Wind turbine generator blade and wind turbine generator

Abstract

The invention provides a wind turbine generator blade and a wind turbine generator, and relates to the technical field of wind turbine generators. A part, in the spanwise direction, of the wind turbine generator blade forms an adjusting section, the maximum thickness of the cross section of the adjusting section is a first parameter, the chord length of the cross section is a second parameter, the ratio of the first parameter to the second parameter is a third parameter, the third parameter is larger than or equal to 0.4, and the third parameter is smaller than or equal to 0.9; the thickness of the opening of the rear edge of the cross section is a fourth parameter, the ratio of the fourth parameter to the second parameter is a fifth parameter, and the fifth parameter is larger than 5.66% and smaller than 24.44%. According to the wind turbine generator blade and the wind turbine generator, the forming quality and the overall rigidity of the blade are improved.

Description

Technical Field

[0001] This application relates to the field of wind turbine technology, and in particular to a wind turbine blade and a wind turbine. Background Technology

[0002] Against the backdrop of continuously growing global demand for renewable energy, wind power has been widely developed and applied due to its clean and sustainable characteristics. The continued development of megawatt-class wind turbines has led to an increase in the length of wind turbine blades, which places more stringent demands on the structural stiffness and stability of the blades. In the currently widely adopted double-web and triple-web structures, the webs and main beams are usually located in the high-curvature regions of the leading and trailing edges of the blade. This structural trend presents greater challenges to the overall structural stability and manufacturing process of the blade. Especially in the region near the blade root (closer to the cylindrical shape), due to the large curvature, problems such as main beam slippage and ply wrinkling are prone to occur, thus affecting the blade's forming quality and overall stiffness performance. Summary of the Invention

[0003] To address at least one of the problems mentioned in the background art, this application provides a wind turbine blade and a wind turbine assembly, which improves the blade's forming quality and overall stiffness.

[0004] To achieve the above objectives, this application provides the following technical solution:

[0005] In a first aspect, this application provides a wind turbine blade, wherein a portion of the blade along the spanwise direction forms an adjustment section, the maximum thickness of the cross-section of the adjustment section is a first parameter, the chord length of the cross-section is a second parameter, the ratio of the first parameter to the second parameter is a third parameter, the third parameter is greater than or equal to 0.4, and the third parameter is less than or equal to 0.9.

[0006] The thickness at the trailing edge opening of the cross-section is the fourth parameter, and the ratio of the fourth parameter to the second parameter is the fifth parameter. The fifth parameter is greater than 5.66% and less than 24.44%.

[0007] As an optional implementation, the third parameter is greater than or equal to 0.5 and less than or equal to 0.8.

[0008] As an optional implementation, the radius of curvature of the leading edge of the cross section is a sixth parameter, which is greater than 0.11 meters and less than 0.47 meters.

[0009] As an optional implementation, the ratio of the length of the adjustment section to the length of the blade is 0.2-0.4.

[0010] As an optional implementation, the distance between the adjustment section and the leaf root is the seventh parameter, and the ratio of the seventh parameter to the leaf length is 0.05-0.1.

[0011] As an optional implementation, the cross section includes a first cross section located at one end of the adjustment section near the blade tip, and the thickness of the trailing edge opening of the first cross section is 0.25 m to 0.28 m.

[0012] As an optional implementation, the cross section also includes a second cross section located at one end of the adjustment section near the blade root, and the thickness of the trailing edge opening of the second cross section is 0.78 m to 1.17 m.

[0013] As an optional implementation, the third and fifth parameters satisfy the following relationship:

[0014] y1 = -92.926x 2 +158.35x-42.81

[0015] Where y1 is the fifth parameter and x is the third parameter.

[0016] As an optional implementation, the third and sixth parameters satisfy the following relationship:

[0017] y2 = -0.6x 2 +1.4782x - 0.3777

[0018] Where y2 is the sixth parameter and x is the third parameter.

[0019] Secondly, this application also provides a wind turbine unit, including the wind turbine blades described in the first aspect.

[0020] The wind turbine blade provided in this application forms an adjustment section along a portion of its spanwise direction. The maximum thickness of the cross-section of the adjustment section is the first parameter, the chord length of the cross-section is the second parameter, the ratio of the first parameter to the second parameter is the third parameter, the third parameter is greater than or equal to 0.4, and the third parameter is less than or equal to 0.9; the thickness at the trailing edge opening of the cross-section is the fourth parameter, the ratio of the fourth parameter to the second parameter is the fifth parameter, and the fifth parameter is greater than 5.66% and less than 24.44%.

