Vibration suppression device, blade assembly and wind generating set

Abstract

The invention relates to a vibration suppression device, a blade assembly and a wind generating set, the vibration suppression device is used for a blade body, the vibration suppression device comprises a restraining assembly, the restraining assembly comprises a first restraining piece and a second restraining piece which are distributed in a spaced mode, and the first restraining piece and the second restraining piece can be arranged on the blade body in a sleeving mode and are fixed relative to the blade body; the vibration suppression assembly is arranged between the first restraining piece and the second restraining piece, and the vibration suppression assembly extends along the spiral path so as to be spirally wound around the blade body; the vibration suppression assembly comprises a turbulent flow unit extending along a spiral path, the turbulent flow unit comprises a spiral matching surface, and the spiral matching surface is used for being attached to the outer surface of the blade body. Vibration response of incoming wind can be reduced, the vibration suppression effect is good, swing of the blade body under the action of the incoming wind is reduced, and safety of the blade body under different working conditions is guaranteed.

Description

Technical Field

[0001] This application relates to the field of wind power technology, and in particular to a vibration damping device, blade assembly, and wind turbine generator set. Background Technology

[0002] As wind turbines rapidly develop towards larger capacity, taller towers, and longer blades, the length of a single blade has exceeded 100 meters, significantly increasing structural flexibility. During various stages, including stacking, hoisting, and no-load operation before grid connection, the blade body is subjected to complex flow field environments, making it highly susceptible to unsteady aerodynamic forces and resulting in structural vibration. This type of vibration mainly manifests as vortex-induced vibration (VIV) and stall-induced vibration (SIV), both typical fluid-induced vibration problems.

[0003] Both types of vibration exhibit fluid-structure coupled dynamics characteristics: the interaction of incoming flow conditions, blade modal characteristics, and damping levels results in significant uncertainty and danger in the vibration response. For ultra-long flexible blades, the blade body may experience significant swaying during on-site operations under the influence of incoming wind, seriously threatening the safety of the blade body under various working conditions such as stacking, hoisting, and grid connection. Summary of the Invention

[0004] One embodiment of this application provides a vibration damping device, a blade assembly, and a wind turbine generator set. The vibration damping device can reduce the vibration response of the incoming wind, has a good vibration damping effect, reduces the swaying of the blade body under the action of the incoming wind, and ensures the safety of the blade body under different operating conditions.

[0005] On one hand, according to one embodiment of this application, a vibration damping device is proposed for a blade body. The vibration damping device includes: a constraint assembly, including a first constraint member and a second constraint member spaced apart, the first constraint member and the second constraint member being able to be sleeved on the blade body and fixed relative to the blade body; a vibration damping component, disposed between the first constraint member and the second constraint member, the vibration damping component extending along a helical path and spirally wound around the blade body; wherein, the vibration damping component includes a turbulence unit extending along the helical path, the turbulence unit including a helical mating surface, the helical mating surface being used to fit against the outer surface of the blade body.

[0006] According to one aspect of the embodiments of this application, the distance from one end of the turbulence unit away from the helical mating surface to the helical mating surface is h, which is perpendicular to the helical direction of the vibration damping component, and the width of the turbulence unit is b, where 0.8≤b / h≤2.5.

[0007] According to one aspect of the embodiments of this application, the vibration damping device further includes a flexible rope that matches the extension path of the turbulence unit and is embedded in the turbulence unit configuration.

[0008] According to one aspect of the embodiments of this application, the turbulence unit is a strip-shaped structure extending along the spiral path, and its cross-sectional shape perpendicular to its own extension direction is polygonal.

[0009] According to one aspect of an embodiment of this application, the polygon has n sides, where 3 ≤ n ≤ 6. And / or, the turbulence unit includes a foamed material.

[0010] According to one aspect of the embodiments of this application, the turbulence unit includes a sharp corner portion disposed opposite to the helical mating surface, and the included angle θ of the sharp corner portion ranges from 60° to 90°.

[0011] According to one aspect of the embodiments of this application, the ratio k / δ of the characteristic height of the turbulence element to the local boundary layer thickness is preferably in the range of 0.3 to 0.7.

[0012] According to one aspect of the embodiments of this application, the vibration damping component further includes a flexible connection unit, and the number of turbulence units is multiple, with a flexible connection unit connecting adjacent turbulence units.

[0013] According to one aspect of the embodiments of this application, the flexible connection unit includes an elastic rope, a flexible sleeve, or a flexible connection belt.

[0014] According to one aspect of the embodiments of this application, the pitch of the plurality of turbulence-disrupting units as a whole is a fixed pitch along the helical direction of the vibration damping assembly. Alternatively, the pitch of the plurality of turbulence-disrupting units as a whole has an increasing trend, which includes one of the following: gradually increasing, increasing segment by segment, first remaining fixed and then gradually increasing, or first remaining fixed and then increasing segment by segment.

[0015] According to one aspect of the embodiments of this application, the vibration damping device further includes a distance fixing component, which is only partially disposed between the first constraint member and the second constraint member. Along the arrangement direction of the first constraint member and the second constraint member, the distance fixing component includes a plurality of spaced limiting parts, and the turbulence unit is sequentially engaged with each limiting part. The distance fixing component is used to engage with the trailing edge of the blade body and fix the relative position of the blade body.

[0016] According to one aspect of the embodiments of this application, along the arrangement direction, the spacing component includes a plurality of spacing units distributed at intervals and a connecting portion connected between two adjacent spacing units, and each spacing unit is provided with a limiting portion.

[0017] According to one aspect of the embodiments of this application, the first constraint member has a ring-shaped structure and is used to be sleeved on the tip of the blade body.

[0018] According to one aspect of the embodiments of this application, the first constraint member includes an annular body and a buffer layer disposed inside the annular body, the buffer layer being configured to contact the blade body.

[0019] According to one aspect of the embodiments of this application, the second constraint member has a ring-shaped structure and is used to be sleeved on the side of the blade body away from the blade tip. The second constraint member is uncoilably oriented in its ring direction.

[0020] According to one aspect of the embodiments of this application, the vibration damping device further includes an unlocking component, which includes a fixing member and a disconnection assembly disposed on the fixing member. The second constraint member is provided with the unlocking component, the fixing member is connected to the second constraint member, and the disconnection assembly is used to disconnect the second constraint member.

[0021] According to one aspect of the embodiments of this application, the disconnect assembly includes a power supply, a switch and a heating element arranged in series, the heating element being connected to a second constraint member to heat and melt the second constraint member; Alternatively, the disconnect assembly includes a drive unit and a cutter, the drive unit drives the cutter to move, and a portion of the second constraint is located on the movement path of the cutter to cut the second constraint by the cutter.

[0022] According to one aspect of the embodiments of this application, the number of disconnect assemblies is two or more, and the two or more disconnect assemblies are all disposed on the fixing member.

[0023] In another aspect, according to an embodiment of this application, a blade assembly is provided, including a blade body; as described above, the vibration damping device includes a first constraint member and a second constraint member sleeved on the blade body and fixed relative to the blade body, and the vibration damping assembly extends along a spiral path and spirally wound around the blade body.

[0024] According to another aspect of the embodiments of this application, the length of the blade body is L1, and the length of the vibration damping device on the blade body is L2, wherein 25%≤L2 / L1≤50%.

[0025] In another aspect, an embodiment of this application provides a wind turbine generator set, including the blade assembly described above.

