A method for designing a guide vane, a fan assembly

Abstract

The application provides a guide vane design method and a fan assembly, and belongs to an energy-saving fan, wherein the guide vane design method comprises the following steps: step 1, designing parameters of a two-dimensional fan blade airfoil; step 2, designing guide vane airfoil sections along the radial direction of a guide piece, wherein the number of the guide vane airfoil sections is multiple; and step 3, connecting the multiple guide vane airfoil sections through a sweep curve to obtain a final guide vane model. According to the application, the technical problem of poor guide efficiency of the guide vanes on the guide cover in the prior art can be solved.

Description

Technical Field

[0001] This invention belongs to the field of fan technology, specifically relating to a guide vane design method and fan components, and is an energy-saving fan. Background Technology

[0002] The airflow driven by the fan blades is transported through guide vanes. These vanes guide the airflow, but currently, there is no systematic and standardized professional design method for guide vanes used in livestock equipment. The industry relies solely on experience to create prototypes, lacking standardized parameter design criteria. During equipment operation, problems such as airflow separation, turbulent eddies, dead zones, and localized negative pressure areas easily occur. Airflow friction and turbulence losses are high, resulting in poor guiding and rectification performance. Furthermore, traditional guide vanes have low lift coefficients, insufficient guiding efficiency, and poor aerodynamic performance, failing to meet the ventilation requirements of modern livestock farming—high air volume, low energy consumption, and high energy efficiency. The overall energy efficiency of the equipment is low, making it difficult to meet the technical upgrade requirements of large-scale livestock ventilation equipment.

[0003] Because the guide vanes on the existing flow shield have technical problems such as low lift coefficient, insufficient flow guiding efficiency, and poor aerodynamic performance, this invention studies and designs a guide vane design method and a fan assembly, which belongs to an energy-saving fan. Summary of the Invention

[0004] Therefore, the present invention provides a guide vane design method and a fan assembly, which belongs to an energy-saving fan and can solve the technical problem of poor guide vane efficiency on the guide shroud in the prior art.

[0005] To address the above problems, this invention provides a guide vane design method, comprising:

[0006] Step 1: Design the parameters of the two-dimensional wind turbine airfoil;

[0007] Step 2: Design the airfoil cross-section along the radial direction of the guide vane; the number of airfoil cross-sections is multiple.

[0008] Step 3: Connect multiple airfoil sections with a sweep curve to obtain the final airfoil model.

[0009] In some embodiments, in step 1, the airfoil length of the guide vane is designed to be l, the curvature of the guide vane to be w, the height of the guide vane to be h, and the thickness of the guide vane to be h1, which satisfy w=h / l, and h / l≤0.2, h1 / h≤0.5.

[0010] In some embodiments, in step 1, both ends of the airfoil are circular arcs forming end faces, the diameter of the circle at one end of the airfoil is ra, and the diameter of the circle at the other end of the airfoil is rb, which satisfies that rb≤0.5ra.

[0011] In some embodiments, in step 1, the angle between the arc center of one end of the airfoil and the center point of the back surface of the airfoil and the horizontal line passing through the origin is the angle of attack g, which satisfies 0 ≤ g ≤ 30°.

[0012] In some embodiments, in step 2, the guide vane is divided into m sections at radial intervals along the guide member, the radial distance between two adjacent sections is rm, rm = (R-rc) / m, the angle between the airfoil section and the horizontal line is the angle of attack g, from r1 to rm, the airfoil angle of attack g on each section increases sequentially, R is the outer diameter of the guide vane, and rc is the inner diameter of the guide vane.

[0013] In some embodiments, the three dimensions of the guide vane are formed by connecting multiple planar airfoils through a sweep curve to form a single guide vane, with the camber of the guide vane being q and the sweep angle being p, where 15≤q≤30° and 45≤p≤60°.

[0014] The present invention also provides a fan assembly including the above-described guide vane design method.