[0021] The wind turbine blade provided in this application addresses the technical problems of main beam slippage and ply wrinkling in the high curvature region of existing double-web and triple-web structures. By incorporating adjustment sections along the blade's span and precisely designing its cross-sectional parameters, the third parameter (maximum thickness to chord length ratio) is maintained between 0.4 and 0.9, and the fifth parameter (trailing edge opening thickness to chord length ratio) is maintained between 5.66% and 24.44%. This not only increases the trailing edge opening angle, delays trailing edge flow separation, and improves aerodynamic stability in this region, but also improves the overlap shape of the main beam and web, effectively mitigating structural slippage and ply wrinkling caused by abrupt curvature changes, thereby enhancing the blade's forming quality and overall stiffness. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 A schematic diagram of a wind turbine blade provided in an embodiment of this application;

[0024] Figure 2 A schematic cross-sectional view of the adjustment section in a wind turbine blade provided in an embodiment of this application;

[0025] Figure 3 A schematic diagram comparing the cross-section of the adjustment section in the wind turbine blade provided in this application embodiment with the cross-section of the blade in the prior art;

[0026] Figure 4 A schematic diagram illustrating the variation of the fifth parameter in the wind turbine blade with the third parameter, provided in an embodiment of this application.

[0027] Figure 5 A schematic diagram showing the variation of the sixth parameter in the wind turbine blade as a function of the third parameter, provided in an embodiment of this application.

[0028] Explanation of reference numerals in the attached figures:

[0029] 100-blade;

[0030] 110 - Adjustment Section;

[0031] 120-front edge;

[0032] 130-Later Edge

[0033] a - the fourth parameter. Detailed Implementation

[0034] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0035] In this application, the terms “upper,” “lower,” “left,” “right,” “front,” “back,” “top,” “bottom,” “inner,” “outer,” “vertical,” “horizontal,” “lateral,” and “longitudinal” indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated devices, elements, or components to having a specific orientation, or to be constructed and operated in a specific orientation.

[0036] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0037] Furthermore, the terms "installation," "setup," "equipped with," "connection," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0038] Furthermore, the terms "first," "second," etc., are primarily used to distinguish different devices, elements, or components (which may be the same or different in specific type and construction), and are not intended to indicate or imply the relative importance or quantity of the indicated devices, elements, or components. Unless otherwise stated, "a plurality of" means two or more.

[0039] Currently, in the double-web and triple-web structures widely used in large-megawatt wind turbine blades, the webs and main spars are typically located in the high-curvature regions of the leading and trailing edges of the blade. This structural trend presents greater challenges to the overall structural stability and manufacturing process of the blade. Especially in the area near the blade root, due to the large curvature, problems such as main spars slippage and ply wrinkling are prone to occur, which in turn affect the blade's forming quality and overall stiffness performance.

[0040] In view of this, this application provides a wind turbine blade, wherein a portion of the blade along its spanwise direction forms an adjustment section. The maximum thickness of the cross-section of the adjustment section is a first parameter, the chord length of the cross-section is a second parameter, and the ratio of the first and second parameters is a third parameter, wherein the third parameter is greater than or equal to 0.4 and less than or equal to 0.9. The thickness at the trailing edge opening of the cross-section is a fourth parameter, and the ratio of the fourth and second parameters is a fifth parameter, wherein the fifth parameter is greater than 5.66% and less than 24.44%. By keeping the third parameter between 0.4 and 0.9 and the fifth parameter between 5.66% and 24.44%, not only is the trailing edge opening angle increased, delaying flow separation at the trailing edge and improving aerodynamic stability in this region, but the overlap shape of the main beam and web is also improved, effectively alleviating structural slippage and layup wrinkling problems caused by abrupt curvature changes, thereby improving the blade's forming quality and overall stiffness.

