Tailway blade, impeller of wind turbine generator and wind turbine generator

Abstract

The invention discloses a tail swinging type blade, an impeller of a wind turbine generator and the wind turbine generator. The blade is divided into a fixed part and a swinging part. The swing part is composed of a link matrix jointly established by a plurality of chain link units and pin shafts and blade shell segments. Each chain link unit comprises a connecting piece, a sleeve and a supporting piece. The two connecting pieces are arranged in parallel, and the sleeve and the supporting piece are arranged between the two connecting pieces. The pin shaft is sleeved with the sleeve, and the blade shell is supported by the supporting piece in a segmented mode. A group of chain link units which are arranged in the chord line direction of the blades and penetrate through the multiple pin shafts are basic rows, and adjacent basic rows form a link structure. The multiple chain link units in the spanwise direction of the blade form a basic column, and the supporting pieces in the basic column jointly support the blade shell segments. The plurality of blade shell segments collectively fit the airfoil of the blade. According to the tail-swinging type blade, the aerodynamic shape is changed, the attack angle is changed, the aerodynamic performance of the blade is improved, and the problems that a vertical shaft unit is difficult to start and speed up are solved. The cost is low, the structure is simple, and processing and manufacturing are easy.

Description

Technical Field

[0001] This invention belongs to the field of wind power generation technology, specifically relating to a tail-swivel blade, a wind turbine impeller, and a wind turbine unit. Background Technology

[0002] Vertical axis wind turbines have a long history of development, and extensive research has been conducted globally over the years, particularly on vertical axis turbines using lift blades (such as the Darrieux type). Vertical axis wind turbines lag significantly behind horizontal axis wind turbines in terms of wind energy conversion efficiency. Therefore, large-scale wind turbines currently employ horizontal axis technology. Vertical axis wind turbines, due to their elimination of the need for a yaw system, simpler structure, and relatively lower cost, have secured a place in small and micro wind turbine projects. Among these, the H-type (using straight blades) vertical axis wind turbine is the mainstream model. Existing vertical axis wind turbine technology suffers from two main drawbacks: 1) Poor self-starting capability: when the wind speed exceeds the cut-in wind speed, the rotor remains stationary with a large moment of inertia, resulting in insufficient aerodynamic torque to drive its rotation; 2) When the rotor's tip velocity is relatively low (i.e., high wind speed but low rotational speed), the rotational speed enters a so-called "dead zone" (first proposed by J. R. Barker in a 1983 paper, and verified experimentally by other scholars). The rotor speed is difficult to increase and remains at a low level, thus failing to generate more electricity. The underlying cause of these two technical defects is essentially the same: at a given wind speed, the rotor's aerodynamic torque is insufficient, or in other words, the aerodynamic force generated by the blades is insufficient. From an aerodynamic perspective: when the wind speed is sufficiently high, a stationary rotor or a low tip velocity indicates insufficient rotor rotational speed, causing wind speed to dominate the composite velocity vector on the blades. In other words, regardless of the blade's orientation, the direction of the wind speed determines the direction of the composite velocity, which in turn determines the angle between the composite velocity and the blade chord line, i.e., the angle of attack. A small or large angle of attack will result in insufficient aerodynamic performance of the blades, meaning insufficient aerodynamic force generated on the blades. Insufficient aerodynamic force on the blades leads to insufficient torque generated by the impeller, failing to drive the impeller to increase its speed, creating a vicious cycle. To solve the problem of insufficient start-up capability, most existing technical solutions adopt the method of adding drag-type impellers. However, this solution only has a positive effect during the start-up phase of vertical axis wind turbines. When the impeller speed is high enough, a compatibility problem arises between the drag-type impeller used for start-up and the Darlie lift impeller. That is, in a certain direction, the drag-type impeller and the lift impeller cancel each other out, reducing the overall aerodynamic performance. In addition, the installation of drag-type impellers reduces the blade speed of the lift impeller downwind, further reducing aerodynamic performance, resulting in a trade-off. Changing the aerodynamic performance of the blades requires starting with changing the blade angle of attack. If the direction of the resultant velocity cannot be changed (because the wind speed in the environment where vertical axis wind turbines are located is usually difficult to change artificially, and the impeller speed cannot be improved), then the only solution is to change the pitch angle.For conventional vertical axis wind turbines, the pitch angle is a fixed value, sometimes referred to as the "installation angle," meaning it is determined during blade installation and remains unchanged. The drawback of a fixed pitch angle is that when the angle of attack of the blades differs significantly in different azimuths, a fixed pitch angle cannot guarantee effective improvement in aerodynamic characteristics. Furthermore, an excessively large pitch angle can negatively impact the rotor's tip speed ratio (i.e., increased rotor speed). To address the shortcomings of fixed pitch angle technology, many existing solutions employ variable pitch technology. However, vertical axis wind turbines differ from horizontal axis wind turbines in that the required pitch angle varies for each azimuth. Therefore, implementing variable pitch requires the vertical axis wind turbine to have the ability to detect the azimuth angle in real time, and it must also have an actuator to actively change the pitch angle. This system functionality necessitates the use of electrical and control systems (e.g., slip rings), significantly increasing the cost of the vertical axis wind turbine and reducing system reliability. This creates a paradox: increasing pitch capability is intended to improve the performance of vertical axis wind turbines and enhance their market competitiveness, while the addition of traditional pitch systems reduces the cost-effectiveness and reliability of vertical axis wind turbines. In summary, current vertical axis wind turbine technology still cannot solve the following problems: 1) without affecting the high-speed operating efficiency of the rotor, rotor startup is difficult; 2) without significantly increasing costs, the rotor, after startup, is in a low tip speed ratio state and cannot effectively and quickly increase its rotational speed for power generation. Therefore, a new technology is needed to break through the inherent limitations of existing pitch and other technologies, achieving improved aerodynamic performance by changing the blade pitch angle and angle of attack while maintaining low cost, simple structure, and high reliability. Summary of the Invention

