Method and control device for suppressing flutter of wind turbine blade based on trailing edge deformation

Abstract

The present invention relates to a method and a control device for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge part. The wind turbine blade includes: an airfoil main body part, a movable connecting piece, and a trailing edge part connected to the airfoil main body part through the movable connecting piece. The method includes: obtaining a control strategy; controlling the trailing edge part to change the end deformation angle of the trailing edge part with the movable connecting piece as a fulcrum based on the control strategy, so as to suppress the flutter of the blade. In the technical solution of the present invention, the configuration of the airfoil main body part, the movable connecting piece, and the trailing edge part connected to the airfoil main body part through the movable connecting piece is introduced. By obtaining an accurate control strategy and implementing the dynamic adjustment of the end deformation angle of the trailing edge part, the adaptability and stability of the wind turbine blade in the face of strong winds and unstable airflow conditions are significantly improved. At the same time, its fatigue life is greatly enhanced, the potential safety hazards caused by flutter are reduced, thereby improving the overall operation efficiency and safety of the wind turbine unit.

Description

Technical Field

[0001] The present invention relates to the field of wind power generation, and specifically provides a method for suppressing flutter of a wind turbine blade based on trailing edge deformation and a control device therefor. Background Art

[0002] In the prior art, with the development trend of wind turbines towards large-scale, the aspect ratio of wind turbine blades has increased sharply, resulting in increased structural flexibility and the problem of stall flutter has become prominent.

[0003] The flutter problem not only seriously affects the fatigue life of the blade and the entire structure, but may also cause structural damage under certain working conditions, thus causing huge potential safety hazards and economic losses.

[0004] Correspondingly, there is a need in the art for a new solution for suppressing flutter of wind turbine blades to solve the above problems. Summary of the Invention

[0005] In order to overcome the above defects, the present invention is proposed to provide a solution to solve or at least partially solve the technical problem that flutter is likely to occur during the use of wind turbine blades in the prior art.

[0006] In a first aspect, the present invention provides a method for suppressing flutter of a wind turbine blade based on trailing edge deformation, wherein the wind turbine blade includes: an airfoil main body part, a movable connecting member, and a trailing edge part connected to the airfoil main body part through the movable connecting member. The method includes: obtaining a control strategy; and based on the control strategy, controlling the trailing edge part to change the end deformation angle of the trailing edge part with the movable connecting member as a fulcrum to suppress the flutter of the wind turbine blade.

[0007] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the control strategy includes: changing the end deformation angle of the trailing edge part according to a preset periodic function, where the periodic function reflects the relationship between time and the end deformation angle of the trailing edge part.

[0008] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the method further includes: obtaining the current wind speed and / or the change rate of the current wind speed; and in response to the current wind speed and / or the change rate of the current wind speed satisfying a preset control start condition, performing "controlling the trailing edge part to change the end deformation angle of the trailing edge part with the movable connecting member as a fulcrum based on the control strategy".

[0009] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the method further includes: obtaining a model of the trailing edge deformation, where the model of the trailing edge deformation at least reflects the relationship between the end deformation angle of the trailing edge and the surface point coordinates of the trailing edge; obtaining the vector wind speed in real time; where the method for obtaining the control strategy includes: obtaining the control strategy based on the vector wind speed and the model of the trailing edge deformation.

[0010] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the step of "obtaining the control strategy based on the vector wind speed and the model of the trailing edge deformation" includes: at least simulating based on the vector wind speed and the model of the trailing edge deformation to obtain the offset displacement and flutter angle of the blade flutter; adjusting the magnitude of the end deformation angle of the trailing edge so that the offset displacement and flutter angle of the blade flutter meet the preset requirements.

[0011] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the material used for the trailing edge is a flexible material, where the flexible material is used to make the chord line of the trailing edge approximate to an arc when the end deformation angle of the trailing edge is non-zero. The method for constructing the mathematical model of the trailing edge deformation includes: setting a section along the chord line of the airfoil main body; obtaining the end deformation angle of the trailing edge and the length of the chord line of the trailing edge; based on the end deformation angle of the trailing edge, obtaining the first central angle of the first virtual sector formed by the end of the trailing edge as the first endpoint, the movable connection as the second endpoint, and the tangent point; based on the length of the chord line of the trailing edge and the first central angle, obtaining the first radius corresponding to the first virtual sector; obtaining the original coordinates of the surface point of the trailing edge and the first arc length from the mapping point of the surface point on the chord line of the trailing edge to the second endpoint; based on the first radius and the first arc length, obtaining the deformation angle of the mapping point of the surface point on the chord line of the trailing edge; based on the deformation angle of the mapping point of the surface point on the chord line of the trailing edge, obtaining the second central angle of the second virtual sector formed by the mapping point of the surface point on the chord line of the trailing edge as the third endpoint and the second endpoint as the tangent point; based on the deformation angle of the mapping point of the surface point on the chord line of the trailing edge and the first radius, obtaining the second radius of the second virtual sector; based on the original coordinates of the surface point of the trailing edge, the second central angle, the deformation angle of the mapping point of the surface point on the chord line of the trailing edge, and the second radius, obtaining the surface point coordinates of the trailing edge.

