Airfoil aerodynamic characteristic data correction method and apparatus, and storage medium

Abstract

The present disclosure provides an airfoil aerodynamic characteristic data correction method and apparatus, and a storage medium. The method comprises: acquiring raw aerodynamic characteristic data of a reference airfoil and topcoat aerodynamic characteristic data; performing fitting processing on the acquired data to obtain a correction parameter; acquiring raw aerodynamic characteristic data of a target airfoil; and on the basis of the correction parameter, correcting the raw aerodynamic characteristic data of the target airfoil to obtain the corrected aerodynamic characteristic data of the target airfoil. The present disclosure can improve the consistency of simulation and testing.

Description

Method, device and storage medium for correcting airfoil aerodynamic characteristic data Technical Field

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

[0002] At present, the capacity of wind turbines is increasing, and the blades are getting longer and longer. Blades are a vital component of wind turbines, and the aerodynamic performance of blades directly affects the power generation efficiency of wind turbines. Blade design is based on Blade Element Momentum Theory (BEM), which is interpolated from several standard airfoils and designed with relative thickness, chord length, and twist angle distributed in a certain span direction (the length direction of the blade extension). 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 an important data for measuring the aerodynamic performance of the airfoil. Therefore, in order 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 testing is a relatively reliable method for obtaining airfoil aerodynamic data. However, these tests typically use airfoil models that have been meticulously ground and polished to ensure maximum consistency between the blade shape and theoretical specifications. Furthermore, actual wind turbine blades are also coated with a topcoat. The precise impact of topcoat on airfoil aerodynamic data and blade performance is unclear, but research on this topic is limited within the industry.

[0004] Summary of the Invention

[0005] Therefore, understanding the aerodynamic characteristics data of the airfoil covered with topcoat is crucial to clarifying the impact of topcoat on the aerodynamic performance of the blade.

[0006] In a general aspect, a method for correcting aerodynamic characteristic data of an airfoil is provided, the method comprising: obtaining original aerodynamic characteristic data and topcoat aerodynamic characteristic data of a reference airfoil, wherein the topcoat aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with topcoat, and the reference airfoil model is an isotropic polished model having the reference airfoil; fitting the original aerodynamic characteristic data of the reference airfoil and the topcoat aerodynamic characteristic data to obtain correction parameters; obtaining original aerodynamic characteristic data of a 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.

[0007] In another general aspect, a method for determining aerodynamic performance data of a blade is provided, the method comprising: obtaining a basic airfoil used in a design phase of a target blade and corrected aerodynamic characteristic data of the basic airfoil; and determining the aerodynamic performance data of the target blade based on the corrected aerodynamic characteristic data of the basic airfoil, wherein the corrected aerodynamic characteristic data of the basic airfoil is obtained by a method for correcting airfoil aerodynamic characteristic data according to an embodiment of the present disclosure.

[0008] In another general aspect, a device for correcting airfoil aerodynamic characteristic data is provided, the device comprising: a reference acquisition unit configured to acquire original aerodynamic characteristic data and topcoat aerodynamic characteristic data of a reference airfoil, wherein the topcoat aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with topcoat, and the reference airfoil model is an isotropic polished model having the reference airfoil; a fitting unit configured to perform fitting processing on the original aerodynamic characteristic data of the reference airfoil and the topcoat aerodynamic characteristic data to obtain correction parameters; a target acquisition unit configured to acquire original aerodynamic characteristic data of a target airfoil; and a correction unit configured to perform correction processing on the original aerodynamic characteristic data of the target airfoil according to the correction parameters to obtain corrected aerodynamic characteristic data of the target airfoil.

[0009] In another general aspect, a device for determining aerodynamic performance data of a blade is provided, the device comprising: an acquisition unit configured to acquire a basic airfoil used in a design phase 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 based on the corrected aerodynamic characteristic data of the basic airfoil, wherein the corrected aerodynamic characteristic data of the basic airfoil is obtained by a method for correcting airfoil aerodynamic characteristic data according to an embodiment of the present disclosure.

[0010] In another general aspect, a computer-readable storage medium is provided, which, when instructions in the computer-readable storage medium are executed by at least one processor, causes the at least one processor to execute a method for correcting airfoil aerodynamic characteristic data or a method for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0011] In another general aspect, a computer device is provided, comprising: at least one processor; and at least one memory storing computer-executable instructions, wherein the computer-executable instructions, when executed by the at least one processor, cause the at least one processor to execute a method for correcting airfoil aerodynamic characteristic data or a method for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0012] The present disclosure proposes a method and device for correcting aerodynamic characteristic data of an airfoil, a method and device for determining aerodynamic performance data of a blade, a computer-readable storage medium, and a computer device. By conducting an aerodynamic characteristic experiment on a reference airfoil model covered with topcoat, the topcoat aerodynamic characteristic data of the corresponding reference airfoil after considering the influence of the topcoat can be obtained, thereby combining the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data to determine the correction parameters, 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, a small amount of experiments (i.e., experiments on the reference airfoil) can be used to infer the aerodynamic characteristic data of other airfoils (i.e., the target airfoil) after being covered with topcoat, as the corrected aerodynamic characteristic data, so that the aerodynamic characteristic data of the airfoil after correction is more consistent with the actual operating conditions, which helps to clarify the influence of the topcoat on the aerodynamic performance of the blade, improve the understanding of the operating status of the blade and the unit, and improve the consistency of the simulation and test of the blade and the whole machine.

[0013] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The above and other objects and features of the present invention will become more apparent through the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0015] FIG1 is an aerodynamic characteristic curve showing how the lift coefficient varies with the angle of attack.

[0016] FIG2 is an aerodynamic characteristic curve showing how the drag coefficient varies with the angle of attack.

[0017] FIG3 is an aerodynamic characteristic curve showing how the pitching moment coefficient varies with the angle of attack.

[0018] FIG4 is an aerodynamic characteristic curve showing how the lift-to-drag ratio varies with the angle of attack.

[0019] FIG5 is a flowchart illustrating a method for correcting aerodynamic characteristic data of an airfoil according to an embodiment of the present disclosure.