[0003] In order to solve at least one of the above-mentioned technical problems, a first aspect provides a tail-swinging blade, wherein the blade is divided into a fixed part and a swinging part, the fixed part is defined as the blade extending from the leading edge to the middle part of the blade, and the remaining part is defined as the swinging part, and a connection is provided between the fixed part and the swinging part; The swing section is mainly composed of a rear support structure and blade shell segments; The rear support structure is composed of a link matrix jointly established by multiple link units and multiple pins; Each of the link units includes two identical links, at least two identical sleeves and supports; The two connecting members are arranged in parallel and connected by the two sleeves; the support member is used to support the blade shell segment. The support and the connecting member are separate structures and are fixedly connected together, or the support and the connecting member form an integral structure. Multiple pins are spaced apart along the chord direction of the blade, and the sleeves of multiple link units are sequentially inserted into the pins; a group of multiple link units arranged along the chord direction of the blade constitutes the basic row of the link matrix; Two adjacent basic rows are incorporated into one basic row along the span of the blade, and each link in each basic row simultaneously abuts with two adjacent links in the adjacent basic rows, forming a link structure. The basic rows are arranged along the span of the blade from one end of the blade to the other end; Along the spanwise direction of the blade, multiple link units located in the same column constitute the basic column of the link matrix; multiple supports in the basic column jointly support the blade shell segment; A blade shell segment supported by a basic column can be either two independent structures belonging to the two airfoils of the blade, or a complete structure that can simultaneously accommodate the two airfoils of the blade. When a blade shell segment supported by a basic column is a complete structure, the blade shell segment consists of two airfoil segments and a curved segment. The blade airfoil is formed by the multiple blade shell segments and the fixed portion of the blade shell.

[0004] In a further technical solution, the connector is provided with two spaced circular holes, the diameter of which is the same as the outer diameter of the sleeve end.

[0005] In a further technical solution, the connecting piece is interference-fitted to the end of the sleeve through a circular hole.

[0006] When the support member and the connecting member are separate structures, the two ends of the support member along the span of the blade are respectively fixedly connected to the two connecting members of the same link unit.

[0007] The pin runs through the entire basic row, and the pin adopts an integral structure or a segmented structure.

[0008] When a blade housing segment supported by one of the basic columns is a complete structure, the curved segment is located on the side near the leading edge of the blade.

[0009] When a blade housing segment supported by one of the basic columns is a complete structure, the surface of the curved segment is part of a cylindrical surface.

[0010] From the middle of the blade to the trailing edge of the blade, the support surfaces of the multiple supports in the link units of each basic row are fitted to the airfoil configuration of the blade.

[0011] In a second aspect, a wind turbine impeller is provided, which includes the sway blade described in the first aspect.

[0012] Thirdly, a wind turbine generator is provided, which includes the impeller of the wind turbine generator described in the second aspect.