[0026] An embodiment of the present invention provides a vibration damping device, a blade assembly, and a wind turbine generator. The vibration damping device uses first and second constraint members to sleeve the blade body and fix its relative position, providing a stable installation foundation for the vibration damping assembly connected between the two, ensuring that the vibration damping assembly can reliably spirally wind around the blade body. Because the vibration damping assembly includes a turbulence unit extending along a spiral path and has a spiral mating surface that fits against the outer surface of the blade, the spiral winding shape alters the aerodynamic shape of the blade body under different operating conditions such as stacking, hoisting, and grid connection. The overall aerodynamic effect still manifests as a disturbance boundary condition continuing along the spanwise direction. The continuous disturbance structure of the spirally wound turbulence unit can continuously introduce shear layer disturbances and spanwise vortex structures over a larger range, effectively weakening the coherence length of the Karman vortex street in the spanwise direction, thereby disrupting the basic conditions for vortex-induced frequency locking at the system level. This allows the vibration damping device to reduce the vibration response of the incoming wind, achieving good vibration damping effect, reducing the swaying of the blade body under the action of the incoming wind, and ensuring the safety of the blade body under different operating conditions. Attached Figure Description

[0027] The features, advantages, and technical effects of exemplary embodiments of this application will now be described with reference to the accompanying drawings.

[0028] Figure 1 This is a schematic diagram of the interaction between a vibration damping device and a blade according to one embodiment of this application; Figure 2 yes Figure 1 A cross-sectional view along the AA direction; Figure 3 This is a schematic diagram of the cross-sectional structure of the turbulence unit in another embodiment of this application, perpendicular to its own extension direction; Figure 4 This is a schematic diagram comparing the vibration response curves of a vibration suppression device provided in one embodiment of this application with different blade vibration suppression schemes in the prior art within the frequency lock band. Figure 5 This is a schematic diagram comparing the vibration energy levels of a vibration suppression device provided in one embodiment of this application with different blade vibration suppression schemes in the prior art within the frequency lock band; Figure 6 This is a schematic diagram of the cross-sectional structure of the turbulence unit and flexible rope in the helical direction according to another embodiment of this application; Figure 7 This is a schematic diagram of the structure of a distance-fixing component according to an embodiment of this application; Figure 8 yes Figure 7 A cross-sectional view along the BB direction; Figure 9 This is a schematic diagram illustrating the cooperation between the unlocking component and the second constraint member according to one embodiment of this application; Figure 10This is a schematic diagram of the cooperation between the unlocking device and the second constraint member according to another embodiment of this application.

[0029] Marker explanation: 100. Vibration damping device; 10. Constraint assembly; 11. First constraint element; 12. Second constraint element; 20. Vibration damping components; 21. Turbulence unit; 211. Helical mating surface; 212. Sharp corner; 22. Flexible connection unit; 30. Flexible rope; 40. Distance fixing component; 41. Distance fixing unit; 411. Limiting part; 412. U-shaped groove; 42. Connecting part; 50. Unlock components; 51. Fasteners; 52. Disconnect assembly; 521. Power supply; 522. Switch; 523. Heating element; 524. Drive element; 525. Cutter; 200. Blade body.

[0030] In the accompanying drawings, the same parts use the same reference numerals. The drawings are not drawn to scale. Detailed Implementation

[0031] The features and exemplary embodiments of various aspects of this application will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a comprehensive understanding of this application. However, it will be apparent to those skilled in the art that this application can be implemented without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of this application by illustrating examples. In the accompanying drawings and the following description, at least some well-known structures and techniques are not shown to avoid unnecessarily obscuring the application; and, for clarity, the dimensions of some structures may be exaggerated. Furthermore, the features, structures, or characteristics described below can be combined in any suitable manner in one or more embodiments.

[0032] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the vibration damping device, blade assembly, or wind turbine generator set of this application. It should also be noted in the description of this application that, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0033] As wind turbines rapidly develop towards larger capacity, taller towers, and longer blades, the length of a single blade has exceeded 100 meters, significantly increasing structural flexibility. During various stages, including stacking, hoisting, and no-load operation before grid connection, the blades are exposed to complex flow field environments, making them highly susceptible to unsteady aerodynamic forces and resulting in structural vibrations. These vibrations primarily manifest as vortex-induced vibration (VIV) and stall-induced vibration (SIV), both typical fluid-induced vibration problems.

[0034] Within a certain wind speed range, when turbulence passes over the blade cross-section, vortex structures periodically detach in the wake region. When the vortex shedding frequency is close to the blade's natural frequency, aerodynamic frequency locking is easily triggered, leading to vortex-induced vibration. For long, flexible blades, the lower natural frequency and higher aerodynamic sensitivity significantly increase the risk of VIV (Volatile Induced Vibration). On the other hand, when the blade is stationary or at a high angle of attack, the surface boundary layer separation range expands, forming unsteady stall vortices, which may induce stall-induced vibration. This is characterized by low frequency and large amplitude motion, often occurring under conditions such as stacking, interrupted hoisting, or unloaded rotation.

[0035] Both types of vibration exhibit fluid-structure coupled dynamics characteristics: the interaction of inflow conditions, blade modal characteristics, and damping levels results in significant uncertainty and danger in the vibration response. For ultra-long flexible blades, this can not only cause structural risks such as material fatigue accumulation and bond interface damage, but also lead to large-scale swaying during on-site operations, seriously threatening hoisting and construction safety.

[0036] To suppress vortex-induced vibration (VIV) and stall-induced vibration (SIV) that may occur in long flexible blades under different operating conditions such as storage, transportation, hoisting, and before grid connection, the industry has proposed several solutions. For example, blade vibration suppression schemes employ discrete disturbance components, such as covering the blade with a mesh and setting localized blocky protrusions on its surface, or connecting several spherical components in a "necklace" arrangement using ropes. These schemes are considered localized point or blocky disturbance sources in fluid dynamics, with the disturbance mainly concentrated near a single discrete component, forming localized separated bubbles, wake vortices, or additional vortex systems under the influence of the incoming flow. Due to the insufficient continuity of the disturbance along the blade spanwise, its destructive effect on vortex shedding coherent structures is clearly localized and intermittent.

[0037] Meanwhile, stall-induced vibration typically occurs at high angles of attack or at low speeds when the blades are stationary. It is characterized by extensive boundary layer separation, unsteady development of stall vortices, and low-frequency, large-amplitude vibration responses. Discrete turbulence components in such flow fields primarily increase local drag or dissipate energy. Their effect is often after separation, and their suppression of stall vortices is a reactive effect. Furthermore, under certain operating conditions, they may introduce additional pulsating loads or localized slapping effects, impacting the vibration suppression performance.

[0038] like Figures 1 to 3 As shown, based on this, one embodiment of this application provides a vibration damping device 100, which can reduce the vibration response of the incoming airflow, has a good vibration damping effect, reduces the swaying of the blade body 200 under the action of the incoming airflow, and ensures the safety of the blade body 200 under different working conditions such as hoisting and construction, and has good versatility.

[0039] One embodiment of this application provides a vibration damping device 100 for a blade body 200. The vibration damping device 100 includes a constraint component 10 and a vibration damping component 20. The constraint component 10 includes a first constraint member 11 and a second constraint member 12 spaced apart. The first constraint member 11 and the second constraint member 12 can be sleeved on the blade body 200 and fixed relative to the blade body 200. The vibration damping component 20 is connected between the first constraint member 11 and the second constraint member 12. The vibration damping component 20 extends along a helical path and is helically wound around the blade body 200. The vibration damping component 20 includes a turbulence-disrupting unit 21 extending along the helical path. The turbulence-disrupting unit 21 includes a helical mating surface 211, which is used to fit against the outer surface of the blade body 200.