[0015] In some embodiments, the fan assembly includes a guide vane, the guide vane includes a mounting member, and a plurality of guide vanes obtained by the above-described guide vane design method are spaced apart on the peripheral wall of the mounting member along the circumference, the number of the guide vanes being n, which satisfies 5≤n≤15.

[0016] In some embodiments, the installation angle between the guide vane and the mounting component is v, which satisfies 20°≤ v≤30°.

[0017] In some embodiments, the guide element further includes an outer ring connected to the end of the guide vane away from the mounting member, and a connector is connected between two adjacent guide vanes. The connector is located between the mounting member and the outer ring, and multiple connectors form an intermediate ring.

[0018] In some embodiments, there is at least one intermediate ring, and the total number of the intermediate ring, the mounting component, and the outer ring is n1, where n1 = 3 to 6. The installation angle between the guide vane and the intermediate ring is v2, which satisfies v2 = v + g / i; the installation angle between the guide vane and the outer ring is v3, which satisfies v3 = v + 2g / i, i = g / n1, where v is the installation angle between the guide vane and the mounting component, and g is the angle between the airfoil of the guide vane and the origin.

[0019] The guide vane design method and fan assembly provided by this invention have the following beneficial effects:

[0020] By designing airfoil sections along the radial direction of the guide vane, the number of airfoil sections can be multiple. These multiple airfoil sections are connected by a sweep curve. The airfoil shape of the guide vane adopts a forward-curved sweep curve design, which can increase airflow while reducing air friction loss, thereby improving aerodynamic efficiency. Attached Figure Description

[0021] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.

[0022] Figure 1 This is a flowchart of the guide vane design method of the present invention;

[0023] Figure 2 This is a schematic diagram of the airfoil structure in the guide vane design method of the present invention;

[0024] Figure 3 This is a schematic diagram of the airfoil angle of attack of each section in the guide vane design method of the present invention;

[0025] Figure 4 This is a top view of the five airfoil sections in the guide vane design method of the present invention;

[0026] Figure 5 This is a schematic diagram of the planar distribution of the airfoil in the guide vane design method of the present invention;

[0027] Figure 6 This is a side view of the guide vane installation in the guide vane design method of the present invention;

[0028] Figure 7 This is a schematic diagram of the guide vane structure in the guide vane design method of the present invention;

[0029] Figure 8 This is a schematic diagram of the installation of the guide vanes in the guide vane design method of the present invention. Figure 1 ;

[0030] Figure 9 This is a schematic diagram showing the completed assembly of the guide vanes in the guide vane design method of the present invention;

[0031] Figure 10 This is a side view of the guide vane after assembly in the guide vane design method of the present invention.

[0032] Figure 11 This is a perspective view of the guide vane after assembly in the guide vane design method of the present invention.

[0033] The attached figures are labeled as follows:

[0034] 1. Mounting components; 2. Connecting components; 3. Outer ring. Detailed Implementation

[0035] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0037] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0038] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0039] See also Figure 1-11 As shown, according to an embodiment of the present invention, a guide vane design method is provided, comprising:

[0040] Step 1: Design the parameters of the two-dimensional wind turbine airfoil;

[0041] Step 2: Design the airfoil cross-section along the radial direction of the guide vane; the number of airfoil cross-sections is multiple.

[0042] Step 3: Connect multiple airfoil sections with a sweep curve to obtain the final airfoil model.

[0043] In this technical solution, the airfoil cross-section of the guide vane is designed along the radial direction of the guide vane, and there are multiple airfoil cross-sections of the guide vane. The multiple airfoil cross-sections of the guide vane are connected by a sweep curve. The airfoil shape of the guide vane adopts a forward-curved sweep curve design, which can increase the air volume while reducing the friction loss of the air, thereby improving the aerodynamic efficiency.

[0044] The guide vane design of this invention has the characteristics of high air volume and high static pressure, and can perform for a long time under high pressure conditions, with high static pressure efficiency.

[0045] It should be noted that the guide vanes are stationary components, while the fan blades are rotating components. The guide vanes amplify the effect of high static pressure, allowing ordinary fans (without high static pressure) to achieve the effect of high static pressure, thus increasing the fan's air delivery distance.