[0020] FIG6 is a clean aerodynamic characteristic curve and a paint aerodynamic characteristic curve showing the lift coefficient changing with the angle of attack according to a specific embodiment of the present disclosure.

[0021] FIG. 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.

[0022] FIG8 is a diagram showing a clean aerodynamic characteristic curve and a paint aerodynamic characteristic curve of pitching moment coefficient varying with angle of attack according to a specific embodiment of the present disclosure.

[0023] FIG9 is a clean aerodynamic characteristic curve and a paint aerodynamic characteristic curve showing lift-to-drag ratio changes with angle of attack according to a specific embodiment of the present disclosure.

[0024] FIG10 is a flowchart illustrating a method for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0025] FIG11 is a block diagram illustrating an apparatus for correcting aerodynamic characteristic data of an airfoil according to an embodiment of the present disclosure.

[0026] FIG12 is a block diagram illustrating an apparatus for determining blade aerodynamic performance data according to an embodiment of the present disclosure.

[0027] FIG13 is a block diagram illustrating a computer device according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0028] The following detailed description is provided to help the reader gain a comprehensive understanding of the methods, devices and / or systems described herein. However, various changes, modifications and equivalents of the methods, devices and / or systems described herein will be clear after understanding the disclosure of the present application. For example, the order of operations described herein is merely an example and is not limited to those orders set forth herein, but can be changed as will be clear after understanding the disclosure of the present application, except for operations that must occur in a specific order. In addition, for greater clarity and conciseness, descriptions of features known in the art may be omitted.

[0029] The features described herein can be implemented in different forms and should not be construed as limited to the examples described herein. Rather, the examples described herein are provided to illustrate only some of the many possible ways to implement the methods, devices, and / or systems described herein, which will become clear after understanding the disclosure of this application.

[0030] As used herein, the term "and / or" includes any one of the associated listed items and any combination of any two or more.

[0031] Although terms such as "first," "second," and "third" may be used herein to describe various members, components, regions, layers, or portions, these members, components, regions, layers, or portions should not be limited by these terms. Instead, these terms are used solely to distinguish one member, component, region, layer, or portion from another member, component, region, layer, or portion. Thus, what is referred to as a first member, first component, first region, first layer, or first portion in the examples described herein may also be referred to as a second member, second component, second region, second layer, or second portion without departing from the teachings of the examples.

[0032] In the specification, when an element (such as a layer, region, or substrate) is described as being “on,” “connected to,” or “coupled to” another element, the element may be directly “on,” “connected to,” or “coupled to” the other element, or one or more other elements may be present therebetween. Conversely, when an element is described as being “directly on,” “directly connected to,” or “directly coupled to” another element, there may be no other elements present therebetween.

[0033] The terms used herein are only used to describe various examples and are not intended to limit the disclosure. Unless the context clearly indicates otherwise, the singular is intended to include the plural. The terms "comprise," "include," and "have" indicate the presence of the recited 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.

[0034] Unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which the present disclosure pertains after understanding the present disclosure. Unless expressly defined otherwise herein, terms (such as those defined in general dictionaries) should be interpreted as having a meaning consistent with their meaning in the context of the relevant art and the present disclosure, and should not be interpreted in an idealized or overly formal manner.

[0035] Furthermore, in describing the examples, when it is deemed that a detailed description of well-known related structures or functions would cause ambiguous interpretation of the present disclosure, such detailed description will be omitted.

[0036] The aerodynamic design of a blade is the designer's selection of different standard airfoils and the selection of design lift points. The blade's spanwise lift coefficient, relative thickness, chord length, twist angle, pre-bend, sweep, and other aerodynamic shape parameters are designed using blade element momentum theory. The standard airfoils used in blade design can be publicly available airfoils in the industry, such as the NACA (National Advisory Committee for Aeronautics) airfoil series, the DU (Delft University) airfoil series (a family of airfoils designed by the Delft University of Technology for wind turbine blades), or they can be airfoils designed by the blade developer themselves. The former are often accompanied by publicly available aerodynamic characteristic data, while the latter are proprietary to the blade developer. However, in either case, wind tunnel testing remains the technical means to obtain accurate and reliable aerodynamic characteristic data for the airfoil.

[0037] In experiments, a two-dimensional airfoil model of the airfoil shape is usually processed and the aerodynamic characteristic data of the airfoil is obtained through pressure measurement or force measurement technology. Specifically, the values ​​of certain specific aerodynamic parameters under different incoming flow conditions are measured in the experiment. These aerodynamic parameters include but are not limited to the lift coefficient CL (Lift Coefficient), the drag coefficient Cd (Drag Coefficient), the pitch moment coefficient Cm (Moment Coefficient), and the lift-to-drag ratio K (CL / Cd). The curves of these aerodynamic parameters changing with the angle of attack (ALPHA) (such as Figures 1 to 4) or the curves with the xy axes as the x and y axes are called the aerodynamic characteristic curves of the airfoil. They can be used as the aerodynamic characteristic data of the airfoil and participate in the calculation of the aerodynamic performance of the blade (the aerodynamic performance of the blade is often expressed by parameters such as load and power coefficient). In other words, the aerodynamic performance of the blade is directly related to the aerodynamic characteristic curve presented by the standard airfoil.

[0038] The airfoil models used in the experiment are usually made of metal or carbon fiber materials, and the surface is finely ground and polished to ensure maximum consistency between the appearance and the theory. The material system of the actual blade is currently composed of 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 the wind tunnel experiment, but due to the characteristics of the paint, it presents a surface with a certain roughness similar to orange peel. However, when the blade surface is in such a state, will the aerodynamic characteristics of the airfoil change relative to the aerodynamic characteristics of the airfoil model in the wind tunnel experiment? If so, how much will it change? How big is the impact on the entire machine? These issues are currently little studied in the domestic industry and even worldwide, but they are issues that must be faced in dealing with the consistency of blade and overall machine performance.

[0039] The following will introduce the airfoil aerodynamic characteristic data correction method and device, blade aerodynamic performance data determination method and device, computer-readable storage medium, and computer equipment provided by the embodiments of the present disclosure in conjunction with Figures 1 to 13.