[0040] The first constraint member 11 and the second constraint member 12 of the constraint assembly 10 can be used to fit the blade body 200 and achieve relative fixation. The first and second constraint members 12 are distributed at intervals and can be used to provide mounting points on both sides of the vibration damping assembly 20 to ensure that the vibration damping assembly 20 can be stably spirally wound around the blade.

[0041] The first constraint member 11 and the second constraint member 12 may respectively include a ring structure formed by a flexible strip enclosure, or a ring structure with a certain elastic deformation capability. Of course, the first constraint member 11 may also adopt a rigid strip structure, etc.

[0042] The first constraint member 11 and the second constraint member 12 can be either a single ring structure or formed by connecting multiple constraint segments, for example, by bonding or connecting with connectors.

[0043] The vibration damping component 20 can be disposed between the first constraint member 11 and the second constraint member 12 and connected to the first constraint member 11 and the second constraint member 12 respectively.

[0044] The vibration damping component 20 may include one or more turbulence units 21. When it includes two or more, the two or more turbulence units 21 may be arranged sequentially between the first constraint member 11 and the second constraint member 12. Adjacent turbulence units 21 may be connected directly or indirectly to each other through other connection structures.

[0045] Extending along the spiral path, the spiral is wound around the blade body 200: the spiral path can be centered on the axis of the blade body 200, and the vibration damping component 20 extends along this path to fit the outer surface of the blade to form a spiral winding state. During the winding process, the spiral mating surface 211 of the turbulence unit 21 is always in contact with the blade surface and can be connected to the blade body 200 by means of bonding or other methods.

[0046] Optionally, the turbulence unit 21 is a continuous structure extending along a spiral path, and can be a continuous strip structure.

[0047] Optionally, the turbulence unit 21 is a structure with turbulence characteristics. Optionally, the cross-sectional shape of the turbulence unit 21 in the spiral direction or in the cross-sectional shape of the turbulence unit 21 perpendicular to its own extension direction includes at least one or more abrupt edges, ridges, and curvature abrupt regions.

[0048] An edge can be understood as a geometric angle formed by the intersection of two planes or curved surfaces, which can cause the boundary layer to separate prematurely under the influence of the incoming flow. The fluid action mechanism is: forced early separation of the boundary layer to form a stable shear layer.

[0049] Ridges can be understood as linear protrusions or broken lines on the surface, used to guide the deflection of the shear layer and induce spanwise perturbations.

[0050] A curvature abrupt change region can be understood as a region where curvature changes within a local range but remains geometrically continuous, used to trigger unsteady separation and reattachment processes.

[0051] Optionally, the cross-sectional shape of the turbulence unit 21 in the spiral direction, or the cross-sectional shape of the turbulence unit 21 perpendicular to its own extension direction, can be a regular polygon. Of course, it is not limited to a regular polygon; it can also be a circular, elliptical, or quasi-spherical structure. Optionally, the cross-sectional shape can be provided with at least one of the following: edges, ridges, and regions with abrupt changes in local curvature. This is beneficial for forming discontinuous shear layer disturbances, thereby disrupting the coherence of the incoming vortex.

[0052] An embodiment of the present invention provides a vibration damping device 100, which uses first and second constraint members 12 to sleeve the blade body 200 and fix their relative positions, providing a stable installation base for the vibration damping component 20 connected between the two, and ensuring that the vibration damping component 20 can be reliably spirally wound around the blade body 200.

[0053] Because the vibration damping component 20 includes a turbulence unit 21 extending along a helical path and has a helical mating surface 211 that fits against the outer surface of the blade, the helical winding shape of the vibration damping device 100 changes the aerodynamic shape of the blade body 200 under different operating conditions such as stacking, hoisting, and grid connection. The overall aerodynamic effect still manifests as a disturbance boundary condition that continues along the spanwise direction. Its continuous disturbance structure along the helical path can continuously introduce shear layer disturbances and spanwise vortex structures over a larger range, effectively weakening the coherence length of the Karman vortex street in the spanwise direction, thereby destroying the basic conditions for vortex-induced frequency locking at the system level. Compared with related technologies, the two belong to two different technical routes in terms of disturbance mode: "discrete point disturbance" and "continuous disturbance band".

[0054] Furthermore, by spirally winding the turbulence units, the turbulence characteristics exhibit multi-scale spatial modulation along the blade span. This allows for pre-modulation of the boundary layer separation point location, shear layer stability, and the formation process of stall vortices. By weakening the coherent development of large-scale stall vortices, the probability of low-frequency large-amplitude responses is reduced from the source, resulting in a more stable and predictable vibration suppression effect under stall-induced vibration conditions, reducing vibration response, and decreasing the sway of the blade body 200 under the influence of incoming wind.

[0055] To better illustrate the advantages of the vibration damping device 100 claimed in this application, the following will be combined with Figure 4 as well as Figure 5 By comparing with different vibration suppression schemes in the prior art, such as those without vibration suppression devices on the blades and the schemes disclosed in the prior art or related technologies mentioned above, namely the schemes that use discrete turbulence components, the advantages of the vibration suppression device 100 provided in this application can be further demonstrated by comparing the vibration response and vibration energy level in the frequency-locked band.

[0056] See Figure 4 It is evident that, compared to unturbulent flow and existing discrete turbulence schemes, the helical turbulence unit employed in this application significantly reduces the vibration response peak within the normalized incoming wind speed range and effectively compresses or even eliminates the typical vortex-induced vibration frequency-locking region. This difference indicates that the helical turbulence structure can generate phase-continuous aerodynamic disturbances in the spanwise direction, thereby disrupting the coherence of the vortex street mechanism, while discrete turbulence units only generate disturbances locally, making it difficult to effectively suppress the full spanwise frequency-locking behavior.

[0057] Also see Figure 5 As can be seen from the figure, the normalized vibration energy values ​​in the frequency-locked band are used to reflect the weakening trend of vibration energy in the vortex-induced frequency-locked band by different vibration suppression schemes. The condition without a vibration suppression device is used as the normalization benchmark. Existing publicly available schemes, i.e., discrete turbulence devices, can reduce the frequency-locked energy to some extent because they only disturb the local flow field, but frequency-locked coherence still exists, and their normalized energy level is usually in the range of 0.6 to 0.7. The helical turbulence unit used in this application, by continuously disrupting the vortex shedding phase in the spanwise direction, makes it difficult to establish frequency-locked conditions, thereby significantly reducing the vibration energy in the frequency-locked band, and its normalized level can be reduced to the range of 0.2 to 0.4.

[0058] It should be noted that the values ​​in the figure are schematic normalized results used to illustrate the relative differences in energy levels among different turbulence mechanisms, and do not constitute a limitation on specific numerical performance. Vibration energy is defined as the integral value of the power spectrum of the vibration response within the vortex-induced frequency lock main frequency band, and normalized with the unsuppressed vibration condition as the benchmark.

[0059] According to one aspect of the embodiments of this application, the distance from one end of the turbulence unit 21 away from the helical mating surface 211 to the helical mating surface 211 is h, which is perpendicular to the helical direction of the vibration damping component, and the width of the turbulence unit 21 is b, where 0.8≤b / h≤2.5.

