analysis and magnitude relationship, the aerodynamic characteristic data that can represent the surface state of the blade is corrected and determined. In other words, for the target roughness, this specific embodiment adopts the method of actually measuring the paint roughness of the blade to be measured.

[0083] Specifically, the above logic mainly includes the following three parts.

[0084] The first part: Acquisition of paint roughness data on the blade surface.

[0085] A) Sampling area of the blade to be measured

[0086] Select one or more blades to be measured, observe the storage posture of the blades. Each blade includes but is not limited to 3 sampling areas: the blade root, the middle of the blade, and the blade tip.

[0087] If the blade is placed vertically with the leading edge facing down and the trailing edge facing up, then in the spanwise direction, select the maximum chord length area of the suction surface (near the blade root), the area on both sides of the middle bracket (in the middle of the blade), the starting area of the navigation paint or the area within 10 meters from the blade tip (at the blade tip). For these three spanwise position areas, further select the area within 40% of the chord length from the leading edge in the chordwise direction, and each area is about 0.2 m 2 .

[0088] If the blade is placed horizontally with the pressure side facing up, then in the spanwise direction, select the maximum chord length region, the regions on both sides of the middle bracket, the starting region of the navigation mark paint, or the region within 10 meters from the blade tip. In the chordwise direction, select the region within 40% of the chord length from the leading edge. Priority is given to the suction side. If it is not convenient for measurement operations, the pressure side can be selected, and it is ensured that the roughness meter can be stably placed on the surface.

[0089] The above two sampling regions are sampled on the topcoat surface, avoiding the regions where the leading edge protection system, lightning arrester, and surface markings are located.

[0090] B) Selection of sampling points

[0091] Within each of the selected sampling regions above, select a 40 cm * 40 cm square region with uniform topcoat application quality visually and by finger touch. Mark 25 sampling points in a 5 * 5 grid with a distance of 10 cm between each two sampling points to form a sampling lattice.

[0092] C) Measurement steps

[0093] The measurement operation is carried out according to the following steps:

[0094] 1) According to the storage posture of the blade, select the appropriate sampling region according to the example in Section A.

[0095] 2) Within each sampling region, mark the sampling points according to the example in Section B.

[0096] 3) Set the measurement parameters of the roughness meter. It should be understood that for the embodiments of statistically processing the roughness - process control information, when uniformly measuring a large number of topcoat samples, the same model of roughness meter as here is also used, and the measurement parameters are set to be consistent with those here to ensure a unified measurement standard in different embodiments.

[0097] 4) Use the calibration plate supporting the roughness meter for calibration measurement. The number of measurements is not less than 3 times, and the deviation convergence of the measured value (generally the arithmetic mean roughness Ra) is less than 0.05 μm. Set the calibration to be completed and record the calibration data.

[0098] 5) At the marked sampling points, successively use the calibrated roughness meter to measure the roughness value at the position of each point, record the roughness result data including but not limited to the arithmetic mean roughness Ra, the average ten - point height Rz, the root - mean - square roughness Rq, etc., and organize the data into a table. (Some instruments have upper - computer software that can semi - automatically measure, record, store, and transmit data)

[0099] 6) Statistically process the sampled roughness result data to obtain the statistical value as the target roughness.

[0100] The second part: Conduct a wind tunnel experiment on the reference airfoil model to obtain the aerodynamic characteristic data of the topcoat.

[0101] According to the topcoat roughness value obtained from the first part (i.e., the target roughness), apply the topcoat to the surface of the reference airfoil model in the wind tunnel experiment to reproduce the target roughness, and use the reproduced airfoil model for the experiment. During the process of reproducing the target roughness, there are often situations where it is impossible to match the target roughness measured in the early stage. In this case, through the experiment, the aerodynamic characteristic data of at least one reference airfoil model with a topcoat roughness greater than the target roughness and the aerodynamic characteristic data of at least one reference airfoil model with a topcoat roughness less than the target roughness are obtained. Then, combined with the target roughness, interpolation processing is performed on the aerodynamic characteristic data obtained from the experiment, and the aerodynamic characteristic data of the topcoat that meets the actual target roughness of the reference airfoil can be obtained.