[0040] An embodiment of one aspect of the present disclosure provides a method for correcting aerodynamic characteristic data of an airfoil. FIG5 is a flow chart illustrating a method for correcting aerodynamic characteristic data of an airfoil according to an embodiment of the present disclosure.

[0041] 5 , in step S501 , original aerodynamic characteristic data and topcoat aerodynamic characteristic data of a reference airfoil are acquired.

[0042] Topcoat aerodynamic characteristic data is obtained by conducting aerodynamic characteristic experiments on a reference airfoil model covered with topcoat. For example, the aerodynamic characteristic experiment is a wind tunnel experiment, in which the aerodynamic characteristic data of an airfoil is obtained through pressure or force measurement techniques. Specifically, the data directly measured in the experiment are the aforementioned aerodynamic parameters, and the obtained aerodynamic characteristic data are aerodynamic characteristic curves. The reference airfoil model is a polished model of the reference airfoil, that is, a two-dimensional airfoil model with the reference airfoil shape, which is the blade form commonly used in existing wind tunnel experiments.

[0043] The original aerodynamic characteristic data refers to the existing aerodynamic characteristic data of the reference airfoil, and can also be obtained through wind tunnel experiments. Specifically, according to the different degrees of roughness of the airfoil model surface, the surface working conditions of the airfoil model include clean working conditions and rough working conditions. The clean working condition corresponds to the polished surface not covered with topcoat, and the reference airfoil model belongs to the clean working condition. The rough working condition corresponds to the surface that makes the airfoil flow reach a full turbulent state. The clean working condition and the rough working condition are two extreme working conditions of the airfoil model surface without destroying the appearance. The original aerodynamic characteristic data at least includes clean aerodynamic characteristic data under clean working conditions, which is also the airfoil aerodynamic characteristic data commonly used in the prior art when calculating blade performance. In addition, according to the actual needs of the solution, the original aerodynamic characteristic data may also include rough aerodynamic characteristic data under rough working conditions.

[0044] In step S502, the original aerodynamic characteristic data of the reference airfoil and the aerodynamic characteristic data of the topcoat are fitted to obtain correction parameters.

[0045] The correction parameters can represent the conversion relationship between the original aerodynamic characteristic data and the aerodynamic characteristic data of the topcoat.

[0046] Optionally, the correction parameter includes at least one of a fusion ratio and a correction amount, and the two correspond to a correction method respectively. 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 fusion result is close to the topcoat aerodynamic characteristic data, so that the aerodynamic characteristic data under two extreme working conditions can be combined to determine the aerodynamic characteristic data of the topcoat state (i.e., the state where the corresponding airfoil is covered with topcoat) between the two, 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 is close to the topcoat aerodynamic characteristic data, so that the correction can be achieved with the help of a small amount of original data, which helps to reduce data dependence in the correction process.

[0047] It should be noted that, as shown in Figures 1 to 4, aerodynamic characteristic curves often do not follow a consistent pattern; rather, they may exhibit sudden changes. For this reason, the correction parameter need not remain constant for all horizontal coordinate values, but can be segmented and varied based on actual conditions to fully ensure the accuracy of the correction results.

[0048] In step S503, original aerodynamic characteristic data of the target airfoil is obtained.

[0049] The target airfoil is the airfoil whose aerodynamic characteristic data needs to be corrected.

[0050] In step S504, the original aerodynamic characteristic data of the target airfoil is corrected according to the correction parameters to obtain corrected aerodynamic characteristic data of the target airfoil.

[0051] The corrected aerodynamic characteristic data are the estimated aerodynamic characteristic data of the target airfoil covered with the topcoat.

[0052] According to the method for correcting the aerodynamic characteristic data of an airfoil of an exemplary embodiment of the present disclosure, by conducting an aerodynamic characteristic experiment on a reference airfoil model covered with topcoat, the topcoat aerodynamic characteristic data of the corresponding reference airfoil after considering the influence of the topcoat can be obtained, thereby combining the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data to determine the correction parameters, 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, a small number of experiments (i.e., experiments on the reference airfoil) can be used to infer the aerodynamic characteristic data of other airfoils (i.e., the target airfoil) after being covered with topcoat, as the corrected aerodynamic characteristic data, so that the aerodynamic characteristic data of the airfoil after correction is more consistent with the actual operating conditions, which helps to clarify the influence of the topcoat on the aerodynamic performance of the blade, improve the understanding of the operating status of the blade and the unit, and improve the consistency of the simulation and test of the blade and the whole machine.

[0053] Next, a method for correcting aerodynamic characteristic data of an airfoil according to an exemplary embodiment of the present disclosure will be further introduced.

[0054] 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 target airfoils to correct their own aerodynamic characteristics using the correction parameters of that reference airfoil, it can be understood that this relationship describes the generalization range of the reference airfoil's correction parameters, that is, to which other airfoils can the reference airfoil's correction parameters be generalized and applied. By properly determining this relationship, the reliability of the correction results for the target airfoil can be improved.

[0055] Optionally, the reference airfoil and the target airfoil belong to the same airfoil family. An airfoil family is a group of airfoils with similar geometric and aerodynamic characteristics. These airfoils are typically derived from a common basic design by varying certain design parameters (e.g., relative thickness, camber, bend location, etc.). Different airfoils within the same airfoil family have similar aerodynamic characteristics, making generalizations between these airfoils more reliable.