[0013] The beneficial effects of this invention are as follows: First, it can passively change the aerodynamic shape of the blades according to their orientation, thereby altering the blade's angle of attack. By changing the angle of attack during the impeller startup phase or when the impeller tip speed is relatively low, it improves the blade's aerodynamic performance, increases the impeller's torque, and thus increases the blade's rotational speed. This solves the problems of difficult startup and acceleration in conventional vertical axis turbine units. Second, the aerodynamic shape change of the swaying blade is entirely driven by external wind pressure, avoiding complex and unreliable electric drive mechanisms and sensors. Compared to conventional pitch control technology, this controls system costs and ensures reliability. Third, although the technology of changing aerodynamic shape has been applied to aircraft wings, it heavily relies on expensive materials or components such as flexible skin. The swaying blade, by fitting the aerodynamic shape of the blade to multiple blade shell segments, achieves the effect of changing the blade's aerodynamic shape to improve impeller acceleration performance while controlling blade costs. Finally, the rear support structure of the swaying part and the blade shell segments are made of simple profiles, with simple structure, simple connection relationships, low processing costs, and high reliability. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a tail-swinging blade in the first half-turn of impeller rotation according to an embodiment of the present invention; Figure 2 This is a schematic diagram of a tail-swinging blade in an embodiment of the present invention, showing the tail swaying after the impeller has rotated half a circle. Figure 3 This is a schematic diagram of a tail-swinging blade according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the rear support structure of the oscillating part of a tail-shaped blade according to an embodiment of the present invention. Figure 5 This is a schematic diagram of a tail-swinging blade chain link unit according to an embodiment of the present invention; Figure 6 This is a schematic diagram of a tail-shaped blade chain link unit connector and sleeve connection according to an embodiment of the present invention; Figure 7 This is a schematic diagram of the axial side of a tail-shaped blade link unit according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the basic row of a tail-shaped blade linkage matrix according to an embodiment of the present invention; Figure 9This is a schematic diagram illustrating the arrangement of multiple basic rows in a tail-shaped blade link matrix according to an embodiment of the present invention; Figure 10 This is a schematic diagram of the basic row axis of a tail-shaped blade linkage matrix according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the basic columns of a tail-shaped blade link matrix according to an embodiment of the present invention; Figure 12 This is a top view of a tail-shaped blade according to an embodiment of the present invention; Figure 13 This is a schematic diagram of the segmented arrangement of the blade shell of a tail-shaped blade according to an embodiment of the present invention; Figure 14 This is a schematic diagram of another segmented blade housing configuration according to the present invention.

[0015] Explanation of icon numbers: 1. Blade; 1.1. Fixed part; 1.101. Leading edge; 1.2. Oscillating part; 1.201. Trailing edge; 1.21. Rear support structure; 1.211. Link unit; 1.2111. Connector; 1.2112. Sleeve; 1.2113. Support; 1.2114. Circular hole; 1.212. Pin; 1.22. Blade shell segment; 1.221. Airfoil section; 1.221. Bending section; 1.23. Basic row; 1.24. Basic column; 2. Impeller shaft; 3. Blade chord.

[0016] It is important to note that the above figures are for illustrative purposes only and are not intended to demonstrate any actual structure or reflect the dimensions, proportions, or other details of various components. To more clearly illustrate the principles of the invention and to avoid obscuring these principles with unnecessary details, the examples in the figures have been simplified. These illustrations will not cause inconvenience to those skilled in the art in understanding this patent, while actual embodiments may include more modules or components. Detailed Implementation

[0017] To make the objectives and technical solutions of the embodiments of the present invention clearer, the embodiments of the present invention will be fully described below with reference to the accompanying drawings. This patent describes only a portion of the embodiments, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0018] I. Issues related to improving vertical axis starting capability and acceleration capability at low peak speed ratios This section lists some existing or common technical solutions and explains the advantages and disadvantages of each: 1) Add a resistance-type impeller Drag-type impellers have the advantage of strong starting capability. Therefore, simply adding a drag-type impeller inside the lift-type impeller is indeed effective in improving the starting capability of Darrieux-type vertical axis wind turbines. However, the optimal tip speed ratio of the drag-type impeller is relatively low. That is to say, when the rotational speed of the lift-type impeller (the main source of aerodynamic force) increases, the tip speed ratio also increases. The lift-type impeller operates at maximum efficiency, while the drag-type impeller operates inefficiently, even canceling out the aerodynamic contribution of the lift-type impeller, resulting in a "1 plus 1 less than 1" effect. Therefore, drag-type and lift-type impellers cannot coexist indefinitely. Introducing a mechanism that can detach from the drag-type impeller under given conditions would undoubtedly greatly increase system costs and is not practical. In addition, the presence of the drag-type impeller (whether or not it rotates coaxially with the lift-type impeller) will inevitably affect the wind speed acting on the lift-type impeller, reducing aerodynamic force.