[0102] As known from aerodynamics knowledge, when the surface state of the model changes, it will have an impact on the aerodynamic characteristics of the airfoil (especially the development of the boundary layer and related parameters). The key aerodynamic characteristic parameters obtained in this disclosure are the lift coefficient CL, drag coefficient Cd, pitching moment coefficient Cm, and lift-to-drag ratio K of the airfoil with the topcoat covering the surface. Through the analysis of the data obtained after the wind tunnel experiment, it is found that the aerodynamic characteristics of the airfoil with the topcoat change significantly, manifested as: the lift coefficient CL decreases to a certain extent, the drag coefficient Cd increases to a certain extent, the pitching moment coefficient Cm increases to a certain extent, the lift-to-drag ratio K decreases to a certain extent, and the stall angle of attack advances to a certain extent. The changes in the typical aerodynamic characteristic curves are as Figures 6 to 9 shown, which respectively show the clean aerodynamic characteristic curve under the clean condition and the topcoat aerodynamic characteristic curve under the topcoat state.

[0103] Part Three: Determine the aerodynamic characteristic data of the airfoil considering the topcoat on the blade surface.

[0104] This part has two forms:

[0105] 1) Directly use the aerodynamic characteristic data of the topcoat of the reference airfoil under the target roughness measured in the wind tunnel experiment in the second part above. In other words, directly conduct the experiment in the second part. The advantage of this form is that the data is true and reliable, making the consistency of calculation and testing better. The disadvantage is that the surface roughness cannot be accurately controlled artificially, there are many sensitive variables; it is necessary to test different roughnesses multiple times to enrich the available aerodynamic characteristic data.

[0106] 2) Based on the original aerodynamic characteristic data of known airfoils obtained from existing wind tunnel experiments or numerical simulations, compare these data with the aerodynamic characteristic data of the topcoat of the airfoil obtained from the second part of the test to determine the correction parameters, and apply these correction parameters to other airfoils. Thus, based on the original aerodynamic characteristic data of other airfoils, the corrected aerodynamic characteristic data considering the topcoat can be obtained. For the determination of the correction parameters, for example, the original aerodynamic characteristic data may include the clean aerodynamic characteristic data under clean conditions and the rough aerodynamic characteristic data under rough conditions, and the correction parameter is the fusion ratio of the two. When determining the fusion ratio, the numerical fitting method can be used to compare the result obtained by fusing the above two types of data using the fusion ratio with the aerodynamic characteristic data of the topcoat obtained from the second part of the test to find a close fitting result. The advantage of this form is that it is not necessary to spend financial and human resources to measure the aerodynamic characteristic data of the topcoats of different airfoils, and it can be approximately processed by numerical calculation and fitting methods. To improve the accuracy of the approximation process, wind tunnel experiments can also be conducted on multiple airfoils and multiple topcoat roughnesses to more accurately apply appropriate correction parameter values to different airfoils and topcoat roughnesses.

[0107] Regardless of which of the above forms is adopted, the finally obtained aerodynamic characteristic data considering the topcoat is closer to the actual state of the blade with the paint surface when leaving the factory than the aerodynamic characteristic data obtained from experiments or computational simulations of the standard airfoil with a finely polished surface made of metal or composite materials, which helps to improve the simulation test consistency of the blade performance and the overall machine performance.

[0108] An embodiment of the second aspect of the present disclosure provides a method for determining blade aerodynamic performance data. Figure 10 It is a flowchart showing the method for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0109] Refer to Figure 10 , in step S1001, obtain the basic airfoil used in the design stage of the target blade and the corrected aerodynamic characteristic data of the basic airfoil.

[0110] The basic airfoil is the standard airfoil used in the design of the blade. Multiple standard airfoils are often used in blade design, and this step can be executed separately for each standard airfoil.

[0111] In step S1002, determine the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil.

