Mitigation of In-Plane Vibrations in Large-Scale Wind Turbine Blades with a Track Tuned Mass Damper

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Introduction
Energy is a necessity to drive the sustainable development of the global society [1] and economy.Among many regenerative energy resources, wind power has become a regenerative energy resource that can greatly reduce carbon emissions [2] and fossil fuel consumption due to its unique advantages.Wind energy is harvested by wind turbines to generate electricity.Meanwhile, the industry's net electricity generation has steadily increased.Based on the most recent data provided by GWEC, China's installation capacity for wind output has been in the forefront of the world by 2022.
To harvest more energy and cut energy costs, many contemporary multimegawatt wind turbines are engineered with progressively bigger blades [3], rotors, and towers [4].Te larger blade produces serious vibration under wind loading, which degrades the lifetime of the wind turbine and induces blade fatigue.
Under some extreme conditions, a catastrophic complete collapse of the wind turbine can occur.Under external wind loading and blade gravity, the vibration modes within the blades are categorised as fap-wise (the out-of-plane vibration), edgewise (the in-plane vibration) modes, and torsion.Flap-wise vibrations are efectively dampened aerodynamically during regular operational [5] state, rendering the vibration to be quasistatic [6].In contrast, inplane vibrations associated with low aerodynamic [7] and structural damping will lead to increased blade damage.As shown in Figure 1, due to the special structure form of larger wind turbine blades, the combination of damping caused by the structure and damping caused by aerodynamics in the direction of in-plane vibrations is far less than that in the direction of fap-wise [8], which easily leads to the blade's destruction caused by in-plane vibrations.Te in-plane vibrations will afect the power output [9] of turbines and the potential catastrophic blade failure, which have also been experimentally demonstrated.Hence, in-plane vibrations have become a particularly signifcant consideration [10] for wind turbine blades to avoid fatigue damage.
Because of its signifcance, many scholars at home and abroad began to pay attention to the vibration control of blades from various angles.Te current research studies are mainly carried out from three aspects: improving the traditional pitch control strategy, designing a reasonable vibration control device, and changing the skin material of blades.For the vibration damping designs of blades, the variable pitch control system, with the function of maintaining the stable and safe operation of blades, is the most mature one in the development process of the wind turbine.Te variable pitch control system reduces blade vibration [11] under diferent wind speeds by altering the pitch angle of blades and the angle of attack of wind loading on the blades, thereby maintaining a stable blade root torque and capacity power [12].Te blade can be safely protected by loss of wind energy utilization efciency under high wind speed.Recently, several endeavours focused on the variable pitch control system.A groundbreaking pitch control scheme has been introduced for a wind turbine to decrease the blade root load during variable speed operation [13].As the constant increase of impeller diameter, an autonomous pitch control approach has been devised to enhance the quality of power generation and prolong the life of wind turbines [14] under unbalanced load.However, due to the limitation of practical technologies and theory, the vibration mitigation performance of variable pitch control systems for blade vibration is limited.Bossanyi [15] pointed out that the variable pitch control system can only reduce part of the torque of the blade root in small blades.However, the inertia torque at the blade root under dynamic excitation increases due to the longer blade, which increases the braking force required by the pitch control system, a braking delay, and a weakening efect.With the growth of larger wind turbines, researchers focus more on mitigating wind turbine blade vibration by various methodologies.Among these, intelligent damping materials are gradually applied in the vibration reduction control of buildings [16], machinery [17], and other industries because of a series of advantages, such as self-adaptiveness, fast response, and self-judgment.Nevertheless, intelligent damping materials cannot fully meet the requirements of aerodynamic performance optimization and lightweight and high strength materials.By adding damping devices to increase the damping energy consumption of the structure itself, the vibrating power from structure is dissipated by the supplemental damping control devices.Much research has been carried out into active, semiactive, and passive control devices for mitigating the blade in-plane vibrations.Although the relevant numerical research has achieved good results, the high price and power demands limit the widespread