[0012] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the original coordinates of the surface point of the trailing edge have only a vertical coordinate, and the vertical coordinate is set along the direction perpendicular to the blade length.

[0013] As an alternative or supplement to the above solution, in the method according to an embodiment of the present invention, the step of "obtaining the coordinates of the trailing edge surface point based on the original coordinates of the trailing edge surface point, the second central angle, the angle of deformation of the trailing edge surface point, and the second radius" includes:

[0014] Where x1 and y1 are the coordinates of the trailing edge surface point, α is the angle of deformation of the trailing edge surface point, β is the second central angle, r is the second radius, and y0 is the original coordinate of the trailing edge end surface point.

[0015] In a second aspect, a control device is provided. The control device includes a processor and a storage device. The storage device is adapted to store multiple computer programs, and the computer programs are adapted to be loaded and run by the processor to execute the method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge according to any one of the technical solutions in the above technical solutions.

[0016] In a third aspect, a computer-readable storage medium is provided. The computer-readable storage medium stores multiple computer programs, and the computer programs are adapted to be loaded and run by a processor to execute the method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge according to any one of the technical solutions in the above technical solutions.

[0017] One or more of the above technical solutions of the present invention have at least one or more of the following beneficial effects:

[0018] In implementing the technical solutions of the present invention, the configuration of an airfoil main body part, a movable connecting piece, and a trailing edge part connected to the airfoil main body part through the movable connecting piece is introduced. By obtaining an accurate control strategy and implementing the dynamic adjustment of the deformation angle at the trailing edge end, the adaptability and stability of the wind turbine blade in the face of strong winds and unstable airflow conditions are significantly improved. At the same time, its fatigue life is greatly enhanced, potential safety hazards caused by flutter are reduced, thereby improving the overall operating efficiency and safety of the wind turbine unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Referring to the accompanying drawings, the disclosure of the present invention will become more easily understood. It is easy for those skilled in the art to understand that these drawings are only for illustrative purposes and are not intended to limit the scope of protection of the present invention. In addition, similar numbers in the drawings are used to represent similar components, where:

[0020] Figure 1 is a schematic flowchart of the main steps of a method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge according to an embodiment of the present invention;

[0021] Figure 2It is a schematic diagram of the secondary step process of a wind turbine blade flutter suppression method based on trailing edge deformation according to an embodiment of the present invention;

[0022] Figure 3 It is a schematic diagram of the secondary step process of a wind turbine blade flutter suppression method based on trailing edge deformation according to an embodiment of the present invention;

[0023] Figure 4 It is a schematic diagram of the secondary step process of a wind turbine blade flutter suppression method based on trailing edge deformation according to an embodiment of the present invention;

[0024] Figure 5 It is a schematic diagram of the modeling process of a wind turbine blade flutter suppression method based on trailing edge deformation according to an embodiment of the present invention;

[0025] Figure 6 It is a schematic diagram of a wind turbine blade of a wind turbine blade flutter suppression method based on trailing edge deformation according to an embodiment of the present invention;

[0026] Figure 7 It is a schematic diagram of a cross-section of a wind turbine blade flutter suppression method based on trailing edge deformation according to an embodiment of the present invention. Detailed implementation manners

[0027] The following describes some embodiments of the present invention with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the protection scope of the present invention.

[0028] In the description of the present invention, "module" and "processor" may include hardware, software, or a combination of both. A module may include a hardware circuit, various suitable sensors, communication ports, memories, and may also include a software part, such as a computer program, or a combination of software and hardware. The processor may be a central processing unit, a microprocessor, an image processor, a digital signal processor, or any other suitable processor. The processor has data and / or signal processing functions. The processor may be implemented in software, in hardware, or in a combination of both. The non-transitory computer-readable storage medium includes any suitable medium for storing a computer program, such as a magnetic disk, a hard disk, an optical disk, a flash memory, a read-only memory, a random access memory, and so on. The term "A and / or B" represents all possible combinations of A and B, such as only A, only B, or A and B. The term "at least one A or B" or "at least one of A and B" has the same meaning as "A and / or B" and may include only A, only B, or A and B. The singular terms "a" and "this" may also include the plural form.

[0029] In an embodiment of the present invention, a wind turbine blade includes: an airfoil main body, a movable connecting member, and a trailing edge portion connected to the airfoil main body through the movable connecting member, as Figure 6 shown, where Figure 6 is a schematic diagram of the wind turbine blade. The dividing line between the airfoil main body and the trailing edge portion indicates that the trailing edge portion can move independently. The blade structure in this application optimizes the aerodynamic coefficient by dynamically adjusting the position of the trailing edge portion of the blade, thereby improving the performance and reliability of the wind turbine blade.

[0030] In this embodiment, the airfoil main body is the core part of the blade, responsible for providing the main lift and bearing the wind load. It is made of a rigid material, such as a high-performance composite material or carbon fiber, to ensure sufficient strength and rigidity in the face of high wind speeds.