[0112] Among them, the corrected aerodynamic characteristic data of the basic airfoil are obtained by the airfoil aerodynamic characteristic data correction method provided in any embodiment of the first aspect of the present disclosure, that is, the corrected aerodynamic characteristic data obtained by using this correction method are applied to blade performance calculation, and of course, they can be further applied to the overall performance calculation of a wind turbine generator set. Therefore, the method for determining the blade aerodynamic performance data in the embodiments of the present disclosure has all the beneficial technical effects of the above-mentioned airfoil aerodynamic characteristic data correction method, which will not be elaborated here. By applying the corrected aerodynamic characteristic data of the basic airfoil in blade design, the power generation performance and load level of the blade and the whole machine can be calculated and analyzed closer to the physical reality, and used to guide the performance and load calculation of the whole machine in different application environments, thereby improving the reliability of blade and unit development.

[0113] The calculation method of step S1002 can refer to the method for determining the aerodynamic performance data of the blade according to the clean aerodynamic characteristic data of the basic airfoil, except that the clean aerodynamic characteristic data are replaced by the corrected aerodynamic characteristic data. Briefly speaking, based on the blade element momentum theory, the blade is regarded as an overall composed of multiple blade elements distributed along the span direction. For each blade element, since the airfoil of the current blade element is obtained by interpolating multiple standard airfoils during design, the corrected aerodynamic characteristic curve of the airfoil of the current blade element can also be obtained by interpolating the corrected aerodynamic characteristic curves of multiple standard airfoils. Then, based on this curve and the state of the oncoming flow (such as the oncoming flow angle and local flow velocity), the lift and drag of the current blade element are calculated. Finally, the lift and drag of all blade elements are integrated to obtain the total lift and total drag of the entire blade, as well as the resulting thrust and torque. The actual output power of the blade can also be further calculated by combining the torque and the designed rotational speed of the impeller, so as to obtain the power coefficient of the blade (the ratio of the actual output power to the total power of the wind). All these data can be used as the aerodynamic performance data of the blade.

[0114] Through actual calculation, it is found that after using the aerodynamic characteristic data of the topcoat considering the topcoat state and the corrected aerodynamic characteristic data, compared with the situation calculated using the clean aerodynamic characteristic data, the calculated result of the power generation of the whole machine has a certain degree of reduction, and the ultimate loads and fatigue loads of large components including the blade have varying degrees of changes, and the overall result is closer to the actual operating conditions of the unit. Specifically, for the reasonable calculation of power generation, it can avoid the compensation losses caused by overestimating the power generation and subsequent performance not meeting the standards. For the calculation of loads, for the part that is reasonably increased compared with the calculation result of the existing calculation method, it can capture the situation where the design scheme meets the load requirements faster, thereby reducing the workload of design simulation iteration; for the part that is reasonably reduced compared with the calculation result of the existing calculation method, it can more truthfully reflect the fact that the current scheme has insufficient load-bearing capacity, thereby reducing the risk of the actual operating load of the unit exceeding the limit.

[0115] An embodiment of the third aspect of the present disclosure provides a correction device for airfoil aerodynamic characteristic data. Figure 11 It is a block diagram showing a correction device for airfoil aerodynamic characteristic data according to an embodiment of the present disclosure. Refer to Figure 11 As shown in Figure 11 , the correction device 1100 for airfoil aerodynamic characteristic data includes a reference acquisition unit 1101, a fitting unit 1102, a target acquisition unit 1103, and a correction unit 1104.

[0116] The reference acquisition unit 1101 can acquire the original aerodynamic characteristic data of the reference airfoil and the aerodynamic characteristic data of the topcoat. Among them, the aerodynamic characteristic data of the topcoat is the data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with the topcoat, and the reference airfoil model is an equal airfoil polished model with the reference airfoil.

[0117] The fitting unit 1102 can perform fitting processing on the original aerodynamic characteristic data of the reference airfoil and the aerodynamic characteristic data of the topcoat to obtain correction parameters.