[0060] The height h of the end of the turbulence unit 21 away from the helical mating surface 211 can be understood as: the maximum height of the cross section of the turbulence unit 21 along the normal direction of the blade body 200, that is, the vertical distance from the baseline of the blade body 200 surface to the farthest point of the turbulence unit 21.

[0061] The width b of the turbulence unit 21 can be understood as the width of the contact portion between the turbulence unit 21 and the surface of the blade body 200, that is, the dimension of the helical mating surface 211 along the spanwise direction.

[0062] like Figure 2 As shown, exemplarily, when the cross-sectional shape of the turbulence unit 21 in the spiral direction is triangular, the width b of the turbulence unit 21 can be understood as the width of the base of the triangle, i.e., the side that contacts the blade body 200, and h can be understood as the vertical distance from the vertex to the base.

[0063] like Figure 3 As shown, exemplarily, when the cross-sectional shape of the turbulence unit 21 in the spiral direction is quadrilateral, such as trapezoid, the width b of the turbulence unit 21 can be understood as the width of the lower base of the trapezoid, that is, the width of the side that contacts the blade body 200, and h can be understood as the vertical distance between the upper base and the lower base. Optionally, the width of the upper base is smaller than the width of the lower base.

[0064] In one embodiment of this application, the vibration suppression device uses the ratio b / h of the width b of the turbulence unit 21 to its characteristic height h to affect the turbulence effectiveness, aerodynamic side effects, and structural fit stability. If b / h is less than 0.8, the lateral dimension of the turbulence unit 21 is insufficient, resulting in a small and rapidly decaying shear layer disturbance energy, making it difficult to continuously disrupt the coherence of the wake vortex street, and the vibration suppression effect is unstable. If b / h exceeds 2.5, the excessively large lateral dimension can easily lead to an earlier separation point and an expanded recirculation zone, significantly increasing additional resistance and local pressure pulsation, and increasing the load requirements on the end-constraint and pre-tightening winding system, which is detrimental to reliability. Therefore, a range of 0.8 ≤ b / h ≤ 2.5 is selected. Further, a range of 1.0 ≤ b / h ≤ 2.0 is selected, so that the turbulence unit 21 can generate stable and sufficient shear layer disturbance to suppress frequency locking, while maintaining a good fit span and anti-overturning stability, reducing the risk of warping, slippage, and local stress concentration, while also taking into account the load-bearing requirements of the embedded rope structure and the feasibility of on-site spiral winding construction.

[0065] like Figure 6 As shown, according to one aspect of an embodiment of this application, the vibration damping device 100 further includes a flexible rope 30, which is matched with the extension path of the turbulence unit 21 and embedded in the turbulence unit 21.

[0066] The flexible rope 30 includes, but is not limited to, at least one of fiber rope, nylon rope, aramid rope or carbon fiber composite rope.

[0067] Matching the extension path of the flexible rope 30 with that of the turbulence unit 21 can be understood as follows: the flexible rope 30 is also spirally extended along the spiral path of the vibration damping device. The lengths of the flexible rope 30 and the turbulence unit 21 can be equal, or one can be longer than the other.

[0068] The number of flexible ropes 30 can be equal to the number of turbulence units 21 and set in a one-to-one manner. When there are two or more flexible ropes 30, adjacent flexible ropes 30 can be directly connected, or they can be indirectly connected to each other through other connection structures.

[0069] Discrete turbulence schemes in related technologies often rely on netting, binding, or suspension to connect with the blades. Discrete components may sway, slap, wear, or loosen under the coupled effects of wind-induced loads and blade vibrations, causing relative motion between the turbulence components and the blades. This leads to changes in aerodynamic disturbance boundary conditions over time, and may even introduce secondary excitation. However, an embodiment of this application provides a vibration suppression device that embeds a flexible rope 30 at the bottom edge of the turbulence unit 21 and installs it using a spiral winding pre-tightening method. This allows the flexible rope 30 to form a continuous force-bearing skeleton, effectively transferring and superimposing the pre-tightening force of each turn of the turbulence unit 21 into an effective normal clamping force Neff, significantly improving the interface friction bearing capacity and anti-slip margin.

[0070] Regarding structural stability, the anti-slip condition of the vibration damping device can be characterized by μNeff ≥ Fdrive, where Fdrive is the resultant force of the tangential component of the wind load and the equivalent force of vibration inertia; the anti-peeling condition can be characterized by Mres ≥ Mlift, where Mlift is the local lifting moment and Mres is the anti-lifting moment formed by the bottom edge and the rope frame. Through the above structural design, this application can maintain reliable adhesion and connection strength between the vibration damping device and the blade surface under strong wind and vibration coupling conditions, significantly improving operational stability and durability.

[0071] Meanwhile, the vibration damping device provided in one embodiment of this application can improve the overall reliability of the vibration damping device by setting a flexible rope 30. On the one hand, the flexible rope 30 serves as a load-bearing frame, improving the overall connection strength of the vibration damping device under wind-induced loads and vibrations; on the other hand, it provides flexible buffering capacity, reducing local stress concentration, allowing limited deformation compensation under gusts or large vibrations, reducing the risk of stress concentration and detachment caused by overall excessive rigidity, avoiding cracking or detachment of the turbulence unit 21 due to repeated vibrations, and ensuring the safety of the blade body 200 under different working conditions such as stacking, hoisting, and grid connection.

[0072] In some alternative embodiments, the vibration damping device provided in one embodiment of this application has a turbulence-disrupting unit 21 in the form of a strip-shaped structure extending along a spiral path. The cross-sectional shape of the turbulence-disrupting unit in the spiral direction is polygonal.

[0073] like Figure 2 as well as Figure 3 As shown, optionally, the cross-sectional shape of the turbulence unit 21 perpendicular to its own extension direction can be triangular, quadrilateral or more polygonal.

[0074] The polygonal cross-section ensures that the turbulence unit 21 has multiple windward surfaces, thereby effectively disrupting the incoming airflow and breaking the periodic formation of the vortex structure. The number of sides and the side length of the polygon can be flexibly designed according to the vibration suppression requirements.

[0075] It is understandable that in a polygon, each edge can be a straight edge, or at least some edges can be curved surfaces. The polygon can be understood as the disturbance unit 21 being a strip-shaped polyhedral structure wound along a spiral path around the blade body 200. Each surface can be planar or curved, etc. In specific implementation, for each disturbance unit 21, a strip with a polygonal cross-section along its own length can be taken. This strip is spirally wound around the blade body along the corresponding spiral path of the vibration damping component. The cross-section uses a polygonal structure with a triangular or trapezoidal base, allowing the vibration damping device to form surface contact or near-surface contact with the blade surface. This results in more uniform normal support under wind load and reduces the tendency for localized edge lifting.

[0076] Optionally, the spiral winding structure of the vibration damping component 20 can change the flow trajectory of the incoming airflow on the surface of the blade body 200, break the condition of the periodic shedding of the vortex structure, and at the same time, the spiral shape makes the airflow disturbance effect distributed along the length of the blade body 200, avoid local vibration intensification, and adapt to different incoming flow directions and wind speed conditions.

[0077] Optionally, the polygonal cross-section of the turbulence unit 21 can be used to generate multi-directional airflow disturbances under the action of the incoming wind, thereby disrupting the integrity of the vortex structure in the wake region, reducing the risk of vortex shedding frequency coupling with the blade's natural frequency, while the blade-fitting structural design ensures that the disturbance effect directly acts on the airflow field on the blade surface.