installation of active as well as semiactive systems in wind turbine blades.In general, a tuned mass damper (TMD) holds an advantage over active and semiactive systems, and in that, it requires no external energy input, which is widely applied in the high-rise building [18] as well as long-span structures, such as Sydney TV Tower in Australia and John Hancock Building in the United States [19].Te vibration reduction rate of TMD in wind-induced structural engineering can reach about 50%.With the diversifcation of TMD forms [20,21] and the further promotion of application scope, many scholars are committed to applying TMD to hollow structures such as blades, nacelles, and towers.Fitzgerald et al. [22] frstly proposed to apply TMD to blade vibration reduction.Te analysis shows that the reduction rate of blade tip displacement could reach about 39%.Later, an active TMD damping control system linked to the inner wall we at the blade tip by fexible cable [23] was proved to efectively reduce displacement from the blade's tip.Nevertheless, the narrow blade's tip space of the wind turbine cannot efectively meet the displacement required for TMD.Cong and Murtagh et al. [24,25] put forward the installation of multiple TMDs in wind turbines, which solve the problem of limited TMD space in the web of blades.Dinh and Basu [26] used TMD to conduct in-depth investigation on passive vibration suppression of wind turbine tower.He simplifed the wind turbine to a mass series model with multiple degrees of freedom and added TMD at the appropriate position of the model to indirectly lessen the irrational amplitude of blades by adjusting the overall motion displacement of the wind turbine.To better reduce the in-plane vibrations of blades, Zhang et al. successively proposed a cylindrical TLD [27], CLCD [28], and a box TLD [29] to suppress the inplane vibration of blade in real time.Te research shows that these devices can efectively reduce the dynamic vibration of blades in the in-plane direction.Later, Zhang and Larsen

In-plane
Out-of-plane proposed the mathematical expressions for attaining the best calibration (tuning) of the rotational inertia double-tuned mass damper (RIDTMD) [30] to suppress in-plane vibrations within a wind turbine blade in action and compared them with the optimized RIDTMD and optimal TMD.Te analysis revealed a greater capability of the RIDTMD to dampen blade vibrations compared to the TMD.Diferent vibration reduction methods achieve diferent vibration reduction efects.Qiao et al. [31] performed numerical analysis of the model using the fnite element method and proposed an active vibration system to efciently suppress the vibration of smart blades by obtaining the displacement responds from piezoelectric actuation and piezoelectric sensors.Bolat and Sivrioglu [32] introduced a new active damping structure with magnetorheological layer patch, and the results indicated that the scheme was efective in mitigating vibrations of a small-scale blade.Sivrioglu et al. [33] pointed that mixed norm robust controllers attached to blade structure can successfully attenuate the vibrations of the blade.Staino et al. [34] proposed the double control system of an active cable connection system and pitch control system.When the participation ratio of the double control system is 0.6 and 0.4, respectively, the damping rate in the blade tip displacement is capable of reaching 63%, and the power loss can only reach about 15%.Cong [35] designed a spatial H ∞ controller and a pair of active cables installed at each blade tip to reduce the vibration amplitude.Jokar et al. [36] proposed an actuator confguration which can generate out-of-plane and in-plane bound control loads and introduced a new perturbation observer to assess bounds perturbations for decreasing the HAWT blade vibration.Chen et al. [37] reduced the blade tip displacementcaused torsional vibration by setting a rotating eddy current device inside the blades to achieve energy dissipation.
In the past few years, there has been growing research focus on the vibration damping of blades, focusing on the efect of passive control devices in proposed control strategies.However, there are relatively few studies on the parameters of passive control strategies, especially the investigations regarding the optimization of the parameters in the control strategies.On the contrary, the main tendency for in-plane vibrations control is the design of an active damping control device and the application research of new intelligent material.However, no matter how simple and efective the active device is, its defects, i.e., needing constant external energy, are inevitable.Considering the wind turbine blades in a rotating state for a long time, it is relatively difcult to design the external energy supply.In the area of vibration damping technology, the emergence of new intelligent materials greatly enriches the vibration reduction methods, but there are relatively few intelligent materials to meet the requirements of wind turbine blades' aerodynamic performance optimization, lightweight as well as high strength.