[0031] In this embodiment, the movable connecting member not only provides a physical connection between the airfoil main body and the trailing edge portion, but also allows the trailing edge portion to swing relative to the airfoil main body. This swing is achieved by the control system controlling the movable connecting member. The control body of the movable connecting member can be selected but is not limited to hydraulic or pneumatic actuators, servo motors, etc. The movable connecting member enables the trailing edge portion to swing in different directions, specifically perpendicular or approximately perpendicular to the blade surface. In one embodiment, the movable connecting member controls the swing direction of the trailing edge portion to swing approximately perpendicular to the chord line of the airfoil main body, thereby dynamically adjusting its shape according to the wind conditions and the operating state of the blade.

[0032] In this embodiment, the material used for the trailing edge portion is a flexible material or a rigid material. In the prior art, rigid materials are used for the trailing edge portion.

[0033] In this embodiment, the advantage of using a flexible material to make the trailing edge portion is that when the trailing edge portion swings, the flexible material can make the influence of this swing smoother. This is because the flexible material has good elasticity and can produce appropriate deformation when subjected to wind force. This deformation can absorb part of the energy, reduce the impact and vibration generated when the trailing edge portion swings, thereby more effectively protecting the blade and extending its service life. In contrast, when the trailing edge portion made of a rigid material swings, the transition may appear more abrupt. Especially when adjusting quickly or dealing with sudden wind forces, the response of the rigid trailing edge may result in greater mechanical stress, thereby affecting the structural stability and reliability of the blade.

[0034] In this application, the definition of the term "oscillation" is as follows: The oscillation in this application includes: periodic motion or quasi-periodic motion similar to a simple pendulum, and also includes the action of moving the trailing edge part to a certain specific angle through a movable connecting piece. Such oscillation can be dynamic, adjusted according to environmental parameters such as wind speed and wind direction monitored in real time, or static, that is, adjusting the trailing edge part to the optimal position to adapt to the current wind conditions and then remaining unchanged. Such a design allows the trailing edge part to be effectively adjusted under a wide range of operating conditions, optimizing its performance by changing the aerodynamic profile and angle of attack of the blade, reducing stall and flutter phenomena, and improving the overall efficiency and stability of the wind turbine.

[0035] In this application, through the above structural design, active suppression control of the flutter of the wind turbine blade can be achieved. In addition, the design of the present invention also takes into account the reliability of the overall structure and the convenience of maintenance, ensuring the high efficiency and economy of the wind turbine blade during long-term operation.

[0036] Example 1:

[0037] Refer to the appendix Figure 1 , Figure 1 is a schematic diagram of the main step flow of a method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge part according to an embodiment of the present invention. As Figure 1 shown, the method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge part in the embodiment of the present invention mainly includes the following steps S10 - step S20.

[0038] Step S10: Obtain a control strategy.

[0039] Step S20: Based on the control strategy, control the trailing edge part to change the end deformation angle with the movable connecting piece as the fulcrum to achieve suppression of the flutter of the blade.

[0040] In one implementation, the control strategy can be either pre-set or obtained in real time based on other methods.

[0041] In one implementation, for a pre-set control strategy, the control strategy is usually determined based on historical data, simulation analysis of flutter behavior, or field experiments. In one implementation, through research on wind speed changes, wind direction changes and their effects on blade flutter, or improvements in the blade structure, a set of fixed control rules or parameter settings can be designed to guide the deformation control of the trailing edge part. The advantage of a pre-set control strategy is that it is simple to operate, easy to set, and can achieve a certain effect of suppressing blade flutter.

[0042] In another embodiment, the control strategy obtained through real-time calculation can selectively utilize methods such as deep learning and neural networks or mathematical models to dynamically calculate the optimal trailing edge deformation control strategy based on environmental parameters such as the wind speed and wind direction monitored in real time. If the obtained control strategy is obtained through real-time calculation, then this method can achieve more precise flutter suppression by continuously learning and adapting to different wind conditions. For example, using a deep learning model, it is possible to predict the possible flutter situations that the blade may encounter in the short term in the future based on the current and past wind data, and accordingly adjust the deformation angle of the trailing edge to best respond to the predicted wind changes. The advantage of the control strategy obtained through real-time calculation is that it can handle more complex and changeable environmental conditions. Although this solution uses more computing power and slightly increases the overall cost, it improves the efficiency and effect of flutter suppression compared to the pre-set control strategy.

[0043] In one embodiment, the control strategy includes: changing the end deformation angle of the trailing edge periodically according to a preset function.

[0044] In this embodiment, the strategy for controlling the end deformation angle of the trailing edge is implemented based on a preset periodic function. In this embodiment, the periodic function is not limited to common trigonometric functions (such as sine and cosine functions), but may also include other functions with periodic change characteristics.

[0045] In this embodiment, after analysis by the applicant, it is considered that the flutter of the wind turbine blade often has periodicity, so using a periodic function as the basis of the control strategy achieves better results. Since flutter is caused by the periodic load change generated by the wind acting on the blade, therefore, by applying the deformation angle adjustment with corresponding periodicity, the influence of these periodic loads can be effectively resisted or offset, thereby reducing or suppressing flutter. In one embodiment, the sine function α max = A m sin(ωt) is used to adjust the end deformation angle of the trailing edge, where A m represents the maximum amplitude of the deformation, ω represents the adjustment frequency, t represents time, and α max represents the end deformation angle of the trailing edge. By precisely selecting A m and ω, the deformation of the trailing edge can reduce the influence of flutter caused by the wind.