[0078] According to one aspect of the embodiments of this application, the polygon has n sides, where 3 ≤ n ≤ 6.

[0079] Optionally, the polygon can have any number of sides, from 3 to 6.

[0080] like Figure 2 as well as Figure 3 As shown, for example, the cross-section of the turbulence unit 21 can be triangular, quadrilateral (such as trapezoidal), or other polygonal cross-sections. A triangular cross-section has sharp angles in the windward direction, which can form significant shear layer disturbances and flow-directed vortex structures, breaking down the coherence of the Karman vortex and suppressing the frequency-locking effect of vortex-induced vibration. A trapezoidal cross-section controls the boundary layer separation point through obtuse angles and step effects, making it suitable for medium-inflow intensity conditions; other polygonal cross-sections (such as pentagons and hexagons) can be selected according to the aerodynamic characteristics of the blades, achieving turbulence effects in different frequency bands.

[0081] In some alternative embodiments, the turbulence unit 21 includes a foamed material.

[0082] Optionally, the turbulence unit 21 may include at least one of foamed polyethylene, foamed polypropylene, foamed polyurethane, ethylene-vinyl acetate copolymer, and rubber-based composite foam material.

[0083] One embodiment of this application provides a vibration damping device 100, in which the turbulence unit 21 includes a foamed material, ensuring that it has the characteristics of low density, easy molding and resistance to environmental aging while meeting the vibration damping requirements.

[0084] In some alternative embodiments, the turbulence unit 21 may include foamed polyethylene, which has the advantages of being lightweight, having good cushioning properties, being easy to process, and having controllable costs.

[0085] like Figure 2As shown, according to one aspect of the embodiment of this application, the turbulence unit 21 includes a sharp corner portion 212 disposed opposite to the spiral mating surface 211, and the included angle θ of the sharp corner portion 212 is in the range of 60°~90°.

[0086] The included angle of the pointed corner 212 can be any value between 60° and 90°, including both 60° and 90°.

[0087] When the pointed corner 212 is included, the cross-sectional shape of the turbulence unit 21 can be a triangle, a pentagon, or of course, other polygonal structures.

[0088] The vibration damping device provided in one embodiment of this application, through the setting of the aforementioned sharp corner 212 and the angle limitation, enables the turbulence unit 21 to both generate directional disturbance and avoid local stress concentration caused by excessively small angle.

[0089] According to one aspect of the embodiments of this application, the ratio of the characteristic height k of the turbulence unit 21 to the local boundary layer thickness δ, k / δ, ranges from 0.3 to 0.7.

[0090] The local boundary layer thickness δ can be understood as the distance at which the velocity on the local surface of the blade body 200 reaches 99% of the free flow velocity in the normal direction. δ is not a fixed value; it is a local flow characteristic scale that varies along the spanwise direction and angle of attack of the blade body 200.

[0091] Characteristic height k: can be understood as the equivalent height at which the disturbance unit 21 effectively disturbs the boundary layer and shear layer on the blade surface.

[0092] For triangular, trapezoidal and other polygonal cross-section disturbance elements 21, the characteristic height k can be understood as the cross-sectional height component that participates in the effective disturbance, which is usually less than or equal to the height h.

[0093] The value of k / δ can be any value between 0.3 and 0.7, including the two extreme values ​​of 0.3 and 0.7. Of course, the value of k / δ can also be any value between 0.4 and 0.6, and 0.5 can be selected.

[0094] One embodiment of this application provides a vibration suppression device 100. When k / δ < 0.3, the disturbance is insufficient to disrupt the stable vortex street structure, resulting in a decrease in vibration suppression effect. When k / δ > 0.7, it easily causes complete separation of the boundary layer, leading to a sharp increase in additional drag and adversely affecting the overall aerodynamic performance of the blade. By ensuring that the value of k / δ is within the range of 0.3 to 0.7, a better balance between the turbulence effect and aerodynamic performance can be achieved.

[0095] Continue reading Figure 1As shown, according to one aspect of the embodiments of this application, the vibration damping component 20 further includes a flexible connection unit 22, and the number of turbulence units 21 is multiple, with a flexible connection unit 22 connecting adjacent turbulence units 21.

[0096] The number of turbulence-disrupting units 21 can be two, three, or more. Multiple turbulence-disrupting units 21 can be distributed at intervals along the spiral path, and a flexible connecting unit 22 can be connected between two adjacent turbulence-disrupting units 21.

[0097] The flexible connection unit 22 includes an elastic material and has elastic deformation capability. The flexible connection unit 22 is used for deformation compensation of the turbulence unit 21.

[0098] Optionally, the flexible connection unit 22 includes, but is not limited to, at least one of: elastic rope, flexible sleeve and polymer connecting strip, which can maintain the overall continuity of the vibration damping device 100 and allow adjacent turbulence units 21 to generate limited relative displacement under wind load, thereby achieving deformation compensation.

[0099] The flexible connection unit 22 can be directly connected to the two adjacent turbulence units 21. For example, it can be connected by adhesive, embedded connection or anchoring.

[0100] Of course, the flexible connection unit 22 can also be indirectly connected to the two adjacent turbulence units 21. For example, when the vibration damping device 100 also includes a flexible rope 30, the flexible connection unit 22 can also be connected to the flexible rope 30 embedded in the turbulence unit 21. The flexible connection unit 22 and the flexible rope 30 can be connected and fixed by rolling, binding, or buckling.

[0101] Optionally, the flexible connection unit 22 can be extended along the spiral path for the extension trajectory of the region.

[0102] One embodiment of this application provides a vibration damping device 100. Under strong winds, the aforementioned configuration can prevent the vibration damping component 20 from cracking or becoming loose due to excessive rigidity and localized stress concentration. This is because the multi-segment flexible connection unit 22 can effectively distribute the load and reduce the risk of damage caused by sudden gusts. Furthermore, the structure of the multi-segment turbulence units 21 connected by the flexible connection unit 22 offers greater flexibility during installation and disassembly. The length and number of individual turbulence units 21 can be flexibly adjusted according to the length of the blade body 200 and specific construction conditions, thereby improving on-site adaptability and reliability. This design, while ensuring turbulence continuity, endows the vibration damping device with high wind resistance and durability, further enhancing its applicability in various scenarios involving long, flexible blades.

[0103] According to one aspect of the embodiments of this application, the flexible connection unit 22 includes an elastic rope, a flexible sleeve, or a flexible connecting belt. This arrangement maintains the overall continuity of the vibration damping device while allowing adjacent units to undergo limited relative displacement under wind load, thereby achieving deformation compensation.

[0104] According to one aspect of the embodiments of this application, the pitch of the plurality of turbulence units 21 is a fixed pitch along the helical direction of the vibration damping component.

[0105] A fixed pitch can be understood as the distance between two adjacent helical segments of each turbulence unit 21 being equal in the arrangement direction of the first constraint member 11 and the second constraint member 12. A uniform pitch is used in each helical segment. For example... Figure 1 The structure shown has d1=d2=d3.

[0106] By setting multiple turbulence units 21 with a fixed overall pitch, it is beneficial to form them in a regular winding pattern on the blade body 200, and it can meet the vibration suppression requirements.

[0107] Of course, the above-described method of using a fixed pitch is only one optional embodiment. In some embodiments, the pitch of the multiple turbulence units 21 as a whole can also increase, and the increasing trend includes one of the following: gradually increasing, increasing segment by segment, keeping it fixed first and then gradually increasing, or keeping it fixed first and then increasing segment by segment.