[0019] 2) Variable blades Pitch control is a standard technology in horizontal axis wind turbines and a standard feature of variable speed power regulation wind turbines. However, it is less common in vertical axis wind turbines. Nevertheless, some existing patented technologies still explore variable pitch blades (or impellers). Theoretically, if the blades could be pitch-adjusted, the angle of attack could indeed be changed by adjusting the pitch angle, thereby improving the aerodynamic performance of the blades (impeller). However, the cost is high: taking an H-type (i.e., straight-blade) vertical axis wind turbine as an example, a pitch control system is added to the conventional straight blade configuration. This includes a transmission mechanism to drive the blade rotation, bearings required for pitch control, a drive unit (such as a pitch motor and reducer as the power source), and a (variable frequency) driver. Furthermore, a controller (such as a PLC) capable of calculating the required pitch angle in real time is needed. Since the drive unit and controller (especially the controller) generally do not rotate with the impeller, slip rings are required to transmit the electrical energy and control signals needed to drive the pitch control to the drive end. Meanwhile, since the pitch angle required for the blades of a vertical axis wind turbine changes in every azimuth, an azimuth angle measurement device is needed. Finally, to ensure closed-loop control in the pitch control, an actual pitch angle measurement device is also required to provide angle measurement as negative feedback to the drive or controller. Furthermore, the number of pitch angle measurement devices should be consistent with the number of blades. As can be seen from the above description, achieving independent blade pitch control in a vertical axis wind turbine requires a relatively complex drive control and detection system (including slip rings). Besides significantly increasing costs, the large number of nodes in this system inevitably leads to increased risk points and decreased reliability. This system not only has numerous components but also occupies considerable space; it is conceivable that it is impossible to install a blade pitch system in small and micro wind turbines (with power ranging from tens of watts to several kilowatts). It is worth noting that some existing technologies mention unified pitch control, where a single drive unit simultaneously drives all blades to pitch at the same angle. This technology is entirely feasible in horizontal axis wind turbines and has existing practical applications. However, it is unsuitable for vertical axis wind turbines. The reason is that the azimuth angle of each blade is different at any given time. Different azimuth angles require different pitch angles. Therefore, setting a uniform pitch angle for all blades will greatly reduce the actual effect of improving the aerodynamic performance of the blades.

[0020] 3) Deformable blades Current deformable blades are all active deformable blades. By incorporating pneumatic or hydraulic drive mechanisms within the blade shell, the internal "skeleton" structure of the blade is essentially altered. Simultaneously, materials similar to flexible skins used in fighter jets, such as film membranes, are used to change the blade's shape in accordance with the alteration of the blade's "skeleton" structure, thereby changing the airfoil and consequently altering the blade's chord line and angle of attack. Disadvantages of this technical approach include: firstly, the need for a complex actuator and detection equipment to change the blade's aerodynamic shape based on measured values ​​(such as azimuth angle and rotational speed), significantly increasing costs and reducing reliability. Secondly, the cost of flexible skin-like blade shells to accommodate changes in the blade's "skeleton" structure is high; for civilian commercial vertical axis wind turbine blades, such costly shell materials are not a viable option. Furthermore, unlike fighter jet applications, blades rotate at high speeds within a vertical axis impeller, requiring different aerodynamic shapes for different azimuth angles within a single revolution—essentially constantly changing the aerodynamic shape throughout a revolution. Even if the actuator could achieve timely "skeleton" deformation within such a high-speed rotating blade, the blade shell encasing the skeleton would still suffer significant fatigue damage (it's worth noting that the flexible skin in fighter jet wings does not undergo such frequent expansion and contraction). Therefore, the existing deformable blade technology is not practical.

[0021] II. Core Features of Patents The core technical features and technical effects of the tail-sweeping blade proposed in this paper can be summarized in the following two points: 1) Multiple link units form multiple basic rows and columns, constituting a link matrix composed of multiple link units and pins. Multiple supports within the link matrix collectively support the blade's outer shell, while relative rotation between the basic columns allows for deformation of the blade's internal support structure (or "skeleton"). The main advantage is that, apart from slight differences in the shape of the supports, the main structure of each link unit remains unchanged throughout the matrix, facilitating mass production. Furthermore, the multi-segment link structure, with multiple pins as pivots, enables segmented rotation, achieving the technical effect of overall structural deformation. In addition, the link matrix provides better support for the blade shell than existing technologies, eliminating the problem of large areas of the blade shell lacking supporting structures underneath.

[0022] 2) Based on the airfoil profile curve of the blade, segmented blade shells are constructed, and these segments collectively fit the aerodynamic shape of the blade. When the internal support (or "skeleton") of the blade deforms, the segmented blade shells move relative to each other, ensuring the integrity of the overall blade shape. This avoids the use of expensive shell materials (similar to the flexible skin used in aircraft wings). Furthermore, the relative movement between the segmented blades does not involve metal stretching or contraction, thus avoiding fatigue strength issues.

[0023] III. Basic Principles of Patents The technical solution aims to achieve the following three functions: 1) The internal support of the blade has the function of deformation. This is achieved through the link unit matrix and multiple pins. The basic columns in the link matrix actually form a rotating pair with the corresponding pins, so that multiple basic columns can rotate relative to each other, thereby deforming the middle and rear part of the blade, and thus achieving an effect similar to "fish tail swing".