[0118] The target acquisition unit 1103 can acquire the original aerodynamic characteristic data of the target airfoil;

[0119] The correction unit 1104 can perform correction processing on the original aerodynamic characteristic data of the target airfoil according to the correction parameters to obtain the corrected aerodynamic characteristic data of the target airfoil.

[0120] Optionally, the aerodynamic characteristic data of the topcoat is the aerodynamic characteristic data of the reference airfoil when covered with the target roughness topcoat; the topcoat roughness of the target airfoil is within the target roughness range, and the target roughness range is related to the target roughness.

[0121] Optionally, the relative thickness of the target airfoil is within the target relative thickness range, and the target relative thickness range is related to the relative thickness of the reference airfoil.

[0122] Optionally, the correction device for airfoil aerodynamic characteristic data further includes a sampling unit (not shown in the figure) and a statistical unit (not shown in the figure). The sampling unit can acquire multiple roughness sampling values of the blade to be measured, where the blade to be measured is a blade designed based on the reference airfoil and covered with the topcoat; the statistical unit can perform statistical processing on the multiple roughness sampling values to obtain the target roughness.

[0123] Optionally, the reference acquisition unit 1101 may further: acquire at least one first experimental aerodynamic characteristic data and at least one second experimental aerodynamic characteristic data, where the first experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness less than the target roughness, and the second experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness greater than the target roughness; perform interpolation processing on the at least one first experimental aerodynamic characteristic data and the at least one second experimental aerodynamic characteristic data according to the target roughness to obtain the topcoat aerodynamic characteristic data.

[0124] Optionally, the reference airfoil model covered with the topcoat is a model obtained by covering the surface of the reference airfoil model with the topcoat according to the reference process parameters, the reference process parameters are the process parameters used when the blade to be measured is applying the topcoat, and the blade to be measured is a blade designed based on the reference airfoil; the target roughness is obtained by querying the process-roughness correspondence information based on the reference process parameters, and the process-roughness correspondence information is used to record the process parameters and the corresponding topcoat roughness, and / or, the target roughness is obtained by measuring the reference airfoil model covered with the topcoat.

[0125] Optionally, a separable protective film is provided between the reference airfoil model and the topcoat, and the surface roughness error of the separable protective film relative to the surface roughness of the reference airfoil model is less than the error threshold.

[0126] Optionally, according to the different roughness degrees of the blade surface, the blade surface conditions include a clean condition and a rough condition. The clean condition corresponds to a polished surface without the topcoat, and the rough condition corresponds to a surface that makes the airfoil flow reach the fully turbulent state. The original aerodynamic characteristic data includes the clean aerodynamic characteristic data under the clean condition; the correction parameters include at least one of a fusion ratio and a correction amount. Wherein, the original aerodynamic characteristic data further includes the rough aerodynamic characteristic data under the rough condition. The fusion ratio is used to fuse the clean aerodynamic characteristic data and the rough aerodynamic characteristic data of the reference airfoil to make the fused result approximate to the topcoat aerodynamic characteristic data. The correction amount includes at least one of an absolute correction value and a correction ratio, and the correction amount is used to correct the clean aerodynamic characteristic data of the reference airfoil to make the corrected result approximate to the topcoat aerodynamic characteristic data.

[0127] An embodiment of the third aspect of the present disclosure provides a device for determining blade aerodynamic performance data. Figure 12 is a block diagram showing a device for determining blade aerodynamic performance data according to an embodiment of the present disclosure. Refer to Figure 12 , the device 1200 for determining blade aerodynamic performance data includes an acquisition unit 1201 and a determination unit 1202.

[0128] The acquisition unit 1201 can acquire the basic airfoil used in the design stage of the target blade and the corrected aerodynamic characteristic data of the basic airfoil.

[0129] The determination unit 1202 can determine the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil.

[0130] Wherein, the corrected aerodynamic characteristic data of the basic airfoil is obtained by the airfoil aerodynamic characteristic data correction method provided in any embodiment of the first aspect of the present disclosure.

