阅读说明：本技术 一种基于仿生凹凸前缘结构的流动分离控制方法 (Flow separation control method based on bionic concave-convex front edge structure ) 是由 张一楠 张明明 廖猜猜 秦志文 于 2021-08-09 设计创作，主要内容包括：本发明提供了一种基于仿生凹凸前缘结构的流动分离控制方法,所述方法用于控制风电叶片叶展中部及叶根区域流动分离,所述方法包括如下步骤：S1：测试仿生凹凸前缘风力机翼型的气动性能；S2：进行气动性能优化设计,得到凹凸前缘结构尺寸；S3：结合风电叶片设计平台,设计风电叶片并完成校验；S4：根据S2获得的凹凸前缘结构尺寸,制作凹凸前缘结构,将所述凹凸前缘结构安装在S3获得的风电叶片上。本发明所提供的基于仿生凹凸前缘结构的流动分离控制方法,通过将风电叶片大厚度叶展位置处的前缘设计成凹凸结构,并通过粘接的方式实现前缘凸起结构与风电叶片前缘表面的连接,通过这种方法实现了对流动分离的有效抑制。(The invention provides a flow separation control method based on a bionic concave-convex leading edge structure, which is used for controlling flow separation of the middle part of a blade span and a blade root area of a wind power blade and comprises the following steps: s1: testing the aerodynamic performance of the bionic concave-convex leading edge wind turbine airfoil; s2: carrying out pneumatic performance optimization design to obtain the size of the concave-convex front edge structure; s3: designing a wind power blade and completing verification by combining a wind power blade design platform; s4: and manufacturing a concave-convex front edge structure according to the size of the concave-convex front edge structure obtained in the step S2, and mounting the concave-convex front edge structure on the wind power blade obtained in the step S3. According to the flow separation control method based on the bionic concave-convex front edge structure, the front edge at the large-thickness blade span position of the wind power blade is designed into the concave-convex structure, the connection between the front edge convex structure and the front edge surface of the wind power blade is realized in a bonding mode, and the effective inhibition on flow separation is realized through the method.)

1. A flow separation control method based on a bionic concave-convex leading edge structure is used for controlling flow separation of a blade span middle part and a blade root area of a wind power blade and is characterized by comprising the following steps:

s1: testing the aerodynamic performance of the bionic concave-convex leading edge wind turbine airfoil;

s2: optimizing the aerodynamic performance by predicting the aerodynamic performance of the wind turbine airfoil to obtain the structural size of the concave-convex front edge;

s3: designing a wind power blade and completing verification by combining a wind power blade design platform;

s4: and manufacturing a concave-convex front edge structure according to the size of the concave-convex front edge structure obtained in the step S2, and mounting the concave-convex front edge structure on the wind power blade obtained in the step S3.

2. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 1, wherein the bionic concave-convex leading edge structure is a periodically distributed convex leading edge structure with sine regular change.

3. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 1, wherein the step S1 comprises the following steps:

s1.1: extracting an original wind turbine airfoil profile aiming at the middle part of a blade span of a wind power blade and the blade section of a blade root region, and performing modification design on the original wind turbine airfoil profile;

s1.2: and modifying the wing profile leading edge into a large-thickness bionic wind turbine wing profile with a concave-convex leading edge structure to obtain the aerodynamic performance of the bionic wind turbine wing profile.

4. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 3, wherein the relative thickness of the wind turbine airfoil is not less than 40%.

5. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 1, wherein the concave-convex leading edge structure size comprises an amplitude and a wavelength, the amplitude is the height of the convex leading edge, and the wavelength is the width of the convex leading edge.

6. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 5, wherein the S2 comprises:

s2.1: simplifying each concave-convex front edge structure into a small-sized delta wing model, wherein the height and the spread length of the delta wing model correspond to the A and the wavelength lambda of the concave-convex front edge;

s2.2: deducing lift force and resistance force generated by each concave-convex front edge by utilizing a delta wing theory;

s2.3: calculating the total lift coefficient and the total resistance coefficient generated by the concave-convex front edge structure according to the lift force and the resistance generated by each concave-convex front edge obtained in the step S2.2;

s2.4: determining a stall attack angle according to an original airfoil aerodynamic force change rule, obtaining a calculation formula of the overall lift coefficient and the drag coefficient before and after stall, and optimizing aerodynamic performance according to the calculation formula to obtain the structural size of the concave-convex leading edge.

7. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 6, wherein the overall lift force F generated by each convex structure of the concave-convex leading edge structure_LWith integral resistance F_DThe following formula:

wind turbine airfoil with n-convex leading edges and concave-convex leading edge structure for generating total lift coefficient C'_LAnd total drag coefficient C'_DComprises the following steps:

wherein α is the inflow angle of attack; c is the chord length of the wing profile, s is the span length of the wing profile, and t is the relative thickness of the wing profile; u is the free incoming flow velocity, and rho is the air density; k_PAnd K_VCorrecting coefficients for the delta wing model; introducing an influence correction coefficient delta of a concave-convex front edge structure on a flow field based on different flow states;

determining a stall attack angle alpha according to an original airfoil aerodynamic force change rule_satllThe overall lift coefficient C generated by the concave-convex leading edge wind turbine airfoil before and after stall_LAnd resistance C_DThe calculation formula of (2) is as follows:

wherein prestall refers to before stall, poststall refers to after stall, CL, Baseline and CD, and Baseline respectively refers to lift force and resistance force of the original airfoil profile.

8. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 1, wherein the S3 comprises: and combining a wind power blade design platform, taking the bionic leading edge airfoil profile obtained by design as a basic airfoil profile, carrying out pneumatic and structural design on the wind power blade, and finishing checking to obtain the wind power blade.

9. The flow separation control method based on the bionic concave-convex leading edge structure as claimed in claim 1, wherein the curvature of the concave-convex leading edge structure edge is the same as that of the blade surface installation region.

10. The flow separation control method based on the bionic concave-convex leading edge structure according to claim 9, wherein the step S4 comprises the following steps:

s4.1: manufacturing a concave-convex front edge structure;

s4.2: marking a bonding area on the surface of the wind power blade obtained in the step S3;

s4.3: cleaning and surface treating the bonding area, and gluing;

s4.4: bonding the concave-convex front edge structure obtained in the step S4.1 to the bonding area after gluing;

s4.5: and removing redundant colloid at the connecting edge seam of the concave-convex front edge structure and the wind power blade, and sealing by using sealant.

Technical Field

The invention belongs to the technical field of engineering application, and particularly relates to a flow separation control method based on a bionic concave-convex front edge structure.

Background

In recent years, the advantages of wind power generation are more and more accepted, and especially, the development of offshore wind power and the enlargement of a wind turbine generator set become main development trends. The single machine capacity of the large-scale wind turbine generator is larger, the unit cost is relatively lower, and the large-scale wind turbine generator can better adapt to the resource condition of wind resource centralized distribution. The length of the wind power blade is continuously increased due to the large-scale wind turbine generator, the structural strength requirement of the blade is more outstanding, and the blade still has better aerodynamic performance on the premise of ensuring the structural strength and is a main obstacle in the blade design process.

The wind turbine airfoil is a basic element forming a wind turbine blade, and the aerodynamic performance and the flow characteristic of the wind turbine airfoil directly influence the efficient and stable operation of a wind turbine. According to the requirements of different blade span positions of the wind power blade, the wind turbine airfoil profile balances aerodynamic performance and structural performance in the design process. For the wing profile of the wind power blade close to the blade tip side area, the aerodynamic performance is more important than the structural performance, and a thin wing profile with a high lift-drag ratio is mostly adopted, so that good aerodynamic performance is obtained, and the wind energy utilization efficiency of the blade is improved. The wing profiles in the middle area of the span of the wind power blade and the area close to the root side of the wind power blade have higher requirements on structural strength, the wing profiles with larger thickness are adopted to effectively improve the structural performance of the blade, and the relative thickness of the wing profiles is generally more than 30%. The definition of high thickness is evolving and airfoils with relative thicknesses above 40% may be referred to as "high thickness" windmill airfoils. The problem of contradiction between blade aerodynamics and structure caused by large-scale wind turbine generator can be relieved by adopting a method of a large-thickness airfoil shape near the root of a wind turbine blade. With the development of large-scale wind turbine generator, the wing profile near the blade root of the wind turbine blade contributes more and more to the generated energy, which further promotes the development of the wind turbine wing profile with large thickness.