[0024] 2) The blades passively deform at appropriate orientations, altering their aerodynamic shape and angle of attack. Based on the internal support deformation capability, the blades deform accordingly depending on their orientation. The entire process requires no external power, achieving completely passive and autonomous blade deformation. The specific principle is as follows: like Figure 1 As shown, the upper part is north, and the wind direction is westerly (i.e., from left to right). When the blade (1) is in the northwest position, the middle and rear part of the blade (1) (i.e., the oscillating part) rotates under the action of wind pressure, causing the tail of the blade (1) to move towards the impeller shaft (2). At this time, the position of the blade's chord line (3) changes, and the pitch angle and angle of attack of the blade (1) change accordingly. Figure 2 As shown, when the blade (1) is in the southeast position, the middle and rear part of the blade (1) (i.e., the oscillating part) moves outward under the action of wind pressure (i.e., away from the impeller shaft (2)). At this time, the position of the blade chord (3) changes, and the pitch angle and angle of attack of the blade (1) change accordingly. It is worth noting that, as Figure 1 The blade (1) shown is positioned in the first half of the impeller's rotation, that is, the half closer to the incoming airflow; as Figure 2 The blade (1) shown is positioned during the latter half of the impeller rotation. The required pitch angle compensation when blade (1) is in the first half of the rotation and the required pitch angle compensation when blade (1) is in the latter half of the rotation have positive and negative angles. The technical solution proposed in this paper enables... Figure 1 and Figure 2 The direction of the blade (1) shown in the figure corresponds exactly to the requirement of different directions of pitch angle compensation (i.e., the positive and negative of the pitch angle). The composition of the velocity vector triangle of the blade (1) in different orientations and the aerodynamic calculation can be found in the existing literature, and will not be elaborated here.

[0025] 3) When the internal support of the blade, which is composed of a link matrix, deforms, the blade automatically adapts through the relative motion of the segmented shell, thereby completing the change of the blade's aerodynamic shape.

[0026] IV. An embodiment of a tail-swinging blade like Figure 3As shown, the oscillating blade is divided into a fixed part (1.1) and an oscillating part (1.2). The fixed part (1.1) extends from the leading edge (1.101) to the middle of the blade (1), and the remaining part is the oscillating part (1.2). The fixed part (1.1) and the oscillating part (1.2) are connected, which includes both the shell connection and the internal support structure connection. In this embodiment, the fixed part (1.1) can be considered to be the leading edge and the part near the leading edge of a conventional blade, mainly composed of the front support structure and the front blade shell. The oscillating part (1.2) is mainly composed of the rear support structure (1.21) and the blade shell segment (1.22).

[0027] like Figure 4 As shown, the rear support structure (1.21) is composed of a link matrix jointly established by multiple link units and multiple pins (1.212). Its main function is to support the blade shell segment (1.22), ensure the integrity of the blade (1), and realize the "tail swing" effect of the blade.

[0028] Among them, such as Figure 5 As shown, each link unit (1.211) includes two identical links (1.2111), at least two identical sleeves (1.2112), and a support (1.2113). In this embodiment, there are two sleeves (1.2112). As the chord length of the blade (1) increases, the length of the links (1.2111) along the chord (3) of the blade increases, and the number of sleeves (1.2112) may increase.

[0029] like Figure 6 As shown, two connecting parts (1.2111) are arranged parallel to each other, and two parallel sleeves (1.2112) are arranged between the connecting parts (1.2111), with each end of the sleeve (1.2112) fixedly connected to one of the two connecting parts (1.2111). A certain distance is reserved between the two sleeves (1.2112) to allow space for the installation of the support (1.2113). The connection point between the end of the sleeve (1.2112) and the connecting part (1.2111) can be close to the edge of the connecting part (1.2111). In some other embodiments, the two sleeves (1.2112) may not be arranged parallel to each other.

[0030] In this embodiment, the connector (1.2111) is a plate with a certain thickness. The structure of the connector (1.2111) itself is not subject to special constraints; in other embodiments, a non-plate structure can be used. It is provided with circular holes (1.2114), the number of which is determined by the number of sleeves (1.2112). The spacing between the circular holes (1.2114) is consistent with or approximately the distance between the sleeves (1.2112) (or consistent with the axial distance of the sleeves (1.2112)), and the space of the circular holes (1.2114) matches the outer diameter of the end of the sleeve (1.2112). The connector (1.2111) is interference-fitted to the end of the sleeve (1.2112) through the circular holes (1.2114).

[0031] like Figure 5 and Figure 7 As shown, the support member (1.2113) is disposed between the two sleeves (1.2112), and the function of the support member (1.2113) is to support the blade shell segment (1.22). The support member (1.2113) and the connecting member (1.2111) are separate structures, fixedly connected together, or the support member (1.2113) and the connecting member (1.2111) form an integral structure. In this embodiment, the support member (1.2113) and the connecting member (1.2111) are separate structures, that is, two independent parts, and fixedly connected together (the connection method can be mechanical connection or welding, etc.). In some other embodiments, the support member (1.2113) and the connecting member (1.2111) can form an integral structure, which is obtained by processing a complete profile.