[0041] Figure 1 A schematic diagram of a wind turbine blade provided in an embodiment of this application; Figure 2 A schematic cross-sectional view of the adjustment section in a wind turbine blade provided in an embodiment of this application; Figure 3 A schematic diagram comparing the cross-section of the adjustment section in the wind turbine blade provided in this embodiment with the cross-section of the blade in the prior art (the dashed line is a schematic diagram of the cross-section of the blade in the prior art); Figure 4 A schematic diagram illustrating the variation of the fifth parameter in the wind turbine blade with the third parameter, provided in an embodiment of this application. Figure 5 A schematic diagram showing the variation of the sixth parameter in the wind turbine blade as a function of the third parameter, provided in an embodiment of this application.

[0042] You can refer to this. Figures 1 to 5 This application provides a wind turbine blade 100, with a portion of the blade 100 forming an adjustment section 110 along its spanwise direction. The maximum thickness of the cross-section of the adjustment section 110 is a first parameter, the chord length of the cross-section is a second parameter, the ratio of the first parameter to the second parameter is a third parameter, the third parameter is greater than or equal to 0.4 and less than or equal to 0.9; the thickness at the opening of the trailing edge 130 of the cross-section is a fourth parameter, the ratio of the fourth parameter to the second parameter is a fifth parameter, the fifth parameter is greater than 5.66% and less than 24.44%.

[0043] The wind turbine blade 100 provided in this application addresses the technical problems of main beam slippage and ply wrinkling in the high curvature region of existing double-web and triple-web structures. By setting an adjustment section 110 along the spanwise direction of the blade 100 and precisely designing its cross-sectional parameters, the third parameter (maximum thickness to chord length ratio) is between 0.4 and 0.9, and the fifth parameter (the ratio of trailing edge 130 opening thickness to chord length) is between 5.66% and 24.44%. This not only increases the trailing edge 130 opening angle, delays flow separation at the trailing edge 130, and improves aerodynamic stability in this region, but also improves the overlap shape of the main beam and web, effectively alleviating structural slippage and ply wrinkling problems caused by abrupt curvature changes, thereby improving the forming quality and overall stiffness of the blade 100.

[0044] It is understandable that setting the third parameter between 0.4 and 0.9 corresponds to the part of blade 100 with relatively large curvature and close to the blade root. This area is prone to main beam slippage and ply layup wrinkling. Targeted design within this range takes into account the structural requirements of blade 100 in this critical part, ensuring a certain structural strength, while also mitigating the main beam slippage and ply layup wrinkling problems caused by the large curvature to a certain extent. This helps to improve the overall forming quality and structural stability of blade 100.

[0045] If the fifth parameter is less than 5.66%, the opening at the trailing edge 130 will be too small, resulting in a abrupt transition at the trailing edge 130. This abrupt transition causes the airflow to separate more quickly upon reaching the trailing edge 130. Premature airflow separation severely affects the aerodynamic performance of the blade 100, leading to unstable lift and reduced power generation efficiency. Furthermore, due to the insufficiently smooth transition at the trailing edge 130, it is difficult to achieve a tight fit between the main beam and the inner wall of the trailing edge 130 during the installation of the main beam and ply. Understandably, during actual operation, the blade 100 is subjected to various complex external forces such as wind loads and vibration loads. This loose fit makes the main beam prone to slippage and the ply prone to wrinkling. Main beam slippage will damage the overall structural support system of the blade 100, reducing its resistance to deformation; ply wrinkling will cause a localized degradation of the material properties of the blade 100, creating weak points. Over time, this may lead to structural damage to the blade 100 and even safety accidents. If the fifth parameter is greater than 24.44%, it will result in an excessively large trailing edge 130 opening and an overly gentle curve transition. An overly gentle trailing edge 130 will alter the airflow path as it passes through the trailing edge 130, significantly increasing airflow resistance. This will increase energy loss during blade 100 rotation and negatively impact the aerodynamic efficiency of blade 100, thus reducing the power generation efficiency of the wind turbine.

[0046] In the above embodiments, the third parameter can be greater than or equal to 0.5 and less than or equal to 0.8. By further limiting the third parameter to 0.5 to 0.8, the range of the adjustment segment 110 is further narrowed. This allows the design to focus on the part of the blade 100 that most needs optimization, reducing design difficulty and material input. In actual manufacturing, this simplifies the process flow, reduces costs, and allows for more precise resolution of potential problems in this area, improving the overall quality and performance of the blade 100.