However, as shown in fig. 7, the inflow attack angle of the thick airfoil of the wind turbine blade in the midspan region and the region near the root side tends to be large, and the flow separation occurs earlier on the surface of the blade due to the large curvature of the upper surface and the large negative pressure gradient at the trailing edge of the airfoil, which causes the midspan region and the root side region to generate low lift and high resistance, resulting in the aerodynamic performance of the blade being reduced, thereby reducing the power generation efficiency of the wind turbine. Therefore, for the wind power blade with large thickness in the middle area of the blade span and the area close to the root side of the blade, the wind power blade with large lifting force value and good stall characteristic can help to maintain high aerodynamic performance, and can prevent the problems of structural damage and the like of the blade. At present, no effective control method is provided for the serious flow separation problem in the middle blade span region and the region close to the blade root side of the wind power blade, most flow separation control methods are not widely applied in engineering, the tail edge of the airfoil is passivated by adopting a symmetrical thickening method mostly based on the experimental research stage of the wind power blade airfoil, and research and analysis show that the blunt tail edge method has an obvious improvement effect on the aerodynamic performance and stall characteristic of the large-thickness airfoil. In addition, the pneumatic accessories added on the surface of the blade can also play a role in improving the aerodynamic performance of the blade, such as a vortex generator, a tail edge flap, a spoiler and other passive control methods.

The prior art flow separation control techniques mainly include active control and passive control. The active control method is characterized in that external energy is introduced into fluid on the surface of the blade to keep the fluid from being separated, and common active control methods comprise methods such as circulation control, synthetic jet flow, blowing and sucking gas flow control and plasma disturbance. In addition, due to the severe and changeable operating environment of the wind power blades, the cost of later-stage operation and maintenance is increased to a great extent by the device system with a complicated active control method; secondly, the active control method needs external energy supply, so that extra energy loss is caused, and the overall economic benefit of the control method can be reduced by realizing flow control through a large amount of external energy supply based on the purpose of improving the power generation efficiency of the large-scale wind power blade; finally, the working environment of the large-scale wind turbine blade is complex and changeable, the incoming wind speed and the incoming wind direction of the wind turbine generator change constantly, and the response speed of the active control method to the wind condition and the transmission precision of the system signal are difficult to meet the working requirement of the wind turbine blade.

The passive control method promotes the boundary layer to keep adhering flow by changing the external shape and structure of the blade or adding aerodynamic accessories on the surface of the blade, so as to realize flow separation inhibition. Compared with an active control method, the passive control method has the advantages of low production cost, no complex control system and signal transmission device, low cost and good economical efficiency. And for the wind power blade, the simple structure of the passive control method enables the installation and the disassembly to be more convenient, and the later maintenance is not needed. However, most of the installation positions and design areas of the currently researched passive control method are located near the trailing edge of the blade airfoil, and a large torsion angle exists at the extending position of the wind power blade, so that in order to ensure the power generation efficiency, the inflow attack angles of the middle area of the blade span and the blade root area are large in the actual operation process, a serious flow separation phenomenon is generated, and a separation area with a large area is formed. Therefore, compared with the flow control method of the front edge of the blade, the flow control method near the tail edge of the blade has poor effect, and the flow separation can be controlled to the maximum extent only by effectively controlling the flow separation in the middle area of the span of the wind power blade and the area of the blade root on the front edge of the blade.

Therefore, a flow separation control method based on a bionic concave-convex front edge structure is needed to be provided for controlling the flow separation of the wind power blade, so that the serious flow separation phenomenon existing in the middle span region and the blade root region of the wind power blade is solved.

Disclosure of Invention

In order to solve the problems, the invention provides a flow separation control method for the middle of the blade span and the blade root region of a wind power blade based on a bionic concave-convex front edge method.