[0046] The mechanism of this embodiment lies in that by periodically adjusting the deformation of the trailing edge, a dynamic regulatory force acting against the wind force can be provided within each flutter cycle. This regulatory force can reduce the overall vibration energy of the blade. Especially when the frequency of the regulatory force is close to or equal to the natural frequency of flutter, through the resonance elimination principle, the flutter phenomenon can be effectively alleviated or eliminated. In addition, the application of the periodic function also provides a high degree of flexibility and adaptability, enabling the control strategy to be dynamically adjusted according to the real-time monitored wind conditions, achieving more precise flutter suppression.

[0047] In this embodiment, by adjusting the deformation angle of the trailing edge, the flutter of the wind turbine blade can be effectively suppressed, and the service life of the blade and the wind turbine can be extended. Thereby improving the stability and reliability of the wind turbine, and further improving the overall power generation efficiency and economy.

[0048] In one embodiment, the material used for the trailing edge is a flexible material.

[0049] In this embodiment, the control strategy adjusts the end deformation angle of the trailing edge through a preset periodic function, and the material selected for the trailing edge is a flexible material. The combination of these two, that is, using the characteristics of the flexible material to assist in implementing the dynamic deformation control based on the periodic function, thus achieving better results.

[0050] Specifically, the dynamic deformation of the flexible material under the control of the periodic function can more effectively reduce the movement of the pressure point and the local air flow separation caused by the change in wind speed. The flexible trailing edge can provide a more delicate adjustment to adapt to the changing air flow conditions. In addition, during the periodic deformation process, the flexible trailing edge can better absorb energy, reduce the flutter energy transmitted to the blade body, thereby reducing the vibration level of the entire blade.

[0051] In summary, the combination of using a flexible material for the trailing edge and the periodic function control strategy can not only more precisely match and offset the dynamic behavior of flutter, but also optimize the aerodynamic performance of the blade through the smooth dynamic deformation of the flexible trailing edge, ultimately achieving the goals of reducing flutter, improving power generation efficiency, and extending the blade life.

[0052] Example 2:

[0053] In this embodiment, most of the technologies are the same as those in Embodiment 1. The difference is that the control strategy in this embodiment is not preset but obtained through calculation. Except for this, the rest of the technologies are the same as those in Embodiment 1, as Figure 2 shown, and the details will not be elaborated here as follows:

[0054] Step S301: Obtain the current wind speed and / or the change rate of the current wind speed.

[0055] In this embodiment, the execution of the control strategy can be controlled by only obtaining the current wind speed, or by obtaining the change rate of the current wind speed, or by obtaining the current wind speed and the change rate of the current wind speed.

[0056] In one embodiment, the current wind speed and the change rate of the current wind speed are monitored in real time to identify whether flutter is likely to occur. The measurement of the current wind speed includes not only the magnitude of the wind force but also the information of the wind direction. Therefore, the obtained current wind speed is a vector wind speed. Similarly, the change rate of the current wind speed is also for the current wind speed, that is, it describes the rates of change of both the wind speed magnitude and the wind direction at the same time. By monitoring these two parameters in real time, the changes in wind conditions can be quickly responded to, simplifying the prediction process of the blade flutter state. Compared with more complex measurement and analysis methods, this approach not only saves costs but also improves efficiency.

[0057] In one embodiment, in order to accurately measure the current wind speed and the change rate of the current wind speed, meteorological measurement devices such as anemometers, wind vanes or ultrasonic-based wind sensors can be used. These devices can provide immediate wind force magnitude and direction data. In this embodiment, these measurement devices can be installed on the top of the wind turbine tower or near the blade to ensure that data reflecting the real wind conditions can be obtained.

[0058] In this embodiment, by obtaining the current wind speed and its change rate as monitoring means, reliable data support and a timely response mechanism are provided for the dynamic suppression of wind turbine blade flutter.

[0059] Step S302: In response to the current wind speed and / or the change rate of the current wind speed satisfying a preset control start condition, execute "controlling the trailing edge to change the end deformation angle of the trailing edge with the movable connection as the fulcrum based on the control strategy".

[0060] In this embodiment, the control strategy controls the trailing edge to change the end deformation angle of the trailing edge with the movable connection as the fulcrum to suppress the flutter of the blade.

[0061] In one embodiment, the preset control start condition is formulated based on the physical mechanism of wind turbine blade flutter and historical experience data. In this application, three specific embodiments corresponding to the preset control start condition are given as follows:

[0062] Embodiment 1: The current wind speed reaches a specific threshold: When the measured wind speed exceeds the specific speed that can cause blade flutter, it is considered that the control start condition is satisfied. This threshold is preset based on the design parameters and experience of the blade. For example: When only the current wind speed information is available, the preset condition may be "the current wind speed exceeds 10 m / s".

[0063] Embodiment 2: The change rate of the current wind speed exceeds a preset threshold: The rapid change of the wind speed is another important factor for the occurrence of flutter. When the change rate of the wind speed exceeds a preset threshold, it is also considered that the control start condition is satisfied. For example, when only the wind speed change rate information is available, the preset condition may be "the wind speed change rate exceeds 3 m / s within 1 second".