[0047] In the above embodiment, the radius of curvature of the leading edge 120 of the cross section can be a sixth parameter, which is greater than 0.11 meters and less than 0.47 meters. Setting the radius of curvature of the leading edge 120 of the cross section between 0.11 meters and 0.47 meters can effectively ensure that the airflow flows smoothly and steadily along the leading edge 120 of the blade 100, thereby improving the aerodynamic performance of the blade 100. Specifically, when the airflow flows through the leading edge 120 of the blade 100, a suitable radius of curvature can guide the airflow to conform to the surface of the blade 100, avoiding premature airflow separation or airflow turbulence, which is crucial for the blade 100 to generate stable lift and reduce aerodynamic drag. Furthermore, this design allows the main beam and ply to achieve a tighter bond with the inner wall of the leading edge 120. Specifically, a suitable radius of curvature provides good spatial conditions for structural plying, allowing the main beam and ply to better conform to the shape of the inner wall of the leading edge 120. During the operation of the blade 100, this effectively reduces the possibility of slippage of the main beam and wrinkling of the ply, enhancing the stability of the blade 100 structure.

[0048] If the radius of curvature of the leading edge 120 is less than 0.11 meters, the profile transition at the leading edge 120 is too abrupt, causing a strong change in airflow as it passes through the leading edge 120. This easily generates local turbulence, leading to a significant increase in aerodynamic drag. Simultaneously, airflow separation will occur prematurely, severely impacting the lift and aerodynamic efficiency of the blade 100. Furthermore, due to the excessive curvature of the leading edge 120 and its complex inner wall shape, the main beam and ply are difficult to fit tightly against the inner wall during installation. When the blade 100 is under operating load, the main beam is prone to slippage, and the ply is prone to wrinkling, posing a challenge to the structural integrity of the blade 100. If the radius of curvature of the leading edge 120 is greater than 0.47 meters, the profile of the leading edge 120 is too gentle. After the airflow passes through the gentle leading edge 120, the adhesion path on the surface of the blade 100 will significantly increase, leading to increased energy consumption of the airflow, reduced aerodynamic efficiency of the blade 100, and ultimately affecting the wind turbine's power generation capacity. Furthermore, an excessively gentle leading edge 120 may alter the internal structural spatial layout, which to some extent hinders the effective laying of the main beam and ply, affecting the overall strength and stability of the blade 100 structure.

[0049] In the above embodiments, the ratio of the length of the adjustment section 110 to the length of the blade 100 can be 0.2-0.4. It is understood that the blade 100 needs to withstand various external forces such as wind load, self-weight, and vibration during operation, and the stress concentration area is mostly close to the blade root. The length of the adjustment section 110 at this ratio can cover the key stress area, provide sufficient structural support for the blade 100, and avoid insufficient support and easy deformation of the blade 100 due to the adjustment section 110 being too short (ratio < 0.2). It can also prevent the overall weight imbalance of the blade 100 due to the adjustment section 110 being too long (ratio > 0.4), which would increase the wind turbine drive load and energy consumption. From a performance optimization perspective, the length of the adjustment section 110 corresponding to this ratio can synergize with the third parameter (0.5-0.8) and the sixth parameter (0.11-0.47 meters) in the above embodiments. This ensures that the optimization effects of parameters such as the thickness of the blade 100 cross-section and the curvature of the leading edge 120 within the adjustment section 110 are fully realized, allowing the airflow to flow smoothly along the surface of the blade 100 and reducing resistance. Furthermore, through reasonable length coverage, the scope for addressing issues such as main beam slippage and ply wrinkling is controlled within the core area, avoiding over-design. In addition, a ratio of 0.2-0.4 can balance material usage and manufacturing difficulty, eliminating the need for excessive composite materials in excessively long optimization areas and reducing costs. Simultaneously, the concentrated optimization range facilitates control over process precision during manufacturing, reducing parameter errors caused by excessively long adjustment sections 110 and improving the forming quality and consistency of the blade 100.