[0046] In some implementations, step 4 is also included: verifying and optimizing the guide vane model. Specifically, the verification step involves simulating the three-dimensional vane model using simulation software to obtain corresponding parameters such as airflow and power, which are used to verify the effectiveness of the designed vane. The optimization step involves adjusting the airfoil structure based on the simulation results and then simulating again to form a closed loop in the design.

[0047] In some embodiments, in step 1, the airfoil length of the guide vane is designed to be l, the curvature of the guide vane to be w, the height of the guide vane to be h, and the thickness of the guide vane to be h1, which satisfy w=h / l, and h / l≤0.2, h1 / h≤0.5.

[0048] In this technical solution, the airfoil has an airfoil length of l, a camber of w, a height of h, and a thickness of h1, satisfying the conditions w = h / l, h / l ≤ 0.2, and h1 / h ≤ 0.5. This design allows for better airflow guidance, ensuring high efficiency under different wind speeds and preventing stall. It also enhances airflow deflection, reduces drag, and improves airflow efficiency.

[0049] See also Figure 2 As shown, the airfoil length of the guide vane refers to the distance between the two ends of the guide vane. Specifically, taking the direction of the arc-shaped opening of the guide vane as upward, the two ends of the guide vane have extension lines in a direction perpendicular to the lower plane, which are the vertical lines passing through the two ends of the guide vane, and the shortest distance between the vertical lines at the two ends of the guide vane; the curvature of the guide vane is such that the two ends of the guide vane are arc-shaped, and there is a line connecting the center of the arc at both ends of the guide vane and the center of the overall arc of the guide vane, and the angle between the two connecting lines; the height of the guide vane refers to the distance between the highest point of the upward extension of the guide vane and the lowest point below the guide vane; the thickness of the guide vane refers to the thickness of the middle part of the airfoil interface of the guide vane.

[0050] In some embodiments, in step 1, both ends of the airfoil are circular arcs forming end faces, the diameter of the circle at one end of the airfoil is ra, and the diameter of the circle at the other end of the airfoil is rb, which satisfies that rb≤0.5ra.

[0051] In this technical solution, the airfoil of the guide vane is generally bow-shaped, with the bow pointing downwards. The airfoil is an asymmetric airfoil with a large leading-edge arc and a small trailing-edge arc, guiding the airflow downwards. The large leading-edge arc delays separation, while the small trailing-edge arc reduces wake turbulence. The leading-edge arc is ra, and the trailing-edge arc is rb, satisfying rb ≤ 0.5ra. After implementation, the efficiency improvement is significant, representing the core design point for enhancing guide vane efficiency.

[0052] In some embodiments, in step 1, the center of the arc at one end of the airfoil is taken as the origin, and the angle between the line connecting the center of the arc at one end of the airfoil and the center point of the back surface of the airfoil and the horizontal line passing through the origin is the angle of attack g, which satisfies 0 ≤ g ≤ 30°.

[0053] See also Figure 3 As shown, the angle between the airfoil and the origin is the angle of attack g, where 0 ≤ g ≤ 30°. To adapt to different wind speeds, preferably, a small angle of attack g = 20° is used for low wind speeds, and a large angle of attack g = 25° is used for high wind speeds to avoid stalling.

[0054] It should be noted that the angle of attack here refers to the angle between the horizontal line passing through the center of the arc at one end of the airfoil, and the line connecting the center of the arc at one end of the airfoil to the center point of the back surface of the airfoil. The back surface of the airfoil refers to the side away from the center of the airfoil's arc, and the center point of the back surface of the airfoil refers to the midpoint of the arc on the side away from the center of the airfoil's arc.

[0055] In some embodiments, in step 2, the guide vane is divided into m sections at radial intervals along the guide member, the radial distance between two adjacent sections is rm, rm = (R-rc) / m, the angle between the airfoil section and the horizontal line is the angle of attack g, from r1 to rm, the airfoil angle of attack g on each section increases sequentially, where R is the outer diameter of the guide vane and rc is the inner diameter of the guide vane.