[0131] Regarding the device in the above embodiments, the specific manners in which each unit performs operations have been described in detail in the embodiments related to the method, and will not be elaborated herein.

[0132] The airfoil aerodynamic characteristic data correction method or the blade aerodynamic performance data determination method according to the embodiments of the present disclosure can be written as a computer program and stored on a computer-readable storage medium. When the instructions corresponding to the computer program are executed by a processor, the airfoil aerodynamic characteristic data correction method or the blade aerodynamic performance data determination method as described above can be implemented. Examples of computer-readable storage media include: read-only memory (ROM), random access programmable read-only memory (PROM), electrically erasable programmable read-only memory (EEPROM), random access memory (RAM), dynamic random access memory (DRAM), static random access memory (SRAM), flash memory, non-volatile memory, CD-ROM, CD-R, CD+R, CD-RW, CD+RW, DVD-ROM, DVD-R, DVD+R, DVD-RW, DVD+RW, DVD-RAM, BD-ROM, BD-R, BD-R LTH, BD-RE, Blu-ray or optical disc memory, hard disk drive (HDD), solid state drive (SSD), card memory (such as, multimedia card, secure digital (SD) card or extreme digital (XD) card), magnetic tape, floppy disk, magneto-optical data storage device, optical data storage device, hard disk, solid state disk, and any other device configured to store a computer program and any associated data, data files, and data structures in a non-transitory manner and provide the computer program and any associated data, data files, and data structures to a processor or computer such that the processor or computer can execute the computer program. In one example, the computer program and any associated data, data files, and data structures are distributed on a networked computer system such that the computer program and any associated data, data files, and data structures are stored, accessed, and executed in a distributed manner by one or more processors or computers.

[0133] Figure 13is a block diagram showing a computer device according to an embodiment of the present disclosure.

[0134] Referring Figure 13 , the computer device 1300 includes at least one memory 1301 and at least one processor 1302. A set of computer-executable instructions is stored in the at least one memory 1301. When the set of computer-executable instructions is executed by the at least one processor 1302, a method for correcting airfoil aerodynamic characteristic data or a method for determining blade aerodynamic performance data according to an exemplary embodiment of the present disclosure is executed.

[0135] As an example, the computer device 1300 may be a PC computer, a tablet device, a personal digital assistant, a smart phone, or other devices capable of executing the above instruction set. Here, the computer device 1300 does not have to be a single electronic device, and may also be any assembly of devices or circuits that can execute the above instructions (or instruction sets) individually or jointly. The computer device 1300 may also be part of an integrated control system or system manager, or may be configured as a portable electronic device that can be interconnected locally or remotely (e.g., via wireless transmission).

[0136] In the computer device 1300, the processor 1302 may include a central processing unit (CPU), a graphics processing unit (GPU), a programmable logic device, a dedicated processor system, a microcontroller, or a microprocessor. By way of example and not limitation, the processor may also include an analog processor, a digital processor, a microprocessor, a multi-core processor, a processor array, a network processor, etc.

[0137] The processor 1302 may run instructions or code stored in the memory 1301, where the memory 1301 may also store data. The instructions and data may also be sent and received via a network interface device over a network, where the network interface device may employ any known transmission protocol.

[0138] The memory 1301 may be integrated with the processor 1302, for example, by arranging RAM or flash memory within an integrated circuit microprocessor, etc. In addition, the memory 1301 may include a separate device, such as an external disk drive, a storage array, or other storage devices that can be used by any database system. The memory 1301 and the processor 1302 may be operatively coupled or may communicate with each other, for example, via an I / O port, a network connection, etc., such that the processor 1302 can read files stored in the memory.

[0139] In addition, the computer device 1300 may also include a video display (such as a liquid crystal display) and a user interaction interface (such as a keyboard, a mouse, a touch input device, etc.). All components of the computer device 1300 may be connected to each other via a bus and / or a network.