In view of the above problems, this study proposes and investigates a new tuned mass damper for in-plane vibration mitigation of blades.Te structure of this paper is as follows: Section 2 explains the composition, model connection, theoretical analysis model, and working principle of the damping control device.Section 3 selects a single blade of a 3-blade horizontal-axis wind turbine as the object of study and simplifes it to a generalized single-degree-of-freedom system, involving just one bending deformation in the inplane direction.Coupled with Hamilton's principle, the Euler-Lagrange models of motion blades in uncontrolled and controlled states are derived to solve the motion equation of the wind turbine blades under external excitation.Taking into account the efect of rotation afecting the wind velocity, the numerical investigations of the mean wind velocity and the fuctuating wind velocity of the rotating blade are conducted in Section 4, where the wind velocity at each sampling point on the blade.In Section 5, generalized nonconventional powers applied to a solitary blade, concerning the assumed degrees of freedom, primarily consisting of components related to wind loading, gravity, and damping force.Te damping in the direction of the assumed degrees of freedom tends to be relatively small, so the damping force is not considered.Te wind loading and gravity are mainly calculated for the rotating blade.Section 6 analyzes the infuence law of the mass ratio, damping ratio, and installation position of the device on the vibration damping efciency of the displacement at the blade tip.Te vibration mitigation performance designed by the optimal parameters is also analyzed.Lastly, Section 7 sums up the key results of this paper.

Configuration of Proposed TMD
Currently, a broad spectrum of vibration control mechanisms is used in building structures [38], bridges [39], and marine engineering [40].TMD is frequently used as vibration damping devices in the area of vibration.Its working principle is as follows: the structure drives the TMD system to move under external excitation, and the inertia power generated by the TMD system acts on the structure in response to reduce the vibration amplitude of the structure, so as to fulfl the aim of mitigating.A novel tuned mass damping control device, installed in the available space within the blade, is proposed in this paper for mitigating in-plane vibrations.Te proposed device is directly installed in the looped frame constituted of the inner web and the main beam of the blade.On the premise of not afecting the aerodynamic characteristics of the blade, the vibration reduction control is investigated.Te confgurations of the proposed device are shown in Figure 2. It is mainly composed of eight sets of spring systems, four sets of track systems, and a mass block.Te sleeve is installed on the mass block which is installed on the track system by the sliding shaft passing through the sleeve.Te spring passes through the sliding shaft.Both ends of the spring are, respectively, installed on the inner wall of the web as well as the sleeve through the fxing ring, so as to facilitate the connection of various components and prevent the collision between the mass block as well as the inside of the web.Te mass block is contacted with the blade web inner wall by sleeve and spring.When the spring connected the fxed ring and the mass block at the appropriate position is in the minimum compression state, it Structural Control and Health Monitoring is realistic to fully utilize the space in the wind turbine during the operation of the mass block.Because of its simple structure form, the device is convenient in site construction and can reduce the blade vibration efectively under reasonable design.Te damping system designed separately without occupying the space of the track system is conducive to the best performance of the mass block.Te mass block has a small volume and occupies a small amount of internal space of the blade during operation, which has a relatively small additional infuence on the aerodynamic performance of the blade.

Theoretical Model of Proposed TMD
In order to strictly guarantee that the mass block has no contact with the inside surface of the blade web while in action, the damping device needs to be installed in the appropriate place at the blade.As shown in Figure 3, the global coordinate system (X T , Y T ) is created in the appropriate position of the airfoil where the damping control device is located, in which X T axis is along the chord direction of the blade element, and Y T axis is along the vertical center line of the mass block in the static state.In Figure 3, b T is defned as the efective chord length of the airfoil in which the vibration control device is positioned, taking a quarter of the actual chord length L. d Ti represents the displacement of the mass block of the vibration control device during operation.m T � μM is the mass of the mass block.
T m T is the designed stifness.Here, μ is the mass ratio between the mass of the mass block and blade modal mass in the vibration damping system.ξ is the damping ratio of the vibration control device.f T is the frequency ratio of both the frequency of the vibration damping system and the blade modal frequency.