The invention aims to provide a flow separation control method based on a bionic concave-convex leading edge structure, which is used for controlling flow separation of the middle part of a blade span and the root region of a wind power blade, and comprises the following steps:

s1: testing the aerodynamic performance of the bionic concave-convex leading edge wind turbine airfoil;

s2: the aerodynamic performance of the wind turbine airfoil is predicted to optimize the aerodynamic performance to obtain the structural size of the concave-convex front edge;

s3: designing a wind power blade and completing verification by combining a wind power blade design platform;

s4: and manufacturing a concave-convex front edge structure according to the size of the concave-convex front edge structure obtained in the step S2, and mounting the concave-convex front edge structure on the wind power blade obtained in the step S3.

The flow separation control method based on the bionic concave-convex front edge structure also has the characteristic that the bionic concave-convex front edge structure is a convex front edge structure which is periodically distributed and changes in a sine rule.

The flow separation control method based on the bionic concave-convex front edge structure provided by the invention is also characterized in that the S1 comprises the following steps:

s1.1: extracting an original wind turbine airfoil profile aiming at the middle part of a blade span of a wind power blade and the blade section of a blade root region, and performing modification design on the original wind turbine airfoil profile;

s1.2: and modifying the wing profile leading edge into a large-thickness bionic wind turbine wing profile with a concave-convex leading edge structure to obtain the aerodynamic performance of the bionic wind turbine wing profile.

The flow separation control method based on the bionic concave-convex leading edge structure is further characterized in that the relative thickness of the wind turbine wing profile is not less than 40%.

The flow separation control method based on the bionic concave-convex front edge structure further has the characteristics that the size of the concave-convex front edge structure comprises amplitude and wavelength, the amplitude is the height of the convex front edge, and the wavelength is the width of the convex front edge.

The flow separation control method based on the bionic concave-convex front edge structure provided by the invention is also characterized in that the S2 comprises the following steps:

s2.1: simplifying each concave-convex front edge structure into a small-sized delta wing model, wherein the height and the spread length of the delta wing model correspond to the A and the wavelength lambda of the concave-convex front edge;

s2.2: deducing lift force and resistance force generated by each concave-convex front edge by utilizing a delta wing theory;

s2.3: calculating the total lift coefficient and the total resistance coefficient generated by the concave-convex front edge structure according to the lift force and the resistance generated by each concave-convex front edge obtained in the step S2.2;

s2.4: determining a stall attack angle according to an original airfoil aerodynamic force change rule, obtaining a calculation formula of the overall lift coefficient and the drag coefficient before and after stall, and optimizing aerodynamic performance according to the calculation formula to obtain the structural size of the concave-convex leading edge.

The flow separation control method based on the bionic concave-convex leading edge structure also has the characteristic that the overall lift force F generated by each convex structure of the concave-convex leading edge structure_LWith integral resistance F_DThe following formula:

wind turbine airfoil with n-convex leading edges and concave-convex leading edge structure for generating total lift coefficient C'_LAnd total drag coefficient C'_DComprises the following steps:

wherein α is the inflow angle of attack; c is the chord length of the wing profile, s is the span length of the wing profile, and t is the relative thickness of the wing profile; u is the free incoming flow velocity, and rho is the air density; k_PAnd K_VCorrecting coefficients for the delta wing model; introducing an influence correction coefficient delta of a concave-convex front edge structure on a flow field based on different flow states;

determining a stall attack angle alpha according to an original airfoil aerodynamic force change rule_satllThe overall lift coefficient C generated by the concave-convex leading edge wind turbine airfoil before (prestall) and after (poststall)_LAnd resistance C_DThe calculation formula of (2) is as follows:

wherein prestall refers to before stall, poststall refers to after stall, CL, Baseline and CD, and Baseline respectively refers to lift force and resistance force of the original airfoil profile.

The flow separation control method based on the bionic concave-convex front edge structure provided by the invention is also characterized in that the S3 comprises the following steps: and combining a wind power blade design platform, taking the bionic leading edge airfoil profile obtained by design as a basic airfoil profile, carrying out pneumatic and structural design on the wind power blade, and finishing checking to obtain the wind power blade.