[0032] The support member (1.2113) is fixedly connected at both ends along the spanwise direction of the blade (1) to two connecting members (1.2111) of the same link unit (1.211). In this embodiment, most of the support members (1.2113) are connected to the connecting members (1.2111) at the end face near the sleeve (1.2112). The support member (1.2113) is provided with two support surfaces for supporting the blade shell segment (1.22), and the support surfaces are located on both sides of the support member (1.2113) in the airfoil direction of the blade (1). Figure 7As shown, in this embodiment, the support member (1.2113) is approximately the shape of a quadrilateral frame (other shapes may be used in other embodiments). The support member (1.2113) is symmetrical about the sleeve (1.2112). The reason for this arrangement is that in this embodiment, the blade (1) uses a symmetrical airfoil, such as the NACA00XX series airfoil. If the blade (1) uses an asymmetrical airfoil, the situation will be more complicated. Because when the blade (1) uses an asymmetrical airfoil, according to the requirements of the new aerodynamic shape generated by the deformation of the blade (1) in the first and second halves of the rotation, the structural shape of the support member (1.2113) should also be asymmetrical, which increases the difficulty of processing and manufacturing.

[0033] like Figure 8 As shown, multiple pins (1.212) are arranged parallel to each other along the chord (3) direction of the blade. Simultaneously, two sleeves (1.2112) of multiple link units (1.211) are sequentially fitted onto two pins (1.212). A group of multiple link units (1.211) arranged along the chord (3) direction of the blade constitutes the basic row (1.23) of the link matrix. In this embodiment, the pins (1.212) are arranged in parallel. In some other embodiments, the pins (1.212) may also be arranged non-parallel. Figure 8 In a basic row (1.23) shown, two adjacent link units (1.211) are not directly connected. Also, since the two sleeves (1.2112) of each link unit (1.211) are relatively fixed, the link unit (1.211) cannot rotate relative to the two pins (1.212) into which its own sleeve (1.2112) is fitted.

[0034] like Figure 9 As shown, two adjacent basic rows (1.23) are incorporated into one basic row (1.23) along the span of the blade (1), and each link (1.2111) in each basic row (1.23) simultaneously fits with two links (1.2111) in the adjacent basic row (1.23), forming a link (1.2111) structure. It can be seen that in such a... Figure 10 In the three basic rows (1.23) shown, adjacent basic rows (1.23) are staggered. They are actually offset by the position of a pin (1.212). Taking the middle basic row (1.23) as an example, two adjacent connecting parts (1.2111) along the chord line (3) of the blade are connected together through a connecting part (1.2111) of another basic row (1.23), forming a connecting structure. And in... Figure 8 In the basic row shown (1.23), two adjacent link units (1.211) are not directly connected. Note the difference here: Figure 8The structure shown only describes the configuration of a basic row (1.23), not the final structural effect. Therefore, the two adjacent link units (1.211) are not directly connected. However, the three basic rows (1.23) shown in Figure 10 represent a more general structural effect. Through the configuration of multiple basic rows (1.23), each basic row (1.23) can link its link units (1.211) together using the link units (1.211) in its adjacent basic rows (1.23). This is the significance of the link matrix. Because the link units (1.211) can be linked together, adjacent link units (1.211) can also rotate relative to each other. Based on this, the rear support structure (1.21) can deform, thereby changing the aerodynamic shape of the blade (1).

[0035] To provide complete support for the shell of the blade (1), the basic rows (1.23) are arranged along the spanwise direction of the blade (1) from one end to the other. It is worth noting that in this embodiment, the distance between the two links (1.2111) in the link unit (1.211) is fixed, i.e., the length of the sleeve (1.2112) is fixed, which is beneficial for mass production. In practice, however, the length of the blade (1) is customizable and can be adjusted according to actual needs. Therefore, the arrangement of multiple basic rows (1.23) may not necessarily be sufficient to cover the entire spanwise direction of the blade (1). In practice, a custom-sized sleeve (1.2112) can be used near the spanwise end of the blade (1) to compensate for the required space, depending on the needs.

[0036] The pin (1.212) runs through all the basic rows (1.23). The pin (1.212) adopts an integral structure or a segmented structure. When the blade (1) length increases, the length of the basic pin (1.212) may not meet the requirements. At this time, multiple pins need to be connected together to form a segmented structure.

[0037] like Figure 11As shown, along the spanwise direction of the blade (1), multiple link units (1.211) located in the same column constitute the basic column (1.24) of the link matrix, that is, multiple link units (1.211) in each basic column (1.24) are fitted into the same two pins (1.212). The support members (1.2113) in each basic column (1.24) jointly support the blade shell segment (1.22). In this embodiment, the support members (1.2113) in all link units (1.211) in the same basic column (1.24) have the same size and shape along the chord (3) direction of the blade. This setting is based on the straight blade scheme of the H-type vertical axis wind turbine, that is, along the spanwise direction of the blade (1), the airfoil of the blade (1) does not change, so the size and shape of the multiple support members (1.2113) supporting each blade shell segment (1.22) will not change. Meanwhile, in each basic row (1.23), the support surfaces of multiple link units (1.211) from the middle of the blade (1) to the trailing edge (1.201), covering the entire oscillating part (1.2), are all designed to fit the airfoil of the blade (1). This design allows the support unit (1.2113) to better fit the blade shell segment (1.22), ensuring that the airfoil of the blade (1) is as expected when the blade (1) does not deform or when it does deform. The multiple blade shell segments (1.22) and the blade shell of the fixed part (1.1) together constitute the airfoil of the blade (1).