[0056] In this technical solution, red, in conjunction with [see also...] Figure 3 , Figure 6 , Figure 9 As shown, the guide vane's three-dimensional shape is formed by connecting multiple airfoil planes, with a radial distance of rm between each plane, where rm = (R - rc) / m. The angle of attack g between the airfoil and the horizontal line is the angle of attack g. From r1 to rm, the angle of attack g on each section increases sequentially, i.e., g1 ≤ g2 ≤ ... ggm. The diameter of the circle at the radial position of each plane on the guide vane is rm, that is, the diameter corresponding to r1 is d1, where d1 is the minimum diameter of the guide vane, and the diameter corresponding to rm is dm, where dm is the maximum diameter of the guide vane. This design can improve the efficiency of the guide vane and reduce power output loss, conforming to aerodynamics.

[0057] It should be noted that, in conjunction with the above, Figure 9 As shown, the guide vane includes multiple guide vanes. Along the radial direction of the guide vane, the guide vanes are divided into multiple sections. Each section is on a circle with a radius of rm and a diameter of dm.

[0058] It should be noted that, in conjunction with the above, Figure 3 and Figure 9As shown, the guide vane is divided into m sections at radial intervals along the guide member. Each section is an airfoil with the airfoil opening facing upwards. A horizontal line passing through the midpoint of the leading edge is perpendicular to the vertical direction of the upper and lower positions.

[0059] In some embodiments, the three dimensions of the guide vane are formed by connecting multiple planar airfoils through a sweep curve to form a single guide vane, with the camber of the guide vane being q and the sweep angle being p, where 15≤q≤30° and 45≤p≤60°.

[0060] In this technical solution, see [reference] Figure 6 and Figure 8 As shown, the three-dimensional shape of the guide vane is formed by connecting multiple airfoil planes, with each plane ranging from p1 to pm from top to bottom. The relative radii of the airfoils on each plane range from r1 to rm, preferably m=5. These are connected by sweep curves to form a single guide vane. The camber of the guide vane is q, and the sweep angle is p, where 15≤q≤30°, 45≤p≤60°, and preferably q=30° and p=60°. The camber q, or the blade bending angle, optimizes the airflow path; the sweep angle p, or the blade axial offset angle, reduces vortices.

[0061] It should be noted that, in conjunction with the above, Figure 8 As shown, the camber q of the guide vane refers to the maximum vertical distance between the arc line and the geometric chord line in the guide vane airfoil in three dimensions. (See also...) Figure 6 As shown, the sweep angle p is the angle between the leading edge of the guide airfoil and the vertical axis of the guide.

[0062] The present invention also provides a fan assembly including the above-described guide vane design method.

[0063] In some embodiments, the fan assembly includes a guide vane, which includes a mounting member 1. Along the circumference of the mounting member 1, a plurality of guide vanes obtained by the above-described guide vane design method are spaced apart on the peripheral wall of the mounting member 1. The number of guide vanes is n, which satisfies 5≤n≤15.

[0064] In this technical solution, the guide vane is composed of multiple single-blade guide vanes arranged in a circular array. The installation angle is v, and the number of single blades is n, where 5 ≤ n ≤ 15, preferably n = 10. This results in more uniform airflow, more reasonable manufacturing costs, and better efficiency.

[0065] In some embodiments, the mounting component 1 is circular, and the guide vanes are mounted on the outer peripheral wall of the mounting component 1.

[0066] In some embodiments, the mounting component 1 is disc-shaped, and the guide vanes are mounted on the outer peripheral wall of the mounting component 1.

[0067] It should be noted that the guide component is the airflow guiding part of the fan, and it is a stationary part.

[0068] In some embodiments, the installation angle between the guide vane and the mounting member 1 is v, which satisfies 20°≤ v≤30°.