The flow separation control method based on the bionic concave-convex front edge structure also has the characteristic that the curvature of the edge of the concave-convex front edge structure is the same as that of the blade surface mounting area.

The flow separation control method based on the bionic concave-convex front edge structure provided by the invention is also characterized in that the S4 comprises the following steps:

s4.1: manufacturing a concave-convex front edge structure;

s4.2: marking a bonding area on the surface of the wind power blade obtained in the step S3;

s4.3: cleaning and surface treating the bonding area, and gluing;

s4.4: bonding the concave-convex front edge structure obtained in the step S4.1 to the bonding area after gluing;

s4.5: and removing redundant colloid at the connecting edge seam of the concave-convex front edge structure and the wind power blade, and sealing.

The flow separation control method based on the bionic concave-convex front edge structure further has the characteristic that the sealing treatment in the S4.5 is sealing through a sealant.

Has the advantages that:

according to the flow separation control method based on the bionic concave-convex front edge structure, the front edge at the large-thickness blade span position of the wind power blade is designed into the concave-convex structure, the connection between the front edge convex structure and the front edge surface of the wind power blade is realized in a bonding mode, and the effective inhibition on flow separation is realized through the method.

According to the flow separation control method based on the bionic concave-convex front edge structure, the concave-convex front edge structure can be quickly installed on the front edge surface of the wind power blade by the concave-convex front edge structure installation method, and the surface of the original wind power blade is not damaged.

The invention provides a flow separation control method based on a bionic concave-convex leading edge structure, and provides a calculation method of concave-convex leading edge airfoil aerodynamic performance, which can be used for rapidly predicting concave-convex leading edge airfoil aerodynamic force with different structural parameters.

Drawings

In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic view of a bionic concave-convex leading edge wind power blade involved in the control method provided by the invention;

FIG. 2 is a schematic view of a high thickness concave-convex leading edge airfoil involved in the control method provided by the present invention;

FIG. 3 is a schematic illustration of the bonding of a concave-convex leading edge structure blade involved in the control method provided by the present invention;

FIG. 4 is a graph showing the result of the airfoil lift of the wind turbine with a large thickness and a bionic concave-convex front edge according to the control method provided by the present invention;

FIG. 5 is a graph showing the result of a flow separation test of a large-thickness airfoil of a wind turbine with a bionic leading edge according to the control method provided by the present invention;

FIG. 6 is a schematic diagram of aerodynamic stall in the control method provided by the present invention;

fig. 7 is a structure diagram of a wind turbine blade in the prior art.

Detailed Description

In order to make the technical means, the creation features, the achievement objects and the effects of the present invention easy to understand, the following embodiments specifically describe the flow separation control method based on the bionic concave-convex front edge structure provided by the present invention with reference to the accompanying drawings.

In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.

The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.

The invention provides a flow separation control method based on a bionic concave-convex front edge structure, which is used for controlling flow separation of the middle blade span and the blade root region of a wind power blade.

The method comprises the following steps:

s1: testing the aerodynamic performance of the bionic concave-convex leading edge wind turbine airfoil, wherein the bionic concave-convex leading edge structure is a convex leading edge structure which is periodically distributed and changes according to a sine rule:

s1.1: extracting an original wind turbine airfoil profile aiming at the middle part of a blade span of a wind power blade and the blade section of a blade root region, and performing modification design on the original wind turbine airfoil profile;

s1.2: modifying the front edge of the wing profile into a large-thickness bionic wind turbine wing profile with a concave-convex front edge structure, and acquiring aerodynamic performance of the bionic wind turbine wing profile through experimental tests or numerical calculation;

wherein, the bionic refers to a bulge imitating the front edge of a whale fin, and the shape of the bionic front edge is a bulge structure with a curved surface transition and smooth connection with the surface of a blade. And (3) combining an airfoil design program (Xfoil and Rfoil) and an airfoil aerodynamic and noise calculation formula, performing aerodynamic and noise performance calculation evaluation on the airfoils with the convex leading edges with different size parameters, and performing multiple optimization and optimization on the size parameters of the convex leading edges according to evaluation results by using an optimization design platform (Isight), so as to finally determine the convex leading edge size parameters with optimal aerodynamic performance and noise level.