[0056] Optionally, the topcoat aerodynamic characteristic data is the aerodynamic characteristic data of the reference airfoil when it is covered with a target roughness topcoat; the topcoat roughness of the target airfoil is within the target roughness interval, and the target roughness interval is related to the target roughness. The effect of the topcoat on the aerodynamic characteristics of the airfoil is likely to come 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, the correction parameters of the reference airfoil are extended to the airfoil whose topcoat roughness is within the target roughness interval, which helps to ensure the effectiveness of the extension and thus improve the reliability of the correction results for the target airfoil. It should be understood that the target roughness is also within the target roughness interval, 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 interval, experiments with different topcoat roughness can be carried out on the reference airfoil according to different requirements for the accuracy of the correction results, and then a reasonable target roughness interval can be determined by comparing the values ​​of the correction parameters corresponding to different topcoat roughnesses. As an example, the surface roughness of blades produced by different manufacturers in the industry that have reached the factory state, that is, the topcoat roughness, can be first obtained, and then the roughness range that can envelop most or all blades on the market can be statistically calculated, and then experiments are conducted on the two endpoint values ​​of the roughness range (that is, the two endpoint values ​​of the roughness range are used as target roughness, aerodynamic characteristics experiments are conducted, and steps S501 and S502 of the present disclosure are executed). 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 of the two is greater than or equal to the set ratio (such as 0.95), it is considered that the topcoat roughness will not affect the aerodynamic characteristics data. From the perspective of topcoat roughness, the correction parameters of the reference airfoil can be extended to any airfoil with other topcoat roughness. 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, then it is believed that the surface paint roughness will affect the aerodynamic characteristic data, and the roughness interval can be simply divided into two sections as two target roughness intervals, and the target roughness corresponding to each of these two target roughness intervals is the two corresponding endpoint values ​​of the original roughness interval. Of course, other roughnesses can be further selected in the original roughness interval for experiments, and the corresponding correction parameters can be determined. According to whether the various roughnesses that have been tested and their corresponding correction parameters are close, the original roughness interval is divided to obtain several target roughness intervals. At this time, the more roughnesses the experiment targets, the more accurate the division of the target roughness interval can be, but it also means that the cost to be paid is higher. In practice, the experiment can be reasonably designed based on the actual situation, and the present disclosure does not limit this.

[0057] Optionally, the relative thickness of the target airfoil lies 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 its maximum dimension perpendicular to the chord-wise direction. The chord-wise direction is the direction of the airfoil's chord line, which is the line connecting the airfoil's leading and trailing edges. The length of the chord line is called the chord length. To achieve dimensionlessness, the relative thickness of an airfoil is typically represented by the ratio of its thickness to its chord length. The relative thickness of an airfoil often significantly affects its aerodynamic characteristics. By using the relative thickness of the airfoil as a parameter to describe the relationship between the reference and target airfoils, the correction parameters for the reference airfoil can be generalized to airfoils with relative thicknesses within the target relative thickness range. This helps ensure the effectiveness of this generalization and, in turn, improves the reliability of the correction results for the target airfoil. Similar to paint roughness, the relative thickness of the reference airfoil also lies within the target relative thickness range. That is, the relative thicknesses of the reference and target airfoils should be relatively close. The target relative thickness range can be determined through appropriately designed experiments based on specific circumstances.

[0058] It should be understood that only the surface roughness can be used as a parameter to describe the relationship between the reference airfoil and the target airfoil, 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, and both the surface roughness and the relative thickness of the airfoil can be used 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, average interval roughness Rsm, relative material ratio Rmr, total profile roughness Pt, and slope of the material ratio curve Pmr. Therefore, at least one of these parameters can be selected as the surface roughness.

[0059] Optionally, after the correction parameters of multiple airfoils of different relative thicknesses within the same airfoil family (hereinafter referred to as the first airfoil family) at multiple target roughnesses have been obtained through experiments or further combined with the correction method disclosed herein, if it is necessary to correct a target airfoil in another airfoil family (hereinafter referred to as the 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 based on the correction parameters of the first airfoil family and the correction parameters of the reference airfoil in the second airfoil family; and correcting the original aerodynamic characteristic data of the target airfoil in the second airfoil family based on 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, the correction parameters of the reference airfoil in the second airfoil family are first corrected to obtain the correction parameters of the target airfoil in the second airfoil family, and then the aerodynamic characteristic data are corrected accordingly. This can further improve the promotion range 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 surface paint roughness of the two is equal, the correction parameters of the two can be recorded as the second 25% correction parameter (this is a known quantity) and the second 30% correction parameter (this is an unknown quantity), respectively. The correction parameters of the two airfoils with the same surface paint roughness and relative thicknesses of 25% and 30% in the first airfoil family are taken and recorded as the first 25% correction parameter and the first 30% correction parameter (both are known quantities), respectively. Then, an equation is established that 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.

[0060] 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 in order to clarify the target roughness range and reproduce the target roughness in the aerodynamic characteristics experiment. In other words, the topcoat roughness of the reference airfoil model covered with topcoat is equal to the target roughness.

[0061] In this regard, in some embodiments, the method for correcting the aerodynamic characteristic data of an airfoil according to the exemplary embodiment of the present disclosure further includes: obtaining a plurality of roughness sampling values ​​of the blade to be measured, wherein 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 that is 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, thereby ensuring the practicality of the experimental results. As an example, a plurality of dispersed spanwise positions can be selected along the spanwise direction of the blade to be measured for roughness collection, and for each spanwise position, only a specific area can be collected, for example, only the position area within 40% of the chord length from the leading edge in the chord direction is collected, because this part of the area has the most obvious impact on the aerodynamic performance of the blade, so as to improve the collection efficiency of the roughness sampling value. As an example, the purpose of statistical processing of multiple roughness sampling values ​​is to convert the multiple roughness sampling values ​​into a numerical value that is sufficient to represent the roughness of the surface paint of the blade to be tested, that is, the target roughness. Therefore, the statistical processing can be a process of calculating statistical values ​​(such as mean, median, mode, etc.), and data cleaning can also be performed before calculating the statistical values ​​to filter out obviously abnormal roughness sampling values. Statistical processing belongs to the existing technology of data processing and will not be expanded here. It should be understood that the statistical processing of roughness here is to convert multiple roughness sampling values ​​of the same blade (i.e., the blade to be tested) into one value to clarify the roughness of the blade, while the operation of calculating the roughness interval in the previous article is to collect the surface roughness of various blades already in the industry to determine the value range of these roughness values. The two are completely different processes.

[0062] 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, wherein the first experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model having a topcoat roughness less than a target roughness, and the second experimental aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model having a topcoat roughness greater than the target roughness; and interpolating 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 experimental data of different roughnesses on the left and right sides of the target roughness and then interpolating the target roughness data as the topcoat aerodynamic characteristic data, it is not necessary to strictly reproduce the target roughness during the experiment, which helps to reduce the difficulty of the experiment and improve the feasibility of the experiment.