Te National Renewable Energy Laboratory (NREL) 5 MW baseline wind turbine is chosen to be the prototype to simulate in-plane responses of the blade.Te proposed model and control schemes were simulated in MATLAB (Te MathWorks Inc, MA, USA).Te specifc details of the wind turbine are displayed in Table 1.
Te blade is simplifed as a cantilever beam mounted on the hub, and the defection and slope of the modal shape at the hub are zero.According to the literature [22], the modal shape function of the blade is where x � r/L, r is the blade's length across the radial distance from the hub.Te modal shape is shown in Figure 4.An Euler-Lagrangian wind turbine computational model, which relies on an energy equation, has been created, taking into account the structural dynamics of the device and the relationship between in-plane and out-of-plane blade vibration.Te wind turbines are complex power production systems, and the blades are in a state of rotation under wind, which is diferent from building structures in the civil engineering industry.In this study, the blade in a 3blade horizontal-axis wind turbine condensed as an Euler-Bernoulli beam, is considered as a cantilever shell structure installed on the hub.Te blade is considered to be a generalized system with a single degree of freedom and only has a solitary fexural deformation along the in-plane direction.After the hub rotates around the center point, the Euler-Lagrange motion model derived from Hamilton's principle is applied to solve the equations of motion under external action.Te equation of motion, in which the Euler-Lagrange formula is a generalized energy equation, indirectly refects the possible coupling relationship between the various degrees of freedom, that is, Here, T represents the kinematic energy of the frame, V represents the potential energy, q i represents the generalized coordination, and Q i represents generalized force at the ith degree of the freedom system.
To efectively diferentiate the diferent states of blades before and after using the TMD vibration reduction control device.Te situation of the wind turbine without the TMD vibration reduction device is characterized as the out-ofcontrol case, and the wind turbine with the TMD vibration reduction control device is defned as the controlled case.Te dynamic models of blades are derived separately for uncontrolled and controlled scenarios.

Derivation of Blade Dynamic Model without Control.
Generally, the typically generalized coordinates are selected in the system to facilitate the calculation of the reference point displacement.In this study, because the blade has infnite degrees of freedom, only the in-plane tip displacement of blade is selected as the generalized coordinate for the study.Te wind turbine blade would be simplifed to a single degree of freedom system for analysis.It is assumed that only a single bending deformation form can be generated.To make the analysis easier, two reference frames are created.One corresponds to the global plane coordinates (X, Y) in the plane, while the second represents the rotational rectangular coordinate (x, y) alongside axis of the blade.Te initial point for both coordinate reference frame is the hub pivot points, as shown in Figure 5.
To maximize the alignment of the wind turbine with the single-degree-of-freedom system, it is assumed that the deformation of the system only is corresponding to the displacement shape function where ϕ in (x) is the displacement shape function of the frst blade deformed along the rotation plane and q i,in (t) is the generalized coordinate of the in-plane blade's tip.

Potential Energy of Wind Turbine
Blade.Following the strain potential energy, V � (1/2)kx 2 , where k is composed of the elastic stifness coefcient as well as the geometric stifness coefcient, x is the displacement required to generate the strain potential energy.Combined with the generalized displacement defnition of blades, the potential energy expression of blades can be obtained as k e,in is the in-plane elastic stifness of the blade.k gr,in represents the in-plane geometrical stifness induced by the centripetal force of the blade.k g,in is the in-plane geometrical stifness generated by the gravity of the blade.Following the principle of virtual work, if a device is in a state of equilibrium under the infuence of an external force, the virtual work of an external force is equal to the virtual deformation work accepted by the deformable body when the system produces a small virtual displacement satisfying the constraint condition.Tat is, W E � W I .Ten, the stifness factors of the blade are solved.Supposing that the unit displacement at blade's tip occurs, that is η(L)� 1, the inner force moment produced within the entire blade is where EI in represents in-plane bending stifness of the blade; L is the blade's length.Assuming that the blade tip induces a virtual displacement of δη b , it can be derived from equation ( 3) that the virtual displacement produced by the whole wind turbine blade can be described as Combining the correlation of displacement and curvature in materials science, it can be concluded that the virtual curvature generated by hypothetical displacement is Following the principle of the deformable body virtual work, when the virtual displacement at blade tip is δη b , the virtual work of external force W I and the virtual strain work W E obtained by the deformed object are calculated as follows: If equations ( 7) and ( 8) are equal, the elastic stifness coefcient in-plane 6 demonstrates that the δe shows how the blade shifts axially through elastic deformation caused by vibration.Te dx microsection is chosen at any location in the axis direction of the blade.It is assumed that the dδ e represents the relative displacement induced by the microsection due to outside forces, then Following the principle of deformable body virtual work, the virtual work W I of the external force of blade and the virtual deformation work W E are given as follows: If equations ( 10) and (11)  2 dx is the coefcient for the geometric stifness of the blade, in which N(x) is the axial force of the blade.