[0069] In this technical solution, the angle between the guide vane and the mounting component 1 is the mounting angle v, which satisfies 20° ≤ v ≤ 30°. Each guide vane is fixed and surrounds the inner and outer rings with the same mounting angle. The root of the guide vane is connected to the inner ring, and the top of the guide vane is connected to the outer arc. The mounting angle v matches the angle of attack g to ensure optimized flow path, precise matching of airflow deflection angle, and improved overall performance.

[0070] In some embodiments, the guide element further includes an outer ring 3, which is connected to the end of the guide vane away from the mounting member 1. A connector 2 is connected between two adjacent guide vanes. The connector 2 is located between the mounting member 1 and the outer ring 3, and multiple connectors 2 form an intermediate ring.

[0071] In this technical solution, the center of the guide vane is mounting component 1, which is the inner ring. The center of the inner ring is closed, and the outer ring is a large ring with screw holes for fixing to the air duct. This increases the reliability of the air duct connection and improves the overall airflow guiding effect. The closed center of the inner ring increases the air pressure inside the air duct, thereby increasing the air delivery distance.

[0072] It should be noted that the connector 2 is located between the mounting part 1 and the outer ring 3, that is, the connector 2 is located in the radial center of the guide.

[0073] In some embodiments, the number of mounting rings for the guide vanes is n1=3~6, preferably n1=3, which are the inner ring, the middle ring, and the outer ring, respectively. That is, the number of middle rings can be increased. When there are multiple middle rings, the multiple middle rings are arranged at radial intervals along the guide vane.

[0074] In some embodiments, the inner ring, middle ring, and outer ring are collectively referred to as the mounting ring. The mounting ring protrudes at one end and has screw holes, with 4 to 8 holes, preferably 4, positioned at a horizontal 45° angle. This method reduces stress concentration, facilitates installation, and results in better structural strength.

[0075] Of course, the mounting ring can also be fixed to the guide vane using other fixing methods.

[0076] In some embodiments, there is at least one intermediate ring, and the total number of the intermediate ring, the mounting component 1, and the outer ring 3 is n1, where n1 = 3 to 6. The installation angle between the guide vane and the intermediate ring is v2, which satisfies v2 = v + g / i; the installation angle between the guide vane and the outer ring is v3, which satisfies v3 = v + 2g / i, i = g / n1, where v is the installation angle between the guide vane and the mounting component 1, and g is the angle between the airfoil of the guide vane and the origin.

[0077] In this technical solution, n1=3, which are the inner ring, the middle ring, and the outer ring, respectively. The installation angle between the guide vane and the inner ring is v1=v; the installation angle between the guide vane and the middle ring is v2=v+g / i; and the installation angle between the guide vane and the middle ring is v3=v+2g / i, i=g / n1. This allows the static pressure of the fan to expand from the center to both sides, increasing the area of ​​high static pressure air and enabling long-distance air delivery. The thickness of the installation ring is 3~5mm, and the various connections between the installation arc and the guide vane have rounded corners to ensure structural strength. g is the angle between the airfoil of the guide vane and the origin, i.e., the angle of attack.

[0078] The guide vane design method of the present invention can solve the following problems:

[0079] 1. Traditional guide vane designs are inefficient, cannot be quickly molded, and have poor model accuracy.

[0080] 2. Guide vanes designed using traditional methods cannot solve the problems of vortex and turbulent airflow in fans.

[0081] 3. Fans designed using traditional methods do not have integrated guide vanes, which can easily lead to air stratification losses and low fan efficiency in high static pressure velocity and high air volume applications.

[0082] The guide vane design method of this invention ensures that the designed guide vane meets the requirements of high static pressure and high flow rate by adjusting key parameters such as airfoil thickness, camber, and length. The guide vane designed by this method features high airflow and high static pressure, can operate under high pressure for extended periods, and has high static pressure efficiency. The airfoil shape of this guide vane adopts a forward-curved sweep curve design, which can increase airflow while reducing air friction loss, thereby improving aerodynamic efficiency.