S2: the aerodynamic performance of the wind turbine airfoil is optimized by predicting the aerodynamic performance of the wind turbine airfoil, and the structure size of the concave-convex front edge is obtained, wherein the structure size of the concave-convex front edge comprises an amplitude A and a wavelength lambda, the amplitude A is the height of the convex front edge, and the wavelength lambda is the width of the convex front edge:

s2.1: simplifying each concave-convex front edge structure into a small-sized delta wing model, wherein the height and the spread length of the delta wing model correspond to the A and the wavelength lambda of the concave-convex front edge;

s2.2: the lift force and the resistance force generated by each concave-convex front edge are deduced by utilizing the delta wing theory, and the overall lift force F generated by each convex structure of the concave-convex front edge structure_LWith integral resistance F_DThe following formula:

s2.3: calculating the total lift coefficient and the total drag coefficient generated by the concave-convex leading edge structure according to the lift force and the drag force generated by each concave-convex leading edge obtained in the step S2.2, wherein any leading edge is provided with n convex wind turbine airfoils, and the total lift coefficient C 'generated by the concave-convex leading edge structure'_LAnd total drag coefficient C'_DComprises the following steps:

wherein α is the inflow angle of attack; c is the chord length of the wing profile, s is the span length of the wing profile, and t is the relative thickness of the wing profile; u is the free incoming flow velocity, and rho is the air density; according to the delta wing theory, the overall lift force received by the delta wing is composed of a potential flow lift force and a vortex lift force, and the resistance received by the delta wing is mainly generated by the component of the potential flow lift force. Wherein the potential flow lift L_P＝K_Psinαcos²Alpha and KP are corrected pressure values of a lifting surface theory; vortex lift L_V＝K_Vcosαsin²And alpha, calculating a series of delta wing models by utilizing a lifting surface theory to obtain a KV value. (ii) a Introducing influence correction coefficient delta of the concave-convex front edge structure on the flow field based on different flow states, wherein the correction coefficient delta is obtained by comparing aerodynamic force test experimental data of concave-convex front edge airfoils with different structural parameters through fitting

S2.4: determining a stall attack angle according to an original airfoil aerodynamic change rule, obtaining a calculation formula of an overall lift coefficient and a drag coefficient before and after stall, and determining a stall attack angle alpha according to the original airfoil aerodynamic change rule_satllThe overall lift coefficient C generated by the concave-convex leading edge wind turbine airfoil before (prestall) and after (poststall)_LAnd resistance C_DThe calculation formula of (2) is as follows:

wherein prestall refers to before stall, poststall refers to after stall, CL, Baseline and CD, and Baseline respectively refers to lift force and resistance force of the original airfoil profile.

And optimizing the aerodynamic performance according to the calculation formula to obtain the size of the concave-convex front edge structure.

In the above embodiments, the overall lift and drag generated by the concave-convex leading edge airfoil can be regarded as the superimposed effect of the lift and drag generated by the original smooth leading edge airfoil and the lift and drag generated by the concave-convex leading edge structure. Before aerodynamic stall (as shown in fig. 6, aerodynamic stall refers to a phenomenon in which the lift of the airfoil is significantly increased and the drag is significantly decreased, and generally, the angle of attack at which the stall occurs is a stall angle of attack), the concave-convex airfoil structure causes the decrease in lift and the increase in drag of the airfoil; and after stall, the concave-convex leading edge structure improves lift and reduces drag. Therefore, the stall angle of attack α is determined from the original airfoil aerodynamic variations_satllConcave-convex leading edge approach at stall angle of attack alpha_satllThe front and back have opposite effects on the aerodynamic performance of the airfoil. Before aerodynamic stall, the original airfoil profile can obtain the lift force and the resistance of the concave-convex leading edge airfoil profile by subtracting the lift force generated by the concave-convex leading edge structure and increasing the resistance generated by the concave-convex leading edge structure; after stall, the calculation method is reversed. By the method for calculating the aerodynamic performance of the airfoil with the concave-convex front edge, the aerodynamic force of the airfoil with the concave-convex front edge with different structural parameters (amplitude A and wavelength lambda) can be quickly predicted, on the basis, the optimal design platform of the airfoil of the wind turbine is combined to improve the aerodynamic performance of the airfoil of the large-thickness bionic wind turbine as an optimal target, the size parameter of the structure of the concave-convex front edge is optimally designed, the size parameter of the structure of the concave-convex front edge when the aerodynamic performance is optimal is obtained, and the height (amplitude A) and the width (wavelength lambda) of the concave-convex front edge with the optimal aerodynamic performance of the airfoil of the large-thickness bionic wind turbine are determined.