[0064] Embodiment 3: Consider both the current wind speed and the change rate of the current wind speed: Consider the comprehensive situation of both the current wind speed and the wind speed change rate. For example, when both the current wind speed and the change rate are obtained simultaneously, the preset condition may be "the current wind speed exceeds 10 m / s and the wind speed change rate exceeds 3 m / s within 1 second".

[0065] In this embodiment, by means of the control start condition, it is determined when it is necessary to suppress flutter through deformation control, avoiding unnecessary operations, thereby improving the overall efficiency of the system. And the control strategy is only activated when it is truly necessary to suppress flutter, avoiding over-regulation or unnecessary energy consumption, which helps to optimize the energy use of the entire system.

[0066] In summary, by activating the control strategy for the trailing edge deformation when the preset control start condition is met, this embodiment can effectively suppress the flutter of the wind turbine blade, optimize the operating performance of the blade, and at the same time ensure the economy and sustainability of the system operation.

[0067] Further, in one embodiment, a control strategy is obtained by using the model of the trailing edge deformation and the vector wind speed obtained in real time, including steps S401 - S403, as Figure 3 shown below:

[0068] Step S401: Obtain the model of the trailing edge deformation.

[0069] In this embodiment, the model of the trailing edge deformation at least reflects the relationship between the end deformation angle of the trailing edge and the coordinates of the surface points of the trailing edge.

[0070] In one embodiment, the material used for the trailing edge is a flexible material, where the flexible material is used to make the chord line of the trailing edge approximate to an arc when the end deformation angle of the trailing edge is non-zero. The construction method of the mathematical model of the trailing edge deformation is as Figure 5As shown in the figure, it includes: setting a section along the chord line of the airfoil main body; obtaining the angle of deformation at the end of the trailing edge part and the length of the chord line of the trailing edge part; based on the angle of deformation at the end of the trailing edge part, obtaining the first central angle of the first virtual sector formed by taking the end of the trailing edge part as the first endpoint, the movable connecting piece as the second endpoint and the tangent point; based on the length of the chord line of the trailing edge part and the first central angle, obtaining the first radius corresponding to the first virtual sector; obtaining the original coordinates of the surface point on the trailing edge part and the first arc length from the mapping point of the surface point on the chord line of the trailing edge part to the second endpoint; based on the first radius and the first arc length, obtaining the angle of deformation of the mapping point of the surface point on the chord line of the trailing edge part; based on the angle of deformation of the mapping point of the surface point on the chord line of the trailing edge part, obtaining the second central angle of the second virtual sector formed by taking the mapping point of the surface point on the chord line of the trailing edge part as the third endpoint and the second endpoint as the tangent point; based on the angle of deformation of the mapping point of the surface point on the chord line of the trailing edge part and the first radius, obtaining the second radius of the second virtual sector; based on the original coordinates of the surface point on the trailing edge part, the second central angle, the angle of deformation of the mapping point of the surface point on the chord line of the trailing edge part and the second radius, obtaining the coordinates of the surface point on the trailing edge part.

[0071] The specific explanation is as follows:

[0072] In one embodiment, the new coordinates of the surface point on the trailing edge part, that is, the coordinates of the surface point on the trailing edge part, are described and calculated through the angle of deformation α at the end of the trailing edge part max and the geometric relationship and polar coordinate system. As Figure 7 shown in the figure, the following is a detailed analysis of this process:

[0073] First, define the angle of deformation α at the end of the trailing edge part max , which is the angle that the trailing edge part can rotate through the control strategy. Based on this angle, taking the end of the trailing edge part as the first endpoint and the movable connecting piece as the second endpoint, and at the same time regarding the second endpoint as the tangent point to construct the first virtual sector, and its first central angle β max is twice that of α max , expressed as β max = 2|α max |. This relationship reflects the significant geometric feature of the deformation at the end of the trailing edge part, that is, the increase in the deformation angle leads to a corresponding increase in the central angle.

[0074] Using the length L0 of the chord line of the trailing edge part and the first central angle β max , calculate the radius r0 of the first virtual sector, and the calculation method is This radius helps to further determine the position of the surface point on the trailing edge part after deformation.

[0075] For any surface point on the trailing edge part, the distance from the mapping point of the surface point on the chord line of the trailing edge part to the movable connecting piece O (i.e., the first arc length L) and the deformation angle α of this point are obtained through the angle of deformation α at the end of the trailing edge partmax and the first radius r0. In this embodiment, α is based on α max calculated from the proportional relationship with the first arc length L, expressed as Based on this angle, the second central angle β and the second radius r of the second virtual sector can be calculated, where β = 2α and r = 2r0sinα.