Te axial load on the blade can be split into the centrifugal load outward fow and the gravitational force radial inward fow of the component, as shown in Figure 7. Assuming that the dx is chosen at any location x of the blade for uniform circular motion, dF(x) � m(x)dxΩ 2 x represents the centrifugal power produced by the microsection, in which Ω is the angular velocity of the blade rotation, then the ith blade azimuth can be expressed as Ψ i � Ωt + (2π/3)(i − 1), the entirety of the blade's centrifugal force at position x can be obtained by integrating along L− x, that is, x gm(ς) cos Ψ i dς represents the radial axial force induced by gravity on the blade, where m(ς) is mass per unit of distance in the radial direction of the blade, so the geometrical stifness is Accordingly, the potential energy may be obtained as

Kinetic Energy of Wind Turbine Blade.
For blades in rotation, the velocity is calculated in the stationary reference frame (x, y), then According to the calculation equation of the kinetic energy, the blade's kinetic energy may be obtained as By inserting equations ( 13) and ( 15) into equation ( 2), the dynamic model of the blade for the uncontrolled case can be obtained as where the expressions of each parameter are explained as follows: Q represents the outside load acting on an individual blade, i.e., Q � Q i,g + Q i,in , where Q i,g is the gravity load along the in-plane direction and Q i,in is the wind loading along the in-plane direction.

Derivation of Blade Dynamic Model with Control.
Te vibration reduction control device, which is simplifed as a TMD vibration reduction system with damping and stifness installed at a particular location on the blade, is installed in the radial direction x 0 of the blade.As shown in Figure 8, the diference between the displacement of the blade at x 0 and the motion displacement of the TMD is x Ti (t) � ϕ in (x 0 )q i,in − d Ti , where d Ti is the generalized coordinate of the TMD.
Combined with equation ( 4), the potential energy in the coupled dynamic model of the blade and vibration reduction control device can be obtained as Considering the efect of blade rotation on the TMD's velocity, the velocity generated by vibration control under external excitations is where k Ti is the stifness of the vibration reduction control device.

Structural Control and Health Monitoring
Combined with equations ( 15) and ( 18), the kinetic energy term in the coupled dynamic model of wind turbine blade as well as vibration reduction control device can be obtained as where m T stands for the mass of the mass block in the vibration reduction control device.Structural Control and Health Monitoring By substituting equations ( 16) and ( 18) into equation ( 2), the dynamic model of the blade in the controlled situation may be acquired as where b T is defned as the efective chord length of the airfoil at the place of the vibration control device, taking a quarter of the actual chord length L T .d Ti represents the displacement of the mass block of the vibration damping system during operation.

Wind Field Simulation considering Blade Rotation
Te spatial wind feld is assumed to be a standardized random feld with certain time-varying characteristics.For most large building structures in a static state, the wind speed acting on these buildings only needs to consider the time-varying characteristics of wind velocity at every point and the correlation between spatial points when the spatial position is determined.However, for the rotating blade, the spatial position changes periodically with time.Te wind velocity acting on the blade needs to consider the timevarying characteristics of wind velocity at each point and the correlation between spatial points.Meanwhile, it also needs to note the impact of the operation point on the periodic change of the spatial position of the blade rotation [41].