[0050] In the above embodiments, the distance between the adjustment section 110 and the blade root of the blade 100 can be the seventh parameter, and the ratio of the seventh parameter to the length of the blade 100 is 0.05-0.1. It can be understood that the blade root itself is the key part connecting the blade 100 to the main shaft of the wind turbine, and it needs to withstand the greatest load impact. Moreover, its own structure is mostly a high-strength rigid design. If the distance between the adjustment section 110 and the blade root is too close (ratio < 0.05), the parameter optimization of the adjustment section 110 (such as cross-sectional thickness, leading edge 120 curvature adjustment) may interfere with the stability of the original rigid structure of the blade root, and may even cause local stress concentration due to structural superposition, increasing the risk of blade root cracking. This ratio range can reserve an appropriate buffer area for the blade root, avoid the design of the adjustment section 110 from affecting the core load-bearing structure of the blade root, and ensure the reliability of the blade root connection. Furthermore, the distance corresponding to the ratio of 0.05-0.1 allows the adjustment segment 110 to accurately cover the critical area outside the blade root, where the curvature begins to change and where main beam slippage and ply wrinkling are prone to occur. This avoids the rigid structure of the blade root itself and allows for parameter optimization of the transition area with high curvature and high load near the blade root. This ensures that the improvement effect of the adjustment segment 110 on structural defects is concentrated in the most urgent areas, avoiding the adjustment segment 110 from deviating from the high-problem area due to excessive distance (ratio > 0.1), thus reducing the optimization effect. In addition, the position of the adjustment section 110 under this ratio can also work in synergy with the length of the adjustment section 110 (ratio 0.2-0.4) and the cross-sectional parameters (third parameter 0.5-0.8, sixth parameter 0.11-0.47 meters) in the above embodiments, so that the force on the blade 100 transitions from the rigid bearing at the blade root to the structural optimization of the adjustment section 110, and then to the aerodynamic high-efficiency zone in the middle of the blade 100, forming a smooth force gradient, reducing the load unevenness caused by structural abrupt changes between regions, and further improving the overall operational stability and service life of the blade 100.

[0051] In the above embodiments, the cross-section may include a first cross-section, which is located at the end of the adjustment section 110 near the blade tip of the blade 100. The thickness at the opening of the trailing edge 130 of the first cross-section is 0.25 meters to 0.28 meters. The thickness at the opening of the trailing edge 130 of the first cross-section is limited to 0.25 meters to 0.28 meters, which can both adapt to the aerodynamic shape transition requirements of the adjustment section 110 towards the blade tip and ensure the structural stability of the main beam and the ply in this area. It is understandable that the first cross section, as the connecting section from the adjustment section 110 to the blade tip, has a trailing edge 130 opening thickness of 0.25-0.28 meters that can form a smooth transition with the aerodynamic profile of the blade tip region. If the thickness is less than 0.25 meters, the aerodynamic shape of the trailing edge 130 will be too narrow, and the airflow will easily generate local turbulence due to the abrupt change in cross section when passing through this point, which will aggravate the airflow separation. If the thickness is greater than 0.28 meters, the trailing edge 130 will be too wide and thick, and the attachment path of the airflow on the surface of the blade 100 will be lengthened, which will not only increase the flow resistance, but may also interfere with the aerodynamic efficiency of the blade tip region and affect the overall power generation performance.

[0052] In the above embodiments, the cross-section may further include a second cross-section located at the end of the adjustment section 110 near the blade root of the blade 100. The thickness of the second cross-section at the opening of the trailing edge 130 is 0.78 meters to 1.17 meters. It is understood that the curvature of the second cross-section near the blade root is relatively large. If the thickness of the opening of the trailing edge 130 is too small, wrinkles or poor adhesion may easily occur during layup due to the narrow space; if it is too thick, more composite material needs to be stacked, increasing process complexity and cost. The thickness of 0.78-1.17 meters provides reasonable space for the layup operation, ensuring a tight bond between the layup and the inner wall of the trailing edge 130, reducing the risk of slippage, controlling material usage and manufacturing difficulty, and improving the stability of the blade 100 molding quality.

[0053] In the above embodiments, the third parameter and the fifth parameter can satisfy the following relationship:

[0054] y1 = -92.926x 2 +158.35x-42.81

[0055] Where y1 is the fifth parameter and x is the third parameter.

[0056] When x varies within the range of 0.4-0.9, y1 will change in a corresponding pattern as x is adjusted. It will not be too low due to x being too small (which may cause insufficient structural or aerodynamic performance associated with the fifth parameter, such as insufficient support for the trailing edge 130 related components), nor will it be too high due to x being too large (which may cause structural redundancy associated with the fifth parameter, such as excessive thickness of the trailing edge 130 increasing weight or interfering with airflow).

[0057] In the above embodiments, the third parameter and the sixth parameter can satisfy the following relationship:

[0058] y2 = -0.6x 2 +1.4782x - 0.3777

[0059] Where y2 is the sixth parameter and x is the third parameter.