[0038] A blade shell segment (1.22) supported by a basic column (1.24) is either two independent structures belonging to the two surfaces of the blade (1), i.e., two independent blade shell segments (1.22), or a complete structure that can simultaneously take into account the two surfaces of the blade (1), i.e., one blade shell segment (1.22) simultaneously takes into account the two surfaces of the blade (1).

[0039] like Figure 3 and Figure 12 As shown, in this embodiment, the blade shell segment (1.22) supported by the support member (1.2113) in a basic column (1.24) has two segments, which belong to the two airfoils of the blade (1). Figure 12As shown, starting from the middle of the blade (1) to the trailing edge (1.201), covering the entire swing section (1.2), multiple support members (1.2113) jointly fit a portion of the airfoil of the blade (1). In other words, in this embodiment, segmenting and fitting a portion of the airfoil of the blade (1) constitutes multiple line segments. By assigning appropriate thicknesses to these line segments, the cross-section of the blade shell segment (1.22) can be obtained. The thickness of the blade shell segment (1.22) is mainly determined by the load-bearing requirements of the blade shell. If it is too thin, it cannot meet the load-bearing requirements; if it is too thick, it will increase the weight of the blade (1).

[0040] The blade shell segments (1.22) are fixed to the support surface, for example, by riveting. In this embodiment, multiple blade shell segments (1.22) are stacked sequentially along the chord (3) direction of the blade. Figure 13 As shown, starting from the middle of the blade (1) to the trailing edge (1.201), covering the entire oscillating portion (1.2), the portion of each blade shell segment (1.22) near the trailing edge (1.201) of the blade covers the portion of the adjacent blade shell segment (1.22) near the leading edge (1.101) of the blade. The stacking arrangement of the blade shell segments (1.22) provided in this embodiment is not the only solution. In other embodiments, other blade shell segment (1.22) arrangements can be established based on the chord length of the blade (1), the required pitch angle compensation, and the required blade deformation.

[0041] like Figure 14 As shown, when a blade shell segment (1.22) supported by a basic column (1.24) is a complete structure (i.e., when there is only one complete blade shell segment (1.22)), the blade shell segment (1.22) consists of two airfoil segments (1.221) and one curved segment (1.222). The curved segment (1.222) is located near the leading edge (1.101) of the blade, and its surface is part of a cylinder. Based on this configuration, when relative rotation occurs between the basic columns (1.24), the end of the airfoil segment (1.221) of the blade shell segment (1.22) moves relative to the surface of the curved segment (1.222) of the adjacent blade shell segment (1.22), and there is no interference between the blade shell segments (1.22).

[0042] Similar to the case of the pin (1.212), the blade shell segment (1.22) can be an integral structure or a segmented structure along the span of the blade (1). When the length of the blade (1) increases, the length of the basic blade shell segment (1.22) may not be sufficient, and multiple parts are needed to form a blade shell segment (1.22) to cover the surface of the blade (1).

[0043] The novelty and advantages of the above technical solution are: a) A link matrix is ​​formed by multiple link units (1.211) and pins (1.212) to support the blade shell, minimizing the unsupported voids below the blade shell, ensuring the load-bearing capacity of the blade shell under wind pressure, and avoiding damage to starting performance due to airfoil deformation. At the same time, the special arrangement of multiple pins (1.212) and multiple basic rows (1.23) in the link matrix enables the deformation of the rear support structure (1.21) of the blade (1). This achieves a change in aerodynamic shape and optimizes aerodynamic performance.

[0044] b) The link matrix structure contains multiple link units (1.211) that are structurally very similar. Therefore, in terms of manufacturing, the same molds, tooling, and processes can be used to mass-produce parts such as links (1.2111) and sleeves (1.2112). Furthermore, these parts are made of simple profiles, which are readily available and inexpensive.

[0045] c) Multiple blade shell segments (1.22) together constitute the shell of the blade (1), which can fit the aerodynamic shape of the blade (1). The blade shell segments (1.22) themselves do not need to be subjected to tensile or contractile deformation, and there is no fatigue problem. It realizes the function of changing the aerodynamic shape of the blade (1) while avoiding the use of expensive materials. Each blade shell segment (1.22) is made of rigid material (such as thin stainless steel plate), which is extremely low in cost and simple to process and manufacture.

[0046] d) The blade (1) deforms under wind pressure and can deform appropriately in any direction, providing appropriate pitch angle compensation. The whole process is completed autonomously and passively. There is no drive mechanism inside the blade (1), the structure is reliable, there are no high-risk components or overly complex system components, and the entire blade (1) exhibits high reliability.