[0076] Finally, based on the calculated α and β above, and the original coordinates y0 of the surface points of the trailing edge part, the coordinates (x1, y1) of the surface points of the trailing edge part after deformation can be calculated using geometric relationships. These new coordinates are given by the following formulas:

[0077] x1 = rcosα - y0sinβ y1 = rsinα + y0cosβ

[0078] This process illustrates how to use the deformation angle at the end of the trailing edge part and geometric relationships to calculate the exact position of the surface points of the trailing edge part after deformation under the action of wind force. The advantage of this method lies in its high accuracy and the ability to directly model physical phenomena. Through this method, the response of the trailing edge part of the wind turbine blade under different wind force conditions can be predicted and analyzed in detail, thus providing a solid foundation for formulating effective control strategies.

[0079] In this embodiment, the original coordinates of the surface points of the trailing edge part are specifically limited to only include the ordinate y. This setting takes into account the simplification of the trailing edge deformation analysis of the wind turbine blade and specific geometric processing. In the model for analyzing the trailing edge deformation of the wind turbine blade and its influence on flutter, especially when dealing with the deformation and twisting of the blade under the action of wind force, the longitudinal change (i.e., the change perpendicular to the blade width direction) is usually more significant and critical than the transverse change (i.e., the change along the blade width direction). This is because the wind force mainly affects the bending and twisting of the blade, and these effects are more easily observed and quantified in the longitudinal direction of the blade.

[0080] In this embodiment, by focusing on the longitudinal change, the calculation model for the trailing edge part deformation analysis can be simplified. In practical applications, the deformation of the trailing edge part of the blade mainly manifests as longitudinal offset and angular change. Therefore, by focusing on the change of the ordinate, the influence of the trailing edge part deformation on the blade performance can be effectively captured while reducing the calculation complexity.

[0081] At the same time, in this embodiment, the change of the ordinate is more directly related to the key factors of blade flutter, such as offset displacement and flutter angle. These parameters are important indicators for analyzing and controlling blade flutter. Therefore, by accurately measuring and simulating the longitudinal change, the flutter state can be more precisely evaluated and control strategies can be formulated.

[0082] Meanwhile, in this embodiment, in the structural design of a wind turbine blade, the deformation of the trailing edge usually appears as twisting or bending along the blade length direction, and the influence of these deformations is most obvious on the cross-section perpendicular to the blade length direction. Therefore, by considering the change in the vertical coordinate of the surface points, the model can better reflect the actual physical situation.

[0083] In summary, in this embodiment, by combining the vertical coordinate with the deformation angle described in polar coordinates, not only the model for analyzing the deformation of the trailing edge is simplified, but also the description and control of the response of the trailing edge under the action of wind force are made more convenient and effective. Through this method, the new coordinates of the surface points after the deformation of the trailing edge can be accurately calculated, thus providing a reliable basis for designing an effective control strategy to suppress blade flutter.

[0084] Step S402: Obtain the vector wind speed in real time.

[0085] Step S403: Obtain a control strategy based on the vector wind speed and the model of the trailing edge deformation.

[0086] In one embodiment, by combining the vector wind speed data with the model of the trailing edge deformation through precise calculation and analysis, it is ensured that the wind turbine blade can maintain the best operating state under various wind conditions, thus effectively suppressing flutter.

[0087] In one embodiment, a control strategy can be generated through three stages: data integration, analysis and calculation, and control strategy generation. Specifically:

[0088] First, the system is responsible for receiving the vector wind speed and integrating the vector wind speed with the model of the trailing edge deformation.

[0089] After that, the system then uses the model of the trailing edge deformation to analyze the forces that the trailing edge may bear under the current wind conditions. This analysis takes into account the magnitude, direction, and change of the wind direction of the vector wind speed to judge how the vector wind speed affects the force on the trailing edge. Based on this analysis, the system uses fluid mechanics and structural mechanics models to calculate how the end deformation angle of the trailing edge should be adjusted to most effectively suppress flutter. Specifically, by calculating and simulating the behavior of the blade under different wind forces, predicting the possibility of flutter occurrence, and determining the best trailing edge deformation strategy to counteract these flutters.

[0090] Finally, based on the above analysis and calculation, the control system generates a specific control strategy. The control strategy may include parameters such as the specific angle of the trailing edge deformation, as well as the deformation speed and duration. The control strategy is adjusted according to the real-time vector wind speed.

[0091] By executing the control strategy, the system can effectively suppress blade flutter and ensure the stable operation of the wind turbine unit.

[0092] In another embodiment, the control strategy is obtained through steps S403-1 to S403-3, which are specifically as follows:

[0093] Step S403-1: Simulate at least based on the model of the vector wind speed and the deformation of the trailing edge to obtain the offset displacement and flutter angle of the blade flutter.

[0094] In one embodiment, the simulation process is based on the current vector wind speed and the model of the trailing edge deformation. The objective of this step is to calculate the offset displacement and flutter angle generated by the wind turbine blade under the action of wind.

[0095] Specifically, at time t0, the blade is affected by a specific wind speed and wind direction. Assume that the blade has two degrees of freedom, namely the offset displacement (displacement in the y direction) and the flutter angle (rotation around the transverse axis of the blade). At this time, the original coordinates of a certain point on the blade, that is, the surface point of the trailing edge, are at the position of coordinates (x0, y0). When reaching the next moment t1, due to the change of the wind speed and wind direction, this surface point moves to a new position, that is, the coordinates of the surface point of the trailing edge are (x1, y1). This movement can be described by the offset displacement y and the flutter angle θ.