[0140] The present disclosure provides a method and device for correcting airfoil aerodynamic characteristic data, a method and device for determining blade aerodynamic performance data, a computer-readable storage medium, and a computer device. By conducting aerodynamic characteristic experiments on a reference blade covered with topcoat, the aerodynamic characteristic data of the corresponding reference airfoil considering the influence of the topcoat can be obtained. Then, by combining the original aerodynamic characteristic data and the aerodynamic characteristic data of the topcoat, correction parameters can be determined, which can more clearly reflect the influence of the topcoat on the aerodynamic characteristics of the airfoil. On this basis, by using the correction parameters to correct the original aerodynamic characteristic data of the target airfoil, the aerodynamic characteristic data of other airfoils (i.e., the target airfoil) after covering the topcoat can be inferred by using a small number of experiments (i.e., the experiments on the reference airfoil), as the corrected aerodynamic characteristic data, so that the corrected aerodynamic characteristic data of the airfoil is more in line with the actual operating conditions, which helps to clarify the influence of the topcoat on the blade aerodynamic performance, improve the understanding of the operating states of the blade and the unit, and improve the consistency of the simulation and testing of the blade and the whole machine.

[0141] The specific embodiments of the present disclosure have been described in detail above. Although some embodiments have been shown and described, those skilled in the art should understand that these embodiments can be modified and varied without departing from the principles and spirit of the present disclosure defined by the claims and their equivalents, and these modifications and variations should also be within the protection scope of the claims of the present disclosure.

Claims

1. A method for correcting airfoil aerodynamic characteristic data, characterized in that, The method for correcting airfoil aerodynamic characteristic data includes: Obtaining the original aerodynamic characteristic data of a reference airfoil and the aerodynamic characteristic data of the topcoat, wherein the aerodynamic characteristic data of the topcoat is data obtained through an aerodynamic characteristic experiment on a reference airfoil model covered with the topcoat, and the reference airfoil model is an equal airfoil polished model having the reference airfoil; Performing a fitting process on the original aerodynamic characteristic data of the reference airfoil and the aerodynamic characteristic data of the topcoat to obtain correction parameters; Obtaining the original aerodynamic characteristic data of a target airfoil; Correcting the original aerodynamic characteristic data of the target airfoil according to the correction parameters to obtain the corrected aerodynamic characteristic data of the target airfoil.

2. The method for correcting airfoil aerodynamic characteristic data according to claim 1, wherein the aerodynamic characteristic data of the topcoat is the aerodynamic characteristic data of the reference airfoil in the case of being covered with a target roughness topcoat; the topcoat roughness of the target airfoil is within a target roughness range, and the target roughness range is related to the target roughness.

3. The method for correcting airfoil aerodynamic characteristic data according to claim 1, wherein the relative thickness of the target airfoil is within a target relative thickness range, and the target relative thickness range is related to the relative thickness of the reference airfoil.

4. The method for correcting airfoil aerodynamic characteristic data according to claim 2, characterized in that, The method for correcting airfoil aerodynamic characteristic data further includes: Obtaining a plurality of roughness sampling values of a to-be-tested blade, wherein the to-be-tested blade is a blade designed based on the reference airfoil and covered with a topcoat; Performing a statistical process on the plurality of roughness sampling values to obtain the target roughness.

5. The method for correcting airfoil aerodynamic characteristic data according to claim 2, characterized in that, Obtaining the aerodynamic characteristic data of the topcoat of the reference airfoil includes: Obtaining at least one first experimental aerodynamic characteristic data and at least one second experimental aerodynamic characteristic data, wherein the first experimental aerodynamic characteristic data is data obtained through an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness less than the target roughness, and the second experimental aerodynamic characteristic data is data obtained through an aerodynamic characteristic experiment on a reference airfoil model with a topcoat roughness greater than the target roughness; Performing an interpolation process on the at least one first experimental aerodynamic characteristic data and the at least one second experimental aerodynamic characteristic data according to the target roughness to obtain the aerodynamic characteristic data of the topcoat.