[0108] To facilitate understanding that the overall pitch of multiple turbulence suppression units 21 tends to increase, the following example illustrates the situation with three turbulence suppression units 21: Regarding the gradual increase: This allows the pitch of each of the three turbulence units 21 to gradually increase from one end to the other, with the minimum pitch of the later turbulence unit 21 being greater than the maximum pitch of the previous turbulence unit 21.

[0109] Regarding the gradual increase, each turbulence unit 21 can use the same pitch, with the pitch of the later turbulence unit 21 being greater than that of the earlier turbulence unit 21.

[0110] The strategy of keeping the pitch constant initially and then gradually increasing it can be achieved by keeping at least a portion of the pitch of the first turbulence unit 21 constant, while gradually increasing the pitch of the subsequent two turbulence units 21. Alternatively, the first two turbulence units 21 can have a fixed pitch, while the pitch of the last turbulence unit 21 gradually increases.

[0111] First keep it fixed and then gradually increase it: This can make at least part of the pitch of the first turbulence unit 21 remain unchanged, and in the next two turbulence units 21, the pitch of the second turbulence unit 21 is greater than the pitch of the first turbulence unit 21.

[0112] It is understood that the above is merely an illustrative example for better understanding of the vibration damping device 100 provided in one embodiment of this application, and is not limited to the above embodiment. Any embodiment can be used as long as the requirement that the pitch of the multiple turbulence units 21 as a whole increases is met.

[0113] In the region near the blade tip, due to the high aerodynamic intensity and vortex shedding frequency, a small pitch arrangement can be used to create dense disturbances in this critical area by the turbulence units 21, maximizing the disruption of frequency-locking characteristics. In the mid-span and near the blade root regions, a larger pitch can be used to balance turbulence continuity and weight control. Therefore, through the above arrangement, it is possible to adapt to the incoming flow characteristics of the blade body 200, which is beneficial to ensuring vibration suppression effect.

[0114] Continue reading Figure 1 , Figure 7 as well as Figure 8 As shown, according to one aspect of the embodiments of this application, the vibration damping device 100 further includes a distance fixing component 40. The distance fixing component 40 is at least partially disposed between the first constraint member 11 and the second constraint member 12. Along the arrangement direction of the first constraint member 11 and the second constraint member 12, the distance fixing component 40 includes a plurality of spaced limiting portions 411. The turbulence unit 21 is sequentially engaged with each limiting portion 411. The distance fixing component 40 is used to cooperate with the trailing edge of the blade body 200 and fix the relative position of the blade body 200.

[0115] The pitching component 40 can be set in the trailing edge region of the blade body 200. It is used to provide pitch constraint during the spiral winding process of the vibration damping component 20, so as to ensure that the vibration damping device 100 can maintain the predetermined pitch distribution under long-term operation and wind-induced action, thereby improving the stability and repeatability of the turbulence effect.

[0116] The distance fixing component 40 can be set independently of the first constraint member 11 and the second constraint member 12. Of course, the distance fixing component 40 can also be connected to the first constraint member 11 and the second constraint member 12.

[0117] Multiple spaced limiting parts 411 can be spaced apart between the first constraint member 11 and the second constraint member 12.

[0118] Optionally, the spacing component 40 can be made of materials with high strength, impact resistance, wear resistance, and environmental aging resistance, such as glass fiber reinforced nylon, carbon fiber reinforced composite materials, stainless steel, or aluminum alloy. For offshore wind power applications, a hybrid structure of composite materials and corrosion-resistant metals can be selected to balance strength and corrosion resistance.

[0119] The limiting part 411 may include a slot, a limiting protrusion, and other structures. The limiting part 411 cooperates with the vibration damping component that is spirally wound. Specifically, it can make the area opposite to the trailing edge of the blade body 200 during the winding process of the turbulence unit 21 be engaged with the corresponding limiting part 411.

[0120] The spacing assembly 40 and the blade body 200 can be connected and fixed by means of bonding or other methods.

[0121] In related technologies, discrete perturbation components typically have fixed geometric dimensions and spacing, and the aerodynamic disturbances they generate often correspond to response characteristics under specific scale and wind speed conditions. When wind speed, Reynolds number, or local modal frequencies of the blades change, this type of disturbance tends to exhibit a limited effective range and a significant narrow-band characteristic in disrupting frequency locking.

[0122] In one embodiment of this application, the vibration damping device 100 is used such that the spacing component 40 can be set in the trailing edge region or trailing edge position of the blade body 200 in the chord direction. The spacing component 40 can provide pitch constraints for the spiral winding of each turbulence unit 21 of the vibration damping device, ensuring that the turbulence unit 21 can maintain the predetermined pitch distribution under long-term operation and wind-induced action, thereby improving the stability and repeatability of the turbulence effect.

[0123] Simulation analysis shows that when the pitch deviation exceeds ±15%, the destructive effect of the vibration damping device on the vortex-induced vibration frequency will decrease by about 30%. After using the fixed-pitch component 40 for constraint, the pitch deviation can be controlled within ±5%, significantly improving the vibration damping stability.

[0124] Furthermore, one embodiment of the vibration suppression device 100 provided in this application allows the pitch to be designed as a fixed value, a gradually varying value, or a multi-segment combination, enabling the turbulence characteristics to exhibit multi-scale spatial modulation along the blade span. For example, a smaller pitch can be used in the blade tip region to enhance the local disturbance density, while a larger pitch can be used in the mid-span and rear sections to balance turbulence continuity and structural weight control. This spatial modulation method can create a multi-scale disturbance effect in the aerodynamic response, thereby weakening the coherence of vortex shedding over a wider range of wind speeds and frequencies, and improving the adaptability of the vibration suppression effect to changes in operating conditions.

[0125] In some alternative embodiments, the limiting portion 411 includes a groove disposed on the spacing component 40. The groove structure forcibly guides the position of each turbulence unit 21 of the vibration damping component 20, thereby preventing local bending or slippage of the long flexible blades under the coupling effect of wind load and gravity, thus maintaining pitch consistency.

[0126] According to one aspect of the present application, along the arrangement direction, the spacing component 40 includes a plurality of spacing units 41 spaced apart and a connecting portion 42 connecting two adjacent spacing units 41, and each spacing unit 41 is provided with a limiting portion 411.

[0127] The distance fixing unit 41 and the limiting part 411 can be set one-to-one, or each distance fixing unit 41 can include two or more limiting parts 411.

[0128] The connecting portion 42 between two adjacent spacing units 41 can be set independently, or the connecting portion 42 connecting each spacing unit 41 can be an integral structure. For example, the connecting portion 42 can include an integral rigid rod, and multiple spacing units 41 can be spaced and sleeved on the integral connecting portion 42.

[0129] The material of the connecting part 42 can be a rigid material, optionally including glass fiber or carbon fiber. Of course, it can also be a flexible material, such as foam material, which can be formed by molding.

[0130] In some alternative embodiments, both the distance fixing unit 41 and the connecting part 42 may include flange material, the limiting provided on the distance fixing unit 41 may include a groove, and the distance fixing unit 41 and the connecting part 42 may be an integral structure.

[0131] The vibration damping device 100 provided in one embodiment of this application adopts the above-described form for the distance fixing unit 41, which can not only ensure the distance requirement of the turbulence unit 21, but also has a simple structure and is easy to install.