[0083] The guide vane design method of this invention reduces flow separation losses at the blade tip, decreases friction with air, and improves the static pressure efficiency of the fan. The final three-dimensional molding yields a guide vane with high energy efficiency and high static pressure, suitable for fans operating under high static pressure conditions, thus improving the energy efficiency ratio. The reference table compares the effects of traditional fans with the new airfoil and swept-back design guide vane of this method. Under the same operating conditions, the energy efficiency ratio is 18.2% higher than that of traditional fans, and the air volume is increased by 2214 m³ / h, further demonstrating that the guide vane designed by the method of this invention has a better effect, improves efficiency, and results in high overall machine energy efficiency.

[0084]

[0085] It will be readily understood by those skilled in the art that, without conflict, the advantageous technical features of the above-mentioned methods can be freely combined and superimposed.

[0086] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A guide vane design method, characterized in that: include: Step 1: Design the parameters of the two-dimensional wind turbine airfoil; Step 2: Design the airfoil cross-section along the radial direction of the guide vane; the number of airfoil cross-sections is multiple. Step 3: Connect multiple airfoil sections with a sweep curve to obtain the final airfoil model.

2. The guide vane design method according to claim 1, characterized in that: In step 1, the airfoil length of the guide vane is designed to be l, the curvature of the guide vane is w, the height of the guide vane is h, and the thickness of the guide vane is h1, which satisfy w=h / l, and h / l≤0.2, h1 / h≤0.

5.

3. The guide vane design method according to claim 1, characterized in that: In step 1, both ends of the airfoil are circular arcs forming end faces. The diameter of the circle at one end of the airfoil is ra, and the diameter of the circle at the other end of the airfoil is rb, which satisfies that rb≤0.5ra.

4. The guide vane design method according to claim 3, characterized in that: In step 1, the center of the arc at one end of the airfoil is taken as the origin. The angle between the line connecting the center of the arc at one end of the airfoil and the center point of the back surface of the airfoil and the horizontal line passing through the origin is the angle of attack g, which satisfies 0 ≤ g ≤ 30°.

5. The guide vane design method according to claim 1, characterized in that: In step 2, the guide vane is divided into m sections at radial intervals along the guide member, and the radial distance between two adjacent sections is rm, where rm = (R-rc) / m, R is the outer diameter of the guide vane, rc is the inner diameter of the guide vane, and the angle between the airfoil section and the horizontal line is the angle of attack g. From r1 to rm, the angle of attack g of the airfoil on each section increases sequentially.

6. The guide vane design method according to claim 5, characterized in that: The three-dimensional shape of the guide vane is formed by connecting multiple planar airfoils through a sweep curve to form a single guide vane. The curvature of the guide vane is q, and the sweep angle is p, where 15≤q≤30° and 45≤p≤60°.

7. A fan assembly, characterized in that: The guide vane design method includes any one of claims 1-6.

8. The wind turbine assembly according to claim 7, characterized in that: The fan assembly includes a guide vane, which includes a mounting component (1). Along the circumference of the mounting component (1), a plurality of guide vanes obtained by the guide vane design method according to any one of claims 1-6 are spaced apart on the circumferential wall of the mounting component (1). The number of guide vanes is n, which satisfies 5≤n≤15.

9. The wind turbine assembly according to claim 8, characterized in that: The installation angle between the guide vane and the mounting component (1) is v, which satisfies 20°≤ v≤30°.

10. The wind turbine assembly according to claim 9, characterized in that: The guide element also includes an outer ring (3), which is connected to the end of the guide vane away from the mounting element (1). A connector (2) is connected between two adjacent guide vanes. The connector (2) is located between the mounting element (1) and the outer ring (3). Multiple connectors (2) form an intermediate ring.

11. The wind turbine assembly according to claim 10, characterized in that: There is at least one intermediate ring. The total number of the intermediate ring, the mounting component (1), and the outer ring (3) is n1, where n1 = 3~6. The installation angle between the guide vane and the intermediate ring is v2, which satisfies v2 = v + g / i. The installation angle between the guide vane and the outer ring is v3, which satisfies v3 = v + 2g / i, i = g / n1. Where v is the installation angle between the guide vane and the mounting component (1), and g is the angle between the airfoil of the guide vane and the origin.

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