From a functional perspective, this paper focuses on the inplane vibration damping of the blade in a rotating state.To meet the characteristics of natural wind as much as possible, the infuence of the rotation efect of the blades on wind speed is considered.It is supposed that the wind wheel is in a uniform compressible and isotropic turbulent wind feld.
Generally, the natural wind velocity includes the mean wind speed calculated according to the long-term statistical law and the fuctuating wind speed simulated according to its power spectrum.In this study, four sampling points were selected for each blade while the blade is turning.Each sampling point was selected based on the blade element composition of the blade.Te specifc distribution is shown in Figure 9.

Simulation of Mean Wind Speed of Rotating Blades.
Te mean wind velocity is afected by the ground roughness and the height from the ground.Te phenomenon that the wind velocity changes along the height is known as wind shear.At present, there are two kinds of wind shear models: the exponential model and the logarithmic model.
According to the IEC Standard as well as the GL Standard, it is pointed out that the exponential model is more suitable for the practical mean wind velocity.Terefore, the exponential model is applied to gain the mean wind velocity of the wind turbine blade in this paper.Te reference point is selected as the hub midpoint height of wind turbine.Te model that takes into account the wind shear efect follows an exponential function and is denoted as where the mean wind speed at heights of U(z) and U h (z h ) above the ground z as well as z h , respectively, and z h represents the height of the center point of the hub.z � z h + r cos α represents the periodically changing height of a certain point on the wind turbine blade.
In this research, if the rated wind speed of the hub is U h � 12m/s, the mean wind velocity acting on each point of the blade is displayed in Figure 10.It should be noted that the rated wind velocity adopted here is not 11.4 m/s in Table 1.Because the average wind speed was simulated using the exponential model, according to formula (20), then the rated wind velocity U h � 12m/s at the hub center point was used to simulate the average wind velocity at every sampling point.On the same blade, the mean wind speed of each point is in the same phase, and the peak value of the average wind speed increases with the increase of the blade radius.In the process of blade rotation, the mean wind speed varies periodically.
Structural Control and Health Monitoring 4.2.Blade Rotation Efect.Because of the infuence of air pressure and the ground roughness, the wind velocity fuctuates in the high-frequency part for a short time, which is usually expressed by the fuctuating wind speed.During the blade's rotational operation, when the pulsating wind speed considers the longitudinal wind velocity only, it can be simplifed as a stationary ergodic stochastic process related to time as well as space, which is calculated by using its power spectrum.Let the rotation frequency of the blade be f 0 .Te wind velocity time history sample at moment t in radial r of blade is u 1 .Te wind velocity time history sample at moment t + τ be u 2 .Taking the Von-Karman spectrum as the source spectrum, the self-spectrum, as well as the crossspectrum of the rotating sample spectrum considering the efect of wind turbine blade, are, respectively, where c(τ, f), refecting the change of amplitude spectrum, is a coherent function, and can be obtained using the Davenport exponent form where α is the attenuation coefcient.According to the IEC Standard, α � 10; U is the mean wind speed; d(τ) and d ′ (τ) represent the distance between two sampling points, where )|, and α � 2πf 0 τ.α 0 is the initial phase, as shown in Figure 11.
According to IEC, the integral scale of turbulence is L u � 8.1∆ 1 , where ∆ 1 is the scale of longitudinal turbulence, and selected as 42 m.Te standard deviation of longitudinal turbulence is σ u � I ref (0.75U h + 5.6), and I ref denotes the expected value of turbulence is 0.16 at a wind velocity of 15 m/s.
Te rotating sample spectrum is composed of an infnite number of source spectrum that are translated by an integer multiple of the rotating frequency of the wind turbine blade and then multiplied by the corresponding weighting coefcient.Te mth mode, which is the Fourier expansion coefcient of the coherence function, is 1/2π  2π 0 e − im(2πf 0 τ+α 0 ) c ′ (α, f − mf 0 )dα after shifting the weighting coefcient, where e − θi(f− mf 0 ) is the phase delay caused by rotation efect and e imα 0 is initial phase information.When α 0 � 0 and r 1 ≠ r 2 , it represents the cross-spectrum from various dots on the same blade.When α 0 ≠ 0, it represents the cross-spectrum between various dots on distinct blades.When α 0 � 0 and r 1 � r 2 , it represents the self-spectrum of each point on the same blade.As shown in Figure 12, the mth mode has a peak near the m-octave of the rotation frequency, and the peak value gradually falls as the value of increases.Tere is a decrease in the m-order mode, which will result in the decrease phenomenon of the rotation sample spectrum at the mth rotation frequency.