[0132] In some alternative embodiments, the spacing of the spacing components 40 along the blade span can be selected as 0.5m to 4m, and the arrangement is based on the length of the blade body 200 and the coverage ratio of the vibration damping device 100. Arranging the spacing components 40 within the coverage area can ensure that the vibration damping device 100 maintains a uniform or gradually changing pitch distribution throughout its entire length.

[0133] In some alternative embodiments, the vibration damping device 100 provided in one embodiment of this application is provided with a U-shaped slot 412, which is used to match the trailing edge shape of the blade body 200 so as to be fitted onto the trailing edge of the blade.

[0134] Optionally, along the opening direction of the U-shaped slot 412 and toward the side away from the U-shaped slot 412, the cross-sectional size of the spacer unit 41 tends to decrease.

[0135] Optionally, the distance unit 41 is provided with intersecting guide surfaces at one end away from the U-shaped slot 412, and the two guide surfaces are smoothly connected on the side away from the U-shaped slot 412.

[0136] The above settings can reduce the wind resistance of the distance-fixing unit 41 on the trailing edge side.

[0137] According to one aspect of the embodiments of this application, the first constraint member 11 has a ring-shaped structure and is used to be sleeved on the tip of the blade body 200.

[0138] The first constraint member 11 is mainly used to bear wind-induced loads and maintain the stable connection of the vibration damping device at the blade tip. This device can be a fixing device, such as a mechanical fastener, an annular sleeve, or a clamping structure. The blade tip fixing device should preferably be made of high-strength metal or fiber-reinforced composite material, such as stainless steel, aluminum alloy, or carbon fiber reinforced nylon, and its inner surface can be provided with an arc-shaped contact surface that matches the surface of the blade body 200. The circumferential width of the first constraint member 11 can be selected as 8% to 15% of the chord length of the blade body 200 at the circumferential position, ensuring sufficient contact area without affecting the overall aerodynamic shape of the blade body 200.

[0139] In some alternative embodiments, the first constraint member 11 includes an annular body and a buffer layer disposed inside the annular body, the buffer layer being configured to contact the blade body 200. It can also be used in conjunction with a flexible gasket to reduce localized stress concentration and protect the blade paint layer and the composite matrix. The flexible gasket is preferably made of rubber, polyurethane, or other elastic materials to provide both vibration damping and protection.

[0140] According to one aspect of the embodiments of this application, the second constraint member 12 has a ring-shaped structure and is used to be sleeved on the side of the blade body 200 away from the blade tip. The second constraint member 12 is uncoilably configured in its own ring direction.

[0141] like Figure 1 as well as Figure 9 , Figure 10 As shown, the second constraint member 12 can be opened by setting an unlocking component 50 on the second constraint member 12. The unlocking component 50 can be used to quickly release and controllably detach the vibration damping device 100 from the blade body 200 when needed.

[0142] In one embodiment of this application, a vibration damping device 100 is provided. The second constraint member 12 adopts the above-described structure, which facilitates the removal of the clamping force between the second constraint member 12 and the blade body 200 by opening the second constraint member 12. The second constraint member 12 is separated from the blade body 200, and under the action of gravity, the vibration damping device 100 can be separated from the blade body 200, thereby realizing the disassembly of the vibration damping device 100 as needed.

[0143] According to one aspect of the embodiments of this application, the vibration damping device 100 further includes an unlocking component 50, which includes a fixing member 51 and a disconnection assembly 52 disposed on the fixing member 51. The second constraint member 12 is provided with the unlocking component 50. The fixing member 51 is connected to the second constraint member 12. The disconnection assembly 52 is used to cut off the second constraint member 12. The disconnection assembly 52 may include one or more components disposed on the fixing member 51 to facilitate the fulfillment of the cutting off requirement of the second constraint member 12.

[0144] By including the unlocking component 50 in the vibration damping device 100 and defining the above-described structure of the unlocking component 50, the fastener 51 can be connected to the second constraint 12, and the second constraint 12 can be cut open when needed by disconnecting the assembly 52, thus ensuring the disassembly and assembly requirements of the vibration damping device 100.

[0145] like Figure 9 As shown, according to one aspect of the embodiments of this application, the disconnect assembly 52 includes a power supply 521, a switch 522 and a heating element 523 connected in series. The heating element 523 is connected to the second constraint member 12 to heat and melt the second constraint member 12.

[0146] The heating element 523 includes, but is not limited to, structures such as resistance wires, low-melting-point alloy wires, and heating resistance wires, and may also include polymer fuses. The power supply 521 and switch 522 can be mounted on the fixing member 51, which may include a protective box or similar structure. When the second constraint member 12 needs to be cut off, the switch 522 can be closed, and the power supply 521 can energize and heat the heating element 523. Since the heating element 523 is connected to the second constraint member 12, the temperature of the heated element 523 continuously rises until it melts the portion connecting the second constraint member 12 and the heating element 523, allowing the second constraint member 12 to be opened.

[0147] Optionally, the second constraint member 12 may include materials such as low-melting-point plastics to facilitate the melting and setting of the heated member 523.

[0148] like Figure 10 As shown, it can be understood that the disconnect assembly 52 using the above embodiment is only an optional implementation. In some embodiments, the disconnect assembly 52 includes a drive member 524 and a cutter 525. The drive member 524 drives the cutter 525 to move, and a portion of the second constraint member 12 is located on the movement path of the cutter 525 so as to cut the second constraint member 12 by the cutter 525.

[0149] Optionally, the drive unit 524 may include a telescopic cylinder, a telescopic sleeve, or a gear rack or pinion, which are structural components capable of movement to drive the cutter 525 to move.

[0150] The drive unit 524 may optionally be connected to the fixing member 51. In some optional examples, the fixing member 51 may be provided with a guide portion that movably engages with the cutter 525, so that the cutter 525 moves along a predetermined trajectory.

[0151] The above settings also ensure the cutting effect on the second constraint member 12. Optionally, when using the cutter 525 structure, the second constraint member 12 may include at least one of materials such as cloth bags and plastic.

[0152] It is understood that the above is only an example of setting the unlocking component 50 on the second constraint member 12. In some embodiments, the unlocking component 50 can also be set on the first constraint member 11 and / or the vibration damping component 20. The principle of melting or cutting is the same as that of setting it on the second constraint member 12, and will not be repeated here.

[0153] According to one aspect of the embodiments of this application, the number of disconnect assemblies 52 is two or more, and the two or more disconnect assemblies 52 are all disposed on the fixing member 51.

[0154] The disconnect assembly 52 can be arranged in parallel on the fixing member 51 and connected to structural members such as the second constraint member 12. In this way, redundancy can be provided to avoid the problem of difficulty in disassembling and assembling the vibration damping device 100 due to the failure of a single disconnect member.

[0155] In some optional embodiments, the vibration damping device 100 provided in one embodiment of this application may further include a control unit for receiving a control signal and triggering the unlocking component 50 to operate. The signal may be a radio frequency signal, a wireless communication signal, a timed trigger signal, or a mechanical trigger signal.

[0156] Under normal operating conditions, the unlocking component 50 is in the closed state. When release is required, the control unit receives a preset signal, triggering the unlocking device to separate the vibration damping device 100 from the blade body 200 within a preset time range. Utilizing the geometric feature of the blade gradually narrowing from the root to the tip, the vibration damping device 100 can naturally slide off the surface of the blade body 200 after the second constraint member 12 is opened by the unlocking component 50, thereby achieving rapid overall detachment.