[0063] As an example, for embodiments using at least two specific parameters to describe the roughness of the topcoat, two experimental data sets can be obtained for each specific parameter and interpolated to obtain aerodynamic characteristic data corresponding to each specific parameter. Statistical processing can then be performed on these interpolated aerodynamic characteristic data, and the statistical results can be used as the aerodynamic characteristic data for the topcoat. For example, in the case where both the arithmetic mean roughness Ra and the ten-point height average Rz are used, the aerodynamic characteristic data corresponding to the arithmetic mean roughness Ra and the aerodynamic characteristic data corresponding to the ten-point height average Rz can be obtained. Statistical processing can be performed on these two aerodynamic characteristic data sets, such as, but not limited to, calculating an average value or weighted summation, and the statistical results can be used as the aerodynamic characteristic data for the topcoat.

[0064] For each specific parameter's interpolation process, as an example, the weight of the experimental data can be determined based on the relationship between the specific parameter's value and the parameter values ​​to its left and right in the experiment. For example, for the target value Ra1 of the arithmetic mean roughness Ra and the two parameter values ​​Ra2 and Ra3 to its left and right, the values ​​of α and β in the equation Ra1 = αRa2 + βRa3 can be determined. Then, using α and β as weights, the experimental data are weighted and summed to obtain the aerodynamic characteristic data corresponding to the specific parameter Ra1. In addition, for points or regions where the trend of the aerodynamic characteristic curve undergoes a sudden change, the weight value can be locally adjusted to improve the rationality and, therefore, the accuracy of the interpolated aerodynamic characteristic data.

[0065] In 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 formed thereby is calculated in advance and recorded in the process-roughness comparison information. The target roughness can then 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 rolling the topcoat, the tool brand for spraying the topcoat), ambient temperature, ambient humidity, and the number of layers of applied topcoat. 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 and recorded as reference process parameters. The target roughness can be obtained by querying the process-roughness comparison information based on the reference process parameters. This allows the target roughness value to be obtained more reliably without obtaining the actual blade to be measured or without performing a measurement operation, thereby improving the convenience of obtaining the target roughness. In this case, the topcoat-coated reference airfoil model is a model obtained by coating the surface of the reference airfoil model with topcoat according to the reference process parameters. That is, by clarifying the reference process parameters and then directly applying them to the topcoat processing step of the reference airfoil model, a more direct correspondence between the reference airfoil model and the topcoat-coated reference airfoil to be tested is achieved, thereby achieving convenient and accurate reproduction of the target roughness in the aerodynamic characteristics experiment. In other words, only the airfoil model with the target roughness needs to be tested, which can reduce the number of experiments and reduce the experimental cost. Accordingly, since the experimental airfoil model reproduces the target roughness, the target roughness can also be obtained by measuring the experimental airfoil model, that is, by measuring the topcoat-coated reference airfoil model, which can further improve the accuracy of the determined target roughness. It should be understood that the above two methods can also be used simultaneously to obtain the target roughness, the first as a preliminary confirmation and the second as a pre-experimental verification. The two methods are generally consistent. If there is a difference, the verification result shall prevail. If the difference is large, the process-roughness comparison information can be corrected accordingly, which helps to improve the accuracy of the information.

[0066] 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 blades on the market. However, the standards for blade surface topcoat protection systems are not uniform for each blade manufacturer. This process is currently mostly completed by manual rolling or spraying in China and even internationally, and the rollers, paint systems, temperature and humidity, etc. used are all different. Therefore, the surface conditions of the blades after the topcoat is applied vary greatly. Although manufacturers usually test the roughness of the blades they produce (i.e., the topcoat roughness), the measurement tools and tool parameter settings used by different manufacturers are often different, resulting in the roughness obtained directly from the manufacturer not having a uniform standard. By first collecting the topcoat process parameters of various manufacturers, and then uniformly measuring a large number of topcoat samples obtained according to different process parameters, and statistically calculating the process-roughness comparison information, it is possible to study the influence of different sensitive process parameters such as paint, roller, temperature and humidity on the surface state of the topcoat after molding. Then, based on the topcoat process parameters of a certain blade, the process-roughness comparison information is queried to obtain the topcoat roughness of the blade under the unified standard, thereby innovatively using the topcoat process parameters of the blade to uniformly evaluate the topcoat surface state of the blade, which helps to achieve data standardization and can flexibly and conveniently obtain the topcoat roughness of newly produced blades. As an example, the topcoat samples used in the unified measurement can be samples provided by the manufacturer, and are sampled and counted according to the method for obtaining the target roughness described above, that is, multiple roughness sampling values ​​are measured for the topcoat sample, and then statistical processing is performed 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 blade, and the present disclosure is not limited to this.

[0067] In addition, in some embodiments, optionally, a detachable 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 detachable protective film relative to the surface roughness of the reference airfoil model is less than an error threshold. By first covering the reference airfoil model with a detachable protective film and then covering it with topcoat, the topcoat can be easily removed by separating the protective film after the experiment is completed, thereby achieving the reuse of the reference airfoil model and helping to significantly reduce the experimental cost. Of course, the reference airfoil model can also be reused in experiments in other scenarios outside the scenario of the present invention, and the reference airfoil model can even be borrowed from experiments in other scenarios to further reduce the cost of using the reference airfoil model. In addition, compared to coatings, membranous structures are easier to control their surface roughness. By making the surface roughness of the detachable protective film close to that of the reference airfoil model, the introduction of other roughness can be reduced as much as possible, thereby ensuring the validity of the experimental results.

[0068] For example, a reference airfoil model used in an experiment typically has a pressure tapping hole on its surface to accommodate the pressure sensor probe used for testing. To accomplish this, a removable protective film is first applied to the surface of the reference airfoil. A hole is then drilled where the film covers the pressure tapping hole, and both the hole and the pressure tapping hole are blocked. After painting, the blockage is removed, resulting in an experimental airfoil model covered with the removable protective film and topcoat, and equipped with a pressure tapping hole.