Figure 13 describes the relationship between the selfspectrum and cross-spectrum of the rotating sample spectrum between diferent sampling points on the same blade and the relationship between the cross-spectrum of each point on diferent blades.On the same blade, the selfspectrum of a sampling point and the cross-spectrum of another sampling point are quite diferent.In the highfrequency part, the cross-spectrum decreases rapidly and is gradually close to 0. Under the condition of the same radius of diferent blades, the changing trend of the crossspectrum between the two sampling points and any one of the self-spectrums is the same but slightly diferent from that in the high-frequency part, which indicates that the angle between blades has little infuence on the crossspectrum between sampling points of diferent blades.Te variation trend between the self-spectrum Von-Karman and source spectrum in rotating sample spectrum is the same.Due to the infuence of the coherence function in the rotating sample spectrum, the peak value of the rotating sample spectrum appears to drop at a high frequency, and the energy distribution of the rotating sample spectrum is at a high frequency relative to the Von-Karman spectrum.

Simulation of Fluctuating Wind Speed of Rotating Blade.
Te power spectrum mainly describes the statistical characteristics of the energy distribution over frequency in the random process.Tere is a great diference between the turbulent wind speed spectrum of the fxed point and that of the rotating blade, the energy distribution of which has changed fundamentally.To accurately explore the impact of the rotating efect on the wind load applied on the wind turbine, the rotation sample spectrum is employed to simulate the wind speed of the wind feld where the wind turbine is located on the basis of the Von-Karman spectrum.Te simulated wind speed is solved by Cholesky decomposition.For the calculation of the fuctuating wind feld, the corresponding amplitude spectrum can be obtained by calculating the modes of the self-spectrum and cross-spectrum of each point in the rotating sample spectrum.Terefore, a one-dimensional multivariable Structural Control and Health Monitoring amplitude-spectrum matrix is constructed from the autospectrum and cross-spectrum of the rotating sample spectrum as follows: Te matrix of equation ( 22) is decomposed by Cholesky factorization, S uu (f) �  H(f)  H T (f), where  H(f) is the lower triangular matrix.
Te harmonic superposition method is a mathematical simulation scheme based on the summation of a series of triangular series and using a discrete spectrum to approximate the target random process.Te fuctuating wind velocity applied on the wind turbine blade may be viewed as a process driven by the rotating sample spectrum.According to Shinozuka's theory, the process may be described as where j is the count of simulation points; M is the frequency division count of fuctuating wind; f pq is the double exponent frequency.
∆f � f u /M is the frequency step; f u is the cut-of frequency, and its value is determined by the area ratio of interval [0, f u ] and interval [0, ∞] in the power spectrum of rotating samples.Generally, the ratio needs to be close to 1, which can be determined according to the criterion of |df, which ε is far less than 1.In this study, four sampling points were taken on each blade, with m � 2400 and f u � 10.According to the sampling theorem, the time steps ∆t ≤ (1/2f u ) when the time history sample is generated.θ(f) � 2πfτ is phase delay parameters.α pq is a random phase angle, which is evenly distributed on the interval [0, 2π].
Te wind velocity of the blade is calculated by rotating sample spectrum which can transform the dynamic process of the rotation of blade into a static process.Tus, the impact of the blade rotation on the subsequent wind vibration reaction of the blade has no need to be included.In this study, a one blade is used to generate the wind velocity.Te specifc distribution of sampling points is shown in Figure 14.Selecting the sampling point 1 as an example, the fuctuating wind velocity at this point calculated by equation ( 24) is shown in Figure 15, and the mean wind velocity may be combined with the turbulent wind speed as shown in Figure 16.