[0096] Step S403-2: By adjusting the size of the end deformation angle of the trailing edge, make the offset displacement and flutter angle of the blade flutter meet the preset requirements.

[0097] In one embodiment, in order to control the blade flutter and make it meet the preset requirements, the system adjusts the end deformation angle α max of the trailing edge by the size. This adjustment is based on the values of the offset displacement y and the flutter angle θ, and adopts a closed-loop control strategy. The core formula of the control strategy is α max =β1y0 + β2θ0, where β1 and β2 are gain parameters preset according to the dynamic response characteristics of the system, and y0 and θ0 represent the offset displacement and flutter angle at the current moment respectively. Through this control strategy, the system aims to minimize the offset displacement y1 and flutter angle θ1 at the next moment, that is, min(y1, θ1)=f(α max ), so as to effectively suppress the blade flutter.

[0098] In this embodiment, the preset requirements can take various forms, specifically depending on the index requirements for flutter control. The following are two possible ways to set the preset requirements:

[0099] In one embodiment, the end deformation angle of the trailing edge part for obtaining the lowest potential energy point along the descending gradient is determined. Under this setting, the preset requirement is to adjust the offset displacement and flutter angle of the blade flutter to the lowest potential energy point. This means finding a state by controlling the deformation of the trailing edge part so that the total potential energy of the blade system reaches the possible minimum value, thereby theoretically achieving the most stable state.

[0100] In another embodiment, the preset requirement is that the offset displacement and flutter angle of the blade flutter are respectively lower than a specific offset displacement threshold and a flutter angle threshold. These thresholds can be preset according to the design parameters of the blade, the operating requirements of the wind turbine, and safety standards, aiming to ensure that the blade does not exceed the safe operating range under any wind conditions.

[0101] Step S403-3: Take the end deformation angle of the trailing edge part that meets the preset requirement as the control strategy.

[0102] In one embodiment, that is, take α that meets the preset requirement max as the control strategy.

[0103] In this embodiment, this process is an iterative process, which means that the system continuously monitors the offset displacement and flutter angle of the blade, and continuously adjusts the end deformation angle of the trailing edge part according to the real-time data to adapt to the changes in wind speed and direction, so as to effectively control the blade flutter.

[0104] In this embodiment, through the above method, the control strategy can be dynamically adjusted according to the real-time wind conditions to ensure that the blade is always in the best working state, which not only ensures the efficient and stable operation of the wind turbine, but also extends the service life of the blade. In addition, the design of this control strategy takes into account the dynamic response characteristics of the blade, and maximally suppresses flutter by precisely adjusting the deformation of the trailing edge part, improving the accuracy and efficiency of control.

[0105] It should be noted that although the above steps are described in a specific order in the above embodiments, those skilled in the art can understand that in order to achieve the effects of the present invention, different steps do not necessarily have to be executed in such an order, and they can be executed simultaneously (in parallel) or in other orders, and these changes are all within the protection scope of the present invention.

[0106] Those skilled in the art can understand that all or part of the processes in the methods of the above-mentioned embodiments of the present invention can also be completed by instructing relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium. When the computer program is executed by a processor, the steps of the above-mentioned method embodiments can be implemented. Among them, the computer program includes a computer program, and the computer program can be in the form of source code, object code, executable file or some intermediate form, etc. The computer-readable storage medium can include: any entity or device, medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory, random access memory, electrical carrier signal, telecommunication signal, and software distribution medium that can carry the computer program. It should be noted that the content included in the computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the computer-readable storage medium does not include electrical carrier signals and telecommunication signals.

[0107] Furthermore, the present invention also provides a control device. In an embodiment of the control device according to the present invention, the control device includes a processor and a storage device. The storage device can be configured to store a program for executing the method embodiment of suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge. The processor can be configured to execute the program in the storage device, and the program includes, but is not limited to, a program for executing the method embodiment of suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge. For the sake of convenience of description, only the parts related to the embodiments of the present invention are shown. For the specific technical details not disclosed, please refer to the method part of the embodiments of the present invention. The control device can be a control device formed by various electronic devices.

[0108] Furthermore, the present invention also provides a computer-readable storage medium. In an embodiment of the computer-readable storage medium according to the present invention, the computer-readable storage medium can be configured to store a program for executing the method embodiment of suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge. The program can be loaded and run by a processor to implement the method of suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge. For the sake of convenience of description, only the parts related to the embodiments of the present invention are shown. For the specific technical details not disclosed, please refer to the method part of the embodiments of the present invention. The computer-readable storage medium can be a storage device formed by various electronic devices. Optionally, the computer-readable storage medium in the embodiments of the present invention is a non-transitory computer-readable storage medium.

[0109] Furthermore, it should be understood that since the settings of the respective modules are only for illustrating the functional units of the device of the present invention, the physical devices corresponding to these modules can be the processor itself, or a part of the software in the processor, a part of the hardware, or a part of the combination of software and hardware. Therefore, the number of each module in the figure is only illustrative.