[0069] Next, in conjunction with a specific embodiment, a method for correcting the aerodynamic characteristic data of an airfoil according to an exemplary embodiment of the present disclosure is introduced. The overall logic of this specific embodiment is to use a specific blade surface paint roughness measurement method to obtain a certain statistical amount of paint roughness data. Specific parameters that can be used include but are not limited to the arithmetic mean roughness Ra, the ten-point height average Rz, the root mean square roughness Rq, the total height Rt, the profile roughness curve length Rc, the average interval roughness Rsm, the relative material ratio Rmr, the total profile unevenness Pt, the slope of the material ratio curve Pmr, etc.; after the surface of the reference airfoil model in the wind tunnel experiment is rolled with paint, a certain statistical amount of paint roughness data is measured, and the aerodynamic characteristic data of the airfoil under different incoming flow conditions is measured. Through roughness data analysis and quantitative 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 a method of actually measuring the paint roughness of the blade to be tested.

[0070] Specifically, the above logic mainly includes the following three parts.

[0071] Part 1: Data collection of blade surface paint roughness.

[0072] A) Sampling area of ​​the leaf to be tested.

[0073] Select one or more leaves to be tested and observe the storage posture of the leaves. Each leaf includes but is not limited to three sampling areas: the root, middle, and tip of the leaf.

[0074] If the blade is placed vertically with the leading edge facing down and the trailing edge facing up, the maximum chord length area of ​​the suction surface (near the blade root), the left and right areas of the middle bracket (located in the middle of the blade), the starting area of ​​the navigation paint or the area within 10 meters from the blade tip (located at the blade tip) are selected in the span direction. For these three span-wise position areas, the area within 40% of the chord length from the leading edge is further selected in the chord direction. Each area is about 0.2m 2 .

[0075] If the blade is placed horizontally with the pressure side facing upward, then similarly select the area with the maximum chord length, the area around the middle bracket, the starting area of ​​the navigation paint, or the area within 10 meters from the blade tip in the span direction. In the chord direction, select the area within 40% of the chord length from the leading edge. The suction side is preferred. If it is inconvenient to measure, the pressure side can be selected, and the roughness meter must be able to be stably placed on the surface.

[0076] The above two sampling areas are sampled on the surface of the topcoat, avoiding the areas where the leading edge protection system, lightning rods and surface markings are located.

[0077] B) Sampling point selection.

[0078] In each sampling area selected above, select a 40cm*40cm square area where the paint coating quality is uniform both visually and by touch, and mark 25 sampling points (5*5) with a marker or pencil, with a distance of 10cm between each two sampling points, to form a sampling point array.

[0079] C) Measurement steps.

[0080] The measurement operation is carried out in the following steps:

[0081] 1) Based on the storage posture of the leaves, select a suitable sampling area according to the example in Section A.

[0082] 2) Within each sampling area, mark the sampling points according to the examples in Section B.

[0083] 3) Setting the measurement parameters of the roughness meter. It should be understood that for the embodiment of statistical process-roughness comparison information, when a large number of topcoat samples are uniformly measured, the same model of roughness meter as used herein is also used, and the measurement parameters are set consistent with those used herein to ensure the use of a unified measurement standard in different embodiments.

[0084] 4) Use the calibration plate that comes with the roughness meter to perform calibration measurements. The number of measurements should be no less than 3 times. The deviation of the measured value (generally the arithmetic mean roughness Ra) should converge to less than 0.05μm. Set the calibration to be completed and record the calibration data.

[0085] 5) At the marked sampling points, use a calibrated roughness meter to measure the roughness values ​​at each location. Record the roughness data, including but not limited to the arithmetic average roughness Ra, the ten-point height average Rz, and the root mean square roughness Rq, and organize the data into a table. Some instruments equipped with host computer software can semi-automatically measure, record, store, and transmit data.

[0086] 6) Perform statistics on the sampled roughness result data and obtain the statistical value as the target roughness.

[0087] Part 2: Conduct wind tunnel experiments on the reference airfoil model to obtain the aerodynamic characteristics data of the topcoat.

[0088] Based on the topcoat roughness value obtained in the first part (i.e., the target roughness), the surface of the reference airfoil model is painted in a wind tunnel experiment to reproduce the target roughness, and the experiment is conducted using the reproduced airfoil model. In the process of reproducing the target roughness, there are often cases where the target roughness measured in the early stage cannot be matched. In this case, 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 through experiments. Then, combined with the target roughness, the aerodynamic characteristic data obtained in the experiment are interpolated to obtain the topcoat aerodynamic characteristic data of the reference airfoil that meets the actual target roughness.

[0089] It is known from the knowledge of aerodynamics that when the surface state of the model changes, it will affect the aerodynamic characteristics of the airfoil (especially the development of the boundary layer and related parameters), and the key aerodynamic characteristic parameters obtained in the present disclosure are the lift coefficient CL, drag coefficient Cd, pitch moment coefficient Cm, and lift-to-drag ratio K of the airfoil when the surface is covered with topcoat. After analyzing the data obtained after the wind tunnel experiment, it was concluded that the aerodynamic characteristics of the airfoil with topcoat changed significantly, as shown in the following: the lift coefficient CL decreased to a certain extent, the drag coefficient Cd increased to a certain extent, the pitch moment coefficient Cm increased to a certain extent, the lift-to-drag ratio K decreased to a certain extent, and the stall angle of attack was advanced to a certain extent. The changes in the typical aerodynamic characteristic curves are shown in Figures 6 to 9, which respectively show the clean aerodynamic characteristic curves under clean conditions and the topcoat aerodynamic characteristic curves under topcoat conditions.

[0090] Part 3: Determine the aerodynamic characteristics data of the airfoil when considering the blade surface finish.

[0091] This section has two forms:

[0092] 1) Directly use the aerodynamic characteristic data of the reference airfoil at the target roughness, as measured by the wind tunnel experiment in Part 2 above. In other words, proceed directly with the experiment in Part 2. The advantage of this approach is that the data is reliable and authentic, which improves the consistency between calculation and test. However, the disadvantage is that surface roughness cannot be precisely controlled manually and has many sensitive variables; multiple tests at different roughness levels are required to enrich the available aerodynamic characteristic data.