[0157] In another aspect, according to the embodiments of this application, a blade assembly is provided, including a blade body 200 and a vibration damping device 100 provided in the above embodiments. A first constraint member 11 and a second constraint member 12 are sleeved on the blade body 200 and fixed relative to the blade body 200. The vibration damping component 20 extends along a spiral path and is spirally wound around the blade body 200.

[0158] The blade assembly provided in one embodiment of this application includes the vibration damping device 100 provided in the above embodiments. Since the vibration damping assembly 20 includes a turbulence unit 21 extending along a spiral path, and the cross-section of the turbulence unit 21 in the spiral direction is polygonal and has a spiral mating surface 211 that fits against the outer surface of the blade, when the vibration damping device 100 is subjected to turbulence under different working conditions such as stacking, hoisting and grid connection, the spiral winding shape of the blade body 200 changes the local aerodynamic shape of the blade body 200. Moreover, the polygonal shape of the cross-section can break the vortex shedding law of the incoming airflow in different directions, effectively destroy the formation and development of stall vortex, thereby reducing vibration response and reducing the sway of the blade body 200 under the action of the incoming airflow.

[0159] The blade assemblies provided in some embodiments of this application are designed from a system perspective, incorporating a flow-disrupting device, a spacing device, and end-constraint and unlocking devices. This ensures that the vibration suppression scheme covers key aspects such as the realization of the flow-disrupting mechanism, the maintenance of arrangement parameters, and controllable release under abnormal operating conditions. Through this systematic design, not only is a stable vibration suppression effect achieved, but the engineering requirements for installation, operation, and safe release are also taken into account, improving reliability and feasibility in practical application scenarios.

[0160] According to another aspect of the embodiments of this application, the length of the blade body 200 is L1, and the length of the vibration damping device 100 on the blade body 200 is L2, wherein 25%≤L2 / L1≤50%.

[0161] Based on computational fluid dynamics simulation and modal analysis, it can be determined that the first 1 / 4 to 1 / 2 of the blade's span is the region of aerodynamic separation and modal energy concentration, and is also the location where vortex-induced vibration and stall-induced vibration are most likely to occur. Arranging vibration damping devices within this range can ensure vibration reduction while avoiding the additional weight and construction burden of full blade coverage.

[0162] In another aspect, according to the embodiments of this application, a wind turbine generator set is provided, including the above-mentioned blade assembly, which has a good vibration damping effect and can ensure the power generation efficiency of the wind turbine generator set itself.

Claims

1. A vibration damping device for a blade body, characterized in that, The vibration damping device includes: The constraint assembly includes a first constraint member and a second constraint member spaced apart, the first constraint member and the second constraint member being able to be fitted onto the blade body and fixed relative to the blade body; A vibration damping component is disposed between the first constraint member and the second constraint member, and the vibration damping component extends along a helical path to be helically wound around the blade body; The vibration damping component includes a turbulence unit extending along the spiral path. The turbulence unit includes a spiral mating surface, which is used to fit against the outer surface of the blade body.

2. The vibration damping device according to claim 1, characterized in that, The distance from the end of the turbulence unit away from the helical mating surface to the helical mating surface is h, which is perpendicular to the helical direction of the vibration damping component. The width of the turbulence unit is b, where 0.8 ≤ b / h ≤ 2.

5.

3. The vibration damping device according to claim 1, characterized in that, The vibration damping device also includes a flexible rope that matches the extension path of the turbulence unit and is embedded in the turbulence unit.

4. The vibration damping device according to claim 1, characterized in that, The turbulence unit is a strip-shaped structure extending along the spiral path, and the cross-sectional shape of the turbulence unit perpendicular to its own extension direction is polygonal.

5. The vibration damping device according to claim 4, characterized in that, The polygon has n sides, where 3 ≤ n ≤ 6; And / or, the turbulence unit includes a foamed material.

6. The vibration damping device according to claim 1, characterized in that, The turbulence unit includes a sharp corner portion disposed opposite to the spiral mating surface, and the included angle θ of the sharp corner portion ranges from 60° to 90°.

7. The vibration damping device according to claim 1, characterized in that, The ratio of the characteristic height k of the turbulence element to the local boundary layer thickness δ, k / δ, ranges from 0.3 to 0.

7.

8. The vibration damping device according to claim 1, characterized in that, The vibration damping component also includes a flexible connection unit, and there are multiple turbulence units, with the flexible connection unit connecting adjacent turbulence units.

9. The vibration damping device according to claim 8, characterized in that, The flexible connection unit includes an elastic rope, a flexible sleeve, or a flexible connection belt.

10. The vibration damping device according to claim 1, characterized in that, Along the spiral direction of the vibration damping component, the pitch of the multiple turbulence units as a whole is a fixed pitch; Alternatively, the pitch of multiple turbulence units as a whole shows an increasing trend, which includes one of the following: gradually increasing, increasing segment by segment, first remaining fixed and then gradually increasing, or first remaining fixed and then increasing segment by segment.

11. The vibration damping device according to claim 1, characterized in that, The vibration damping device further includes a distance fixing component, which is at least partially disposed between the first constraint member and the second constraint member. Along the arrangement direction of the first constraint member and the second constraint member, the distance fixing component includes a plurality of spaced limiting parts. The turbulence unit is sequentially engaged with each of the limiting parts. The distance fixing component is used to engage with the trailing edge of the blade body and fix the relative position of the blade body.

12. The vibration damping device according to claim 11, characterized in that, Along the arrangement direction, the spacing component includes a plurality of spaced spacing units and a connecting portion connecting two adjacent spacing units, and each spacing unit is provided with the limiting portion.

13. The vibration damping device according to claim 1, characterized in that, The first constraint member has a ring-shaped structure and is used to be fitted onto the tip of the blade body.

14. The vibration damping device according to claim 13, characterized in that, The first constraint member includes an annular body and a buffer layer disposed inside the annular body, the buffer layer being configured to contact the blade body.

15. The vibration damping device according to claim 1, characterized in that, The second constraint member has a ring-shaped structure and is used to be sleeved on the side of the blade body away from the blade tip. The second constraint member can be opened in its ring direction.

16. The vibration damping device according to claim 15, characterized in that, The vibration damping device further includes an unlocking component, which includes a fixing member and a disconnection assembly disposed on the fixing member. The second constraint member is provided with the unlocking component. The fixing member is connected to the second constraint member. The disconnection assembly is used to disconnect the second constraint member.

17. The vibration damping device according to claim 16, characterized in that, The disconnect assembly includes a power supply, a switch, and a heating element arranged in series. The heating element is connected to the second constraint element to heat and melt the second constraint element. Alternatively, the disconnect assembly includes a drive unit and a cutter, the drive unit driving the cutter to move, with a portion of the second constraint located on the movement path of the cutter to cut the second constraint by the cutter.

18. The vibration damping device according to claim 17, characterized in that, The number of disconnect assemblies is two or more, and both or more disconnect assemblies are disposed on the fixing member.

19. A blade assembly, characterized in that, include: The blade itself; The vibration damping device according to any one of claims 1 to 18, wherein the first constraint member and the second constraint member are sleeved on the blade body and fixed relative to the blade body, and the vibration damping component extends along a spiral path and is spirally wound around the blade body.

20. The blade assembly according to claim 19, characterized in that, The length of the blade body is L1, and the length of the vibration damping device on the blade body is L2, wherein 25%≤L2 / L1≤50%.

21. A wind turbine generator set, characterized in that, include: The blade assembly as described in claim 19 or 20.

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