[0110] Those skilled in the art can understand that the respective modules in the device can be adaptively split or combined. Such splitting or combining of specific modules will not cause the technical solution to deviate from the principle of the present invention. Therefore, the technical solutions after splitting or combining will all fall within the protection scope of the present invention.

[0111] So far, the technical solution of the present invention has been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present invention.

Claims

1. A method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge, characterized in that, The wind turbine blade includes: an airfoil main body, a movable connecting member, and a flexible trailing edge portion connected to the airfoil main body through the movable connecting member. The method includes: Obtain a model of the deformation of the trailing edge portion, where the model of the deformation of the trailing edge portion at least reflects the relationship between the end deformation angle of the trailing edge portion and the surface point coordinates of the trailing edge portion; Obtain a control strategy according to the model of the deformation of the trailing edge portion. The control strategy includes: changing the end deformation angle of the trailing edge portion according to a preset periodic function, where the periodic function reflects the relationship between time and the end deformation angle of the trailing edge portion; Based on the control strategy, control the trailing edge portion to change the end deformation angle of the trailing edge portion with the movable connecting member as a fulcrum to suppress the flutter of the wind turbine blade; The method for constructing the model of the deformation of the trailing edge portion includes: Set a section along the chord line of the airfoil main body; Obtain the angle of the end deformation of the trailing edge portion and the length of the chord line of the trailing edge portion; Based on the angle of the end deformation of the trailing edge portion, obtain the first central angle of the first virtual sector formed by the end of the trailing edge portion as the first endpoint, the movable connecting member as the second endpoint, and the tangent point; Based on the length of the chord line of the trailing edge portion and the first central angle, obtain the first radius corresponding to the first virtual sector; Obtain the original coordinates of the surface point of the trailing edge portion and the first arc length from the mapping point of the surface point on the chord line of the trailing edge portion to the second endpoint; Based on the first radius and the first arc length, obtain the deformation angle of the mapping point of the surface point on the chord line of the trailing edge portion; Based on the deformation angle of the mapping point of the surface point on the chord line of the trailing edge portion, obtain the second central angle of the second virtual sector formed by the mapping point of the surface point on the chord line of the trailing edge portion as the third endpoint and the second endpoint as the tangent point; Based on the deformation angle of the mapping point of the surface point on the chord line of the trailing edge portion and the first radius, obtain the second radius of the second virtual sector; Based on the original coordinates of the surface point of the trailing edge portion, the second central angle, the deformation angle of the mapping point of the surface point on the chord line of the trailing edge portion, and the second radius, obtain the surface point coordinates of the trailing edge portion.

2. The flutter suppression method for a wind turbine blade based on trailing edge deformation according to claim 1, characterized in that, The method further includes: Obtain the current wind speed and / or the change rate of the current wind speed; In response to the current wind speed and / or the change rate of the current wind speed satisfying a preset control start condition, execute "Based on the control strategy, control the trailing edge portion to change the end deformation angle of the trailing edge portion with the movable connecting member as a fulcrum".

3. The method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge according to claim 2, wherein The method further includes: Obtain the vector wind speed in real time; Where the method for obtaining the control strategy includes: Based on the vector wind speed and the model of the deformation of the trailing edge portion, obtain the control strategy.

4. The method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge according to claim 3, wherein The "Based on the vector wind speed and the model of the deformation of the trailing edge portion, obtain the control strategy" includes: At least simulate based on the vector wind speed and the model of the deformation of the trailing edge portion to obtain the offset displacement and flutter angle of the blade flutter; By adjusting the magnitude of the end deformation angle of the trailing edge portion, make the offset displacement and flutter angle of the blade flutter meet the preset requirements.

5. The method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge according to claim 3 or 4, characterized in that, Where the material used for the trailing edge portion is a flexible material, and the flexible material is used to make the chord line of the trailing edge portion approximate to an arc when the end deformation angle of the trailing edge portion is not zero.

6. The flutter suppression method for a wind turbine blade based on trailing edge deformation according to claim 5, wherein The original coordinates of the surface points of the trailing edge part only have a vertical coordinate, where the vertical coordinate is set along the direction perpendicular to the blade length.

7. The flutter suppression method for a wind turbine blade based on the deformation of the trailing edge part according to claim 5, wherein The step of "obtaining the coordinates of the surface points of the trailing edge part based on the original coordinates of the surface points of the trailing edge part, the second central angle, the deformation angle of the surface points of the trailing edge part, and the second radius" includes: x1 = rcosα - y0sinβ y1 = rsinα + y0cosβ, where x1 and y1 are the coordinates of the surface points of the trailing edge part, α is the deformation angle of the surface points of the trailing edge part, β is the second central angle, r is the second radius, and y0 is the original coordinate of the surface point at the end of the trailing edge part.

8. A control device, comprising a processor and a storage device, the storage device being adapted to store a plurality of computer programs, characterized in that, The computer program is adapted to be loaded and run by the processor to execute the method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge part according to any one of claims 1 to 7.

9. A computer-readable storage medium storing multiple computer programs, characterized in that, The computer program is adapted to be loaded and run by the processor to execute the method for suppressing the flutter of a wind turbine blade based on the deformation of the trailing edge part according to any one of claims 1 to 7.

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