[0047] e) This type of swivel blade changes its aerodynamic shape, thereby altering the position of the blade's chord (3) and ultimately changing the pitch angle. This is completely different from the existing method of using a relatively complex pitch system to drive the entire blade (1) to rotate around the pitch axis. Based on the technical solution provided in this paper, an active deformable blade can be derived, with a drive mechanism (such as a hydraulic actuator) installed inside the blade, which is expected to replace the traditional pitch system.

[0048] In the description of this invention, it should be noted that the terms "up," "down," "front," "back," "left," and "right," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and 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. Therefore, they should not be construed as limitations on this invention.

[0049] Unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" in this invention should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; similarly, they can refer to mechanical connections, electrical connections, or direct connections, or indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0050] Although the invention has been described with reference to preferred embodiments, various modifications can be made and components can be replaced with equivalents without departing from the scope of the invention. In particular, the technical features mentioned in the various embodiments can be combined in any manner as long as there is no structural conflict. The invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A tail-swinging blade, characterized in that, The blade (1) is divided into a fixed part (1.1) and a swinging part (1.2). The fixed part (1.1) extends from the leading edge (1.101) to the middle of the blade (1), and the remaining part is the swinging part (1.2). The fixed part (1.1) and the swinging part (1.2) are connected. The swinging part (1.2) is mainly composed of a rear support structure (1.21) and blade shell segments (1.22). The rear support structure (1.21) is composed of a link matrix established by multiple link units and multiple pins (1.212). Each link unit (1.211) includes two identical connectors (1.2111), at least two identical sleeves (1.2112) and a support (1.2113). Two connecting members (1.2111) are arranged in parallel, and the connecting members (1.2111) are connected by two sleeves (1.2112); the support member (1.2113) is used to support the blade shell segment (1.22); the support member (1.2113) and the connecting member (1.2111) are separate structures and are fixedly connected together, or the support member (1.2113) and the connecting member (1.2111) form an integral structure; multiple pins (1.212) are arranged at intervals along the chord (3) direction of the blade, and the sleeves (1.2112) of multiple link units (1.211) are sequentially inserted into the pins (1.212); a group of multiple link units (1.211) arranged along the chord (3) direction of the blade is the basic row (1.23) of the link matrix. Two adjacent basic rows (1.23) are incorporated into each other along the span of the blade (1) in a basic row (1.23), and each link (1.2111) in each basic row (1.23) simultaneously abuts against two adjacent links (1.2111) in the adjacent basic row (1.23), forming a link structure; the basic row (1.23) is arranged from one end of the blade (1) to the other end along the span of the blade (1); along the span of the blade (1), multiple link units (1.211) located in the same column form the basic column (1.24) of the link matrix; multiple supports (1.2113) in the basic column (1.24) jointly support the blade shell segment (1.22). The blade shell segment (1.22) supported by one of the basic columns (1.24) is either a separate structure belonging to the two surfaces of the blade (1) or a complete structure that can simultaneously accommodate the two surfaces of the blade (1); when the blade shell segment (1.22) supported by one of the basic columns (1.24) is a complete structure, the blade shell segment (1.22) is...22) The blade (1) is composed of two airfoil sections and one curved section; the multiple blade shell segments (1.22) and the blade shell of the fixed part (1.1) together constitute the airfoil of the blade (1).

2. The tail-swinging blade according to claim 1, characterized in that, The connector (1.2111) is provided with two spaced circular holes (1.2114), the diameter of which is the same as the outer diameter of the end of the sleeve (1.2112).

3. A tail-swinging blade according to claim 2, characterized in that, The connector (1.2111) is interference-fitted to the end of the sleeve (1.2112) through a round hole (1.2114).

4. A tail-swinging blade according to claim 1, characterized in that, When the support member (1.2113) and the link member (1.2111) are separate structures, the two ends of the support member (1.2113) along the span of the blade (1) are respectively fixedly connected to the two links (1.2111) of the same link unit (1.211).

5. A tail-swinging blade according to claim 1, characterized in that, The pin (1.212) runs through all the basic rows (1.23), and the pin (1.212) adopts an integral structure or a segmented structure.

6. A tail-swinging blade according to claim 1, characterized in that, When the blade shell segment (1.22) supported by one of the basic columns (1.24) is a complete structure, the curved segment is located on the side near the leading edge (1.101) of the blade.

7. A tail-swinging blade according to claim 1, characterized in that, When the blade housing segment (1.22) supported by one of the basic columns (1.24) is a complete structure, the surface of the curved segment is part of a cylindrical surface.

8. A tail-swinging blade according to claim 1, characterized in that, From the middle of the blade (1) to the trailing edge (1.201) of the blade, the support surfaces of the multiple supports (1.2113) in the link unit (1.211) of each basic row (1.23) are fitted with the airfoil configuration of the blade (1).

9. An impeller for a wind turbine generator, characterized in that, Including the tail-swinging blade as described in any one of claims 1-8.

10. A wind turbine generator set, characterized in that, Including the impeller of a wind turbine as described in claim 9.

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