S3: combining a wind power blade design platform, taking the bionic leading edge airfoil profile obtained by design as a basic airfoil profile, carrying out pneumatic and structural design on the wind power blade, and finishing checking to obtain the wind power blade

S4: manufacturing a concave-convex front edge structure according to the size of the concave-convex front edge structure obtained in the step S2, and installing the concave-convex front edge structure on the wind power blade obtained in the step S3, as shown in fig. 3:

s4.1: manufacturing a concave-convex front edge structure, wherein the curvature of the edge of the concave-convex front edge structure is the same as that of the surface mounting area of the blade; the same curvature can realize that the concave-convex front edge structure is tightly attached to the surfaces of the suction side and the pressure side of the blade;

s4.2: marking a bonding area on the surface of the wind power blade obtained in the step S3;

s4.3: cleaning and surface treating the bonding area, wherein the surface treatment is to make the surface meet the bonding requirement and uniformly glue the bonding area;

s4.4: bonding the concave-convex front edge structure obtained in the step S4.1 to the bonding area after gluing, and forcibly extruding and fixing to ensure that no bubbles exist in the bonding surface and firm bonding is realized;

s4.5: and removing redundant colloid at the connecting edge seam of the concave-convex front edge structure and the wind power blade, and sealing by using sealant.

In some embodiments, the relative thickness of the wind turbine airfoil is not less than 40%.

In order to verify the flow separation control method based on the bionic concave-convex leading edge structure provided by the embodiment, the flow separation control method can be used for controlling the flow separation of the middle part of the span of the wind power blade and the root region of the wind power blade, extracting the large-thickness special airfoil profile (DU00-W2-401) of the wind turbine with the relative thickness of 40% near the root region of the wind power blade to perform an aerodynamic force and flow field test experiment, and verifying the inhibition effect of the concave-convex leading edge method on the flow separation.

The lift force of the wind power blade root section is a key factor influencing the overall aerodynamic performance of the blade, and the improvement of the lift force characteristic of the large-thickness airfoil section of the root section is very important for improving the power generation efficiency and the operation stability of the wind power blade. The inflow attack angle at the position of the blade root is large, and therefore, the lift characteristic result of the large-thickness airfoil in the high attack angle area (alpha is 10-30 degrees) shown in the figure 4 is obtained through an aerodynamic force test experiment. Compared with the original large-thickness wind turbine airfoil, the bionic concave-convex front edge method can effectively improve the lift force of the large-thickness wind turbine airfoil. In addition, a surface flow field result of the large-thickness wind turbine airfoil is obtained through a PIV flow field test experiment, as shown in fig. 5, the flow separation of the large-thickness wind turbine airfoil with the bionic concave-convex front edge is more delayed, a separation area formed in an airfoil tail edge area is relatively small, and the flow separation is effectively inhibited.

In summary, the invention provides a flow separation control technology based on a bionic concave-convex leading edge structure, and can effectively improve the lift force generated by the large-thickness wind turbine airfoil in the middle area of the blade span and the blade root area of the wind turbine blade. The wind power blade with the bionic concave-convex front edge is obtained through a wind turbine airfoil design program and a blade optimization design platform, and has the function of improving aerodynamic characteristics and stability. On the basis, the invention provides an installation method adopted in the flow separation control technology based on the bionic concave-convex front edge structure, which can realize the quick installation of the concave-convex front edge structure on the front edge surface of the wind power blade and does not generate any damage to the surface of the original wind power blade.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.