[0060] It can be understood that the above formula is a quadratic function that opens downwards, with its vertex corresponding to the optimal value of y2. The effective range of the third parameter x (0.4-0.9) falls exactly within the effective range of the function, ensuring that the sixth parameter (leading edge 120 curvature radius) is always within a reasonable range to meet the performance requirements of blade 100: when x changes between 0.4 and 0.9, y2 will fluctuate regularly, neither causing y2 to be too low due to x being too small (avoiding airflow turbulence and layup problems caused by an excessively small leading edge 120 curvature radius), nor causing y2 to exceed the reasonable upper limit due to x being too large (preventing an increase in aerodynamic drag caused by an excessively smooth leading edge 120).

[0061] Furthermore, this application embodiment also provides a wind turbine, including the wind turbine blade 100 of the above embodiment. A portion of the blade 100 forms an adjustment section 110. The maximum thickness of the cross-section of the adjustment section 110 is a first parameter, the chord length of the cross-section is a second parameter, and the ratio of the first parameter to the second parameter is a third parameter. The third parameter is greater than or equal to 0.4 and less than or equal to 0.9. The thickness at the trailing edge 130 opening of the cross-section is a fourth parameter, and the ratio of the fourth parameter to the second parameter is a fifth parameter. The fifth parameter is greater than 5.66% and less than 24.44%. By ensuring that the third parameter is between 0.4 and 0.9 and the fifth parameter is between 5.66% and 24.44%, not only is the opening angle of the trailing edge 130 increased, delaying flow separation at the trailing edge 130 and improving the aerodynamic stability of this area, but the overlap shape of the main beam and web is also improved. This effectively alleviates the structural slippage and plyfold wrinkling problems caused by abrupt curvature changes, improves the forming quality and overall stiffness of the blade 100, and thus improves the reliability of the wind turbine.

[0062] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A wind turbine blade (100), characterized in that, The blade (100) forms an adjustment section (110) along a portion of its spanwise direction. The maximum thickness of the cross section of the adjustment section (110) is a first parameter, the chord length of the cross section is a second parameter, the ratio of the first parameter to the second parameter is a third parameter, the third parameter is greater than or equal to 0.4, and the third parameter is less than or equal to 0.

9. The thickness at the opening of the trailing edge (130) of the cross-section is the fourth parameter, and the ratio of the fourth parameter to the second parameter is the fifth parameter, which is greater than 5.66% and less than 24.44%.

2. The wind turbine blade (100) according to claim 1, characterized in that, The third parameter is greater than or equal to 0.5 and less than or equal to 0.

8.

3. The wind turbine blade (100) according to claim 2, characterized in that, The radius of curvature of the leading edge (120) of the cross section is a sixth parameter, which is greater than 0.11 meters and less than 0.47 meters.

4. The wind turbine blade (100) according to claim 3, characterized in that, The ratio of the length of the adjustment section (110) to the length of the blade (100) is 0.2-0.

4.

5. The wind turbine blade (100) according to claim 4, characterized in that, The distance between the adjustment section (110) and the leaf root of the blade (100) is the seventh parameter, and the ratio of the seventh parameter to the length of the blade (100) is 0.05-0.

1.

6. The wind turbine blade (100) according to claim 5, characterized in that, The cross section includes a first cross section located at one end of the adjustment section (110) near the tip of the blade (100), and the thickness at the opening of the trailing edge (130) of the first cross section is 0.25 m to 0.28 m.

7. The wind turbine blade (100) according to claim 6, characterized in that, The cross section also includes a second cross section located at one end of the adjustment section (110) near the leaf root of the blade (100), and the thickness of the opening at the trailing edge (130) of the second cross section is 0.78 m to 1.17 m.

8. The wind turbine blade (100) according to any one of claims 1-7, characterized in that, The third parameter and the fifth parameter satisfy the following relationship: y1=-92.926x 2 +158.35x-42.81 Where y1 is the fifth parameter and x is the third parameter.

9. The wind turbine blade (100) according to any one of claims 3-7, characterized in that, The third parameter and the sixth parameter satisfy the following relationship: y2=-0.6x 2 +1.4782x-0.3777 Where y2 is the sixth parameter and x is the third parameter.

10. A wind turbine generator set, characterized in that, Includes the wind turbine blade (100) as described in any one of claims 1-9.

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