[0093] 2) Based on the original aerodynamic data of a known airfoil obtained through existing wind tunnel experiments or numerical simulations, this data is compared with the topcoat aerodynamic data obtained from the second part of the test on that airfoil to determine correction parameters. These correction parameters are then applied to other airfoils, thereby obtaining corrected aerodynamic data that takes the topcoat into account based on the original aerodynamic data of the other airfoils. For example, the original aerodynamic data may include clean aerodynamic data under clean conditions and rough aerodynamic data under rough conditions. The correction parameter is the fusion ratio between the two. To determine the fusion ratio, a numerical fitting method can be used to fuse the two data using the fusion ratio and compare it with the topcoat aerodynamic data obtained from the second part of the test to find a close fit. The advantage of this approach is that it eliminates the need for the financial and human resources required to measure the topcoat aerodynamic data of different airfoils, allowing for approximation through numerical calculation and fitting. To improve the accuracy of the approximation, wind tunnel experiments can be conducted on multiple airfoils and various topcoat roughness levels to more accurately determine the appropriate correction parameter values ​​for different airfoils and topcoat roughness levels.

[0094] Regardless of which of the above forms is used, the final aerodynamic characteristic data taking the topcoat into consideration are closer to the actual state of the blade with paint after leaving the factory than the aerodynamic characteristic data obtained by direct experiment or computational simulation of standard airfoil after fine polishing of the metal or composite material surface, which helps to improve the consistency of simulation tests of blade performance and overall machine performance.

[0095] The embodiment of the second aspect of the present disclosure provides a method for determining aerodynamic performance data of a blade. Figure 10 is a flow chart illustrating a method for determining aerodynamic performance data of a blade according to an embodiment of the present disclosure.

[0096] 10 , in step S1001 , a basic airfoil used in the design phase of a target blade and corrected aerodynamic characteristic data of the basic airfoil are obtained.

[0097] The base airfoil is the standard airfoil used in blade design. Blade design often uses multiple standard airfoils, and this step can be performed separately for each standard airfoil.

[0098] In step S1002 , the aerodynamic performance data of the target blade is determined according to the corrected aerodynamic characteristic data of the basic airfoil.

[0099] Among them, the corrected aerodynamic characteristic data of the basic airfoil is obtained by the correction method of the airfoil aerodynamic characteristic data provided by any embodiment of the first aspect of the present disclosure, that is, the corrected aerodynamic characteristic data obtained by using the correction method is applied to the blade performance calculation, and of course it can also be further applied to the performance calculation of the entire wind turbine generator set. Therefore, the method for determining the blade aerodynamic performance data of the embodiment of the present disclosure has all the beneficial technical effects of the correction method of the airfoil aerodynamic characteristic data, which will not be repeated 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 entire machine can be calculated and analyzed more closely to physical reality, and used to guide the performance and load calculation of the entire machine in different application environments, thereby improving the reliability of blade and unit development.

[0100] The calculation method in step S1002 can refer to the method for determining the aerodynamic performance data of a blade based on the clean aerodynamic characteristic data of a basic airfoil, except that the clean aerodynamic characteristic data is replaced with the modified aerodynamic characteristic data. Simply put, based on the blade element momentum theory, the blade is considered as a whole composed of multiple blade elements distributed along the span. For each blade element, since the airfoil of the current blade element is obtained by interpolating multiple standard airfoils during design, the modified aerodynamic characteristic curves of the multiple standard airfoils can also be interpolated to obtain the modified aerodynamic characteristic curve of the airfoil of the current blade element. The lift and drag of the current blade element are then calculated based on this curve and the state of the incoming flow (e.g., the incoming flow angle and local flow velocity). 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 calculated by combining the torque and the design speed of the impeller, thereby obtaining the blade power coefficient (the ratio of the actual output power to the total wind power). These data can be used as the aerodynamic performance data of the blade.

[0101] Through actual calculations, it was found that after using the topcoat aerodynamic characteristic data and the corrected aerodynamic characteristic data that took into account the topcoat state, the power generation calculation results of the whole machine were reduced to a certain extent compared with the situation calculated using the clean aerodynamic characteristic data. The ultimate load and fatigue load of large components including blades have changed to varying degrees, and the overall result is closer to the actual operation of the unit. Specifically, the reasonable calculation of power generation can avoid the compensation losses caused by overestimation of power generation and substandard performance in the later stage. For the calculation of load, the part of the calculation result that is reasonably increased compared to the existing calculation method can capture the situation where the design scheme meets the load requirements more quickly, thereby reducing the workload of design simulation iterations; the part of the calculation result that is reasonably reduced compared to the existing calculation method can more truthfully reflect the fact that the current scheme has insufficient carrying capacity, thereby reducing the risk of the actual operating load of the unit exceeding the limit.

[0102] In a third aspect, an embodiment of the present disclosure provides a device for correcting airfoil aerodynamic characteristic data. FIG11 is a block diagram illustrating a device for correcting airfoil aerodynamic characteristic data according to an embodiment of the present disclosure. Referring to FIG11 , the device 1100 for correcting airfoil aerodynamic characteristic data includes a reference acquisition unit 1101, a fitting unit 1102, a target acquisition unit 1103, and a correction unit 1104.

[0103] The reference acquisition unit 1101 can obtain the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data of the reference airfoil, wherein the topcoat aerodynamic characteristic data is data obtained by performing an aerodynamic characteristic experiment on a reference airfoil model covered with topcoat, and the reference airfoil model is an isotropic polished model with a reference airfoil.

[0104] The fitting unit 1102 may 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.

[0105] The target acquisition unit 1103 can acquire the original aerodynamic characteristic data of the target airfoil;

[0106] The correction unit 1104 may 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.

[0107] Optionally, the topcoat aerodynamic characteristic data is aerodynamic characteristic data of a reference airfoil when covered with a topcoat of target roughness; the topcoat roughness of the target airfoil is within a target roughness interval, and the target roughness interval is related to the target roughness.