6. The method for correcting airfoil aerodynamic characteristic data according to claim 2, wherein the reference airfoil model covered with the topcoat is a model obtained by covering the surface of the reference airfoil model with the topcoat according to reference process parameters, and the reference process parameters are the process parameters used when processing the topcoat of the to-be-tested blade, and the to-be-tested blade is a blade designed based on the reference airfoil; the target roughness is obtained by querying process-roughness control information based on the reference process parameters, and the process-roughness control information is used to record process parameters and corresponding topcoat roughnesses, and / or, the target roughness is obtained by measuring the reference airfoil model covered with the topcoat.

7. The method for correcting airfoil aerodynamic characteristic data according to any one of claims 1 to 6, wherein A separable protective film is provided between the reference airfoil model and the topcoat, and the error of the surface roughness of the separable protective film relative to the surface roughness of the reference airfoil model is less than the error threshold.

8. The method for correcting airfoil aerodynamic characteristic data according to any one of claims 1 to 6, characterized in that According to the different degrees of surface roughness of the blade, the surface conditions of the blade include a clean condition and a rough condition. The clean condition corresponds to a polished surface without a topcoat, and the rough condition corresponds to a surface that makes the airfoil flow reach a fully turbulent state. The original aerodynamic characteristic data includes the clean aerodynamic characteristic data under the clean condition; The correction parameter includes at least one of a fusion ratio and a correction amount. Wherein, the original aerodynamic characteristic data further includes the rough aerodynamic characteristic data under the rough condition, and the fusion ratio is used to fuse the clean aerodynamic characteristic data and the rough aerodynamic characteristic data of the reference airfoil so that the fused result approaches the aerodynamic characteristic data of the topcoat. The correction amount includes at least one of an absolute correction value and a correction ratio, and the correction amount is used to correct the clean aerodynamic characteristic data of the reference airfoil so that the corrected result approaches the aerodynamic characteristic data of the topcoat.

9. A method for determining the aerodynamic performance data of a blade, characterized in that, The method for determining the aerodynamic performance data of the blade includes: Obtaining the basic airfoil used in the design stage of the target blade and the corrected aerodynamic characteristic data of the basic airfoil; Determining the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil. Wherein, the corrected aerodynamic characteristic data of the basic airfoil is obtained by the method for correcting airfoil aerodynamic characteristic data according to any one of claims 1 to 8.

10. A correction device for airfoil aerodynamic characteristic data, characterized in that, The device for correcting airfoil aerodynamic characteristic data includes: A reference acquisition unit configured to acquire the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data of the reference airfoil. The topcoat aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with a topcoat, and the reference airfoil model is an equal airfoil polished model having the reference airfoil. A fitting unit configured to perform fitting processing on the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data of the reference airfoil to obtain correction parameters. A target acquisition unit configured to acquire the original aerodynamic characteristic data of the target airfoil. A correction unit configured to correct the original aerodynamic characteristic data of the target airfoil according to the correction parameters to obtain the corrected aerodynamic characteristic data of the target airfoil.

11. A device for determining blade aerodynamic performance data, characterized in that, The device for determining the aerodynamic performance data of the blade includes: An acquisition unit configured to acquire the basic airfoil used in the design stage of the target blade and the corrected aerodynamic characteristic data of the basic airfoil. A determination unit configured to determine the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil. Wherein, the corrected aerodynamic characteristic data of the basic airfoil is obtained by the method for correcting airfoil aerodynamic characteristic data according to any one of claims 1 to 8.

12. A computer-readable storage medium, characterized in that, When the instructions in the computer-readable storage medium are run by at least one processor, the at least one processor is caused to execute the method for correcting airfoil aerodynamic characteristic data according to any one of claims 1 to 8 or the method for determining blade aerodynamic performance data according to claim 9.

13. A computer device, characterized in that, Comprising: At least one processor; At least one memory storing computer-executable instructions, wherein, when the computer-executable instructions are run by the at least one processor, the at least one processor is caused to execute the method for correcting airfoil aerodynamic characteristic data according to any one of claims 1 to 8 or the method for determining blade aerodynamic performance data according to claim 9.

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