[0108] Optionally, the relative thickness of the target airfoil is within a target relative thickness interval, and the target relative thickness interval is related to the relative thickness of the reference airfoil.

[0109] Optionally, the correction device for the aerodynamic characteristic data of the airfoil also includes a sampling unit (not shown in the figure) and a statistical unit (not shown in the figure). The sampling unit can obtain multiple roughness sampling values ​​of the blade to be tested, wherein the blade to be tested is a blade designed based on the reference airfoil and covered with topcoat; the statistical unit can perform statistical processing on the multiple roughness sampling values ​​to obtain the target roughness.

[0110] Optionally, the reference acquisition unit 1101 can also: acquire 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 by performing an aerodynamic characteristic experiment on a reference airfoil model with a paint roughness less than a 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 paint roughness greater than a target roughness; and interpolate 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 paint aerodynamic characteristic data.

[0111] Optionally, the reference airfoil model covered with topcoat is a model obtained after covering the surface of the reference airfoil model with topcoat according to reference process parameters, the reference process parameters are the process parameters used when processing the topcoat of the blade to be tested, and the blade to be tested 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, the process-roughness comparison 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 topcoat.

[0112] Optionally, a detachable protective film is provided between the reference airfoil model and the topcoat, and an error of the surface roughness of the detachable protective film relative to the surface roughness of the reference airfoil model is less than an error threshold.

[0113] Optionally, according to the different roughness of the blade surface, the blade surface working conditions include clean working conditions and rough working conditions, the clean working condition corresponds to a polished surface not covered with topcoat, and the rough working condition corresponds to a surface that makes the airfoil flow reach a fully turbulent state, and the original aerodynamic characteristic data includes clean aerodynamic characteristic data under the clean working condition; the correction parameter includes at least one of a fusion ratio and a correction amount, wherein the original aerodynamic characteristic data also includes rough aerodynamic characteristic data under the rough working 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.

[0114] The third aspect of the present disclosure provides a device for determining blade aerodynamic performance data. FIG12 is a block diagram illustrating a device for determining blade aerodynamic performance data according to an embodiment of the present disclosure. Referring to FIG12 , the device 1200 for determining blade aerodynamic performance data includes an acquisition unit 1201 and a determination unit 1202.

[0115] The acquisition unit 1201 may acquire the basic airfoil used in the design phase of the target blade and the modified aerodynamic characteristic data of the basic airfoil.

[0116] The determination unit 1202 may determine the aerodynamic performance data of the target blade according to the corrected aerodynamic characteristic data of the basic airfoil.

[0117] The corrected aerodynamic characteristic data of the basic airfoil are obtained by the method for correcting the aerodynamic characteristic data of the airfoil provided in any embodiment of the first aspect of the present disclosure.

[0118] Regarding the apparatus in the above embodiment, the specific manner in which each unit performs operations has been described in detail in the embodiment of the method, and will not be elaborated on here.

[0119] According to the embodiment of the present disclosure, the method for correcting the aerodynamic characteristic data of the airfoil or the method for determining the aerodynamic performance data of the blade 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 the processor, the method for correcting the aerodynamic characteristic data of the airfoil or the method for determining the aerodynamic performance data of the blade 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 disk storage, hard disk drive (HDD), solid state drive (SSD), card storage (such as, multimedia card, secure digital (SD) card or ultra fast 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, any other device configured to store the 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 so 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 so 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.

[0120] FIG13 is a block diagram illustrating a computer device according to an embodiment of the present disclosure.

[0121] 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 computer-executable instruction set 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.

[0122] As an example, the computer device 1300 can be a PC, a tablet device, a personal digital assistant, a smart phone, or other device capable of executing the above-mentioned instruction set. Here, the computer device 1300 is not necessarily a single electronic device, but can also be any device or circuit that can execute the above-mentioned instructions (or instruction sets) individually or in combination. The computer device 1300 can also be part of an integrated control system or system manager, or can be configured as a portable electronic device that is interconnected with a local or remote (e.g., via wireless transmission) interface.

[0123] In computer device 1300, 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.

[0124] The processor 1302 may execute instructions or codes stored in the memory 1301, which may also store data. Instructions and data may also be sent and received over a network via a network interface device, which may employ any known transmission protocol.

[0125] The memory 1301 may be integrated with the processor 1302, for example, by placing RAM or flash memory within an integrated circuit microprocessor or the like. Furthermore, the memory 1301 may comprise a separate device, such as an external disk drive, a storage array, or any other storage device usable by a 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, or the like, such that the processor 1302 can access files stored in the memory.

[0126] 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.

[0127] The present disclosure proposes a method and device for correcting aerodynamic characteristic data of an airfoil, a method and device for determining aerodynamic performance data of a blade, a computer-readable storage medium, and a computer device. By conducting an aerodynamic characteristic experiment on a reference blade covered with topcoat, the topcoat aerodynamic characteristic data of the corresponding reference airfoil after considering the influence of the topcoat can be obtained, thereby combining the original aerodynamic characteristic data and the topcoat aerodynamic characteristic data to determine the correction parameters, 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, a small number of experiments (i.e., experiments on the reference airfoil) can be used to infer the aerodynamic characteristic data of other airfoils (i.e., the target airfoil) after being covered with topcoat, as the corrected aerodynamic characteristic data, so that the aerodynamic characteristic data of the airfoil after correction is more consistent with the actual operating conditions, which helps to clarify the influence of the topcoat on the aerodynamic performance of the blade, improve the understanding of the operating status of the blade and the unit, and improve the consistency of the simulation and test of the blade and the whole machine.

[0128] The specific implementation methods 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 may be modified and varied without departing from the principles and spirit of the present disclosure, the scope of which is defined by the claims and their equivalents. These modifications and variations should also be within the scope of protection 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 a 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, wherein 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, wherein 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 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 roughness, 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 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 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 blade aerodynamic performance data, 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. Wherein, 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 with 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. An apparatus 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 as described in any one of claims 1 to 8 or the method for determining blade aerodynamic performance data as described in 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 as described in any one of claims 1 to 8 or the method for determining blade aerodynamic performance data as described in claim 9.

Images