Blade Load Analysis considering the Blade Rotation
Te wind turbines operate primarily by the rotation of blades under external wind loading.Te blades are afected by wind loading and gravity load during operation.In the paper, the equation describing the dynamical motion of a lone blade is formulated from Hamilton's principle.Te generalized nonconservative force in the presumed degree of freedom is primarily categorised into three components: wind loading element, gravitation element, and damping force.Since the damping in the direction of the assumed degrees of freedom is relatively small, damping force is not considered.

Calculation of Generalized Wind Loading.
In accordance with the blade element theory, any blade can be subdivided into multiple sections with diverse blade elements in order to investigate the force and moments on every blade element.Te external power applied on each blade may be acquired through the process of integration in the direction of the blade's wingspan.It is generally assumed that there is no radial airfow between each blade element, i.e., the interaction infuence between each blade element is ignored.Te lift factor of the blade primarily governs the aerodynamic power.Te force exerted by the blades on the airfow is constant compared with the rotor.In this study, the radius of the impeller is L. v ∞ is the incoming wind speed.Te axial induction coefcient is represented by a. β is the tan φ � (v ∞ (1 − a)/Ωr(1 + a ′ )) pitch angle.a ′ represents the tangential induction coefcient.φ denotes the angle formed by the incoming wind velocity and the blade element of the rotating plane.Terefore, the infow angle is as follows.v ∞ (1 − a) represents the functional wind velocity at a length r from the hub, and the induction speed is Ωr(1 + a ′ ).α � φ − θ stands for the angle of attack to the blade element airfoil at the local level, c represents the chord length, C L stands for the lift factor, and C D stands for the aerodynamic drag factor, as depicted in Figure 17.Te airfoil's relative velocity may be represented as follows: where the lift force D and drag force L generated by each blade element's unit length are D � (1/2)ρV 2 cC d and L � (1/2)ρV 2 cC l , respectively.In general, only the traction force p T , which runs in parallel with the rotation plane, and the propulsive force p N which is at a right angle to the rotation plane are taken into account as a rotating blade.As displayed in Figure 18, the lift force and drag force can be broken down across two directions, namely, p T � L sin ϕ + D cos ϕ, p N � L cos ϕ + D sin ϕ, then the towing power on the entire ith blade is P i,in �  L 0 p T,i (x, t)ϕ in (x)dx.In accordance with the law of virtual merit, δW � δq i,in P i,in represents the virtual merit performed by the aerodynamic payload across the generalized degree of freedom.Terefore, Q i,in � (δW/δq i,in ) � P i,in represents the generalized aerodynamic load applied to the blade.Axial induction factor a ′ and tangential induction coefcient are calculated according to the equation. where ) means the chord length of blade element and B stands for the count of blades.
To gain more accurate calculation results, there is a need to correct various inductions.First of all, the blade element momentum (BEM) theory used here is founded on the supposition that the blade is infnite, but the actual blade has a fnite length.In order to make the BEM theory meet the actual situation, the Prandtl tip hub loss factor F is proposed, i.e., F � 4/π 2 cos − 1 (e (B(R− r)/2r sin ϕ) ) • cos − 1 (e (B(r− R hub )/2R hub sin ϕ) ), where r hub is the radius at the hub.Considering the Prandtl tip hub loss factor, the axial induction factor a and tangential induction coefcient a ′ are expressed as Secondly, when Prandtl tip hub loss factor [42] is corrected and axial induction factor a > 0.4, momentum theory no longer applies in calculation.Hence, the Spera loss factor is proposed to be corrected; that is, axial induction factor a of the blade can be expressed as   Structural Control and Health Monitoring where K � (4F sin 2 ϕ/σC n ).
Combined with equations ( 30)-( 32), the axial induction coefcient, as well as the tangential induction factor of the blade element at P1 under turbulent wind velocity, is progressively acquired through the utilization of the blade element momentum theory, as displayed in Figure 19.Ten, the wind load applied on the blade element at P1 along the in-plane and out-of-plane directions can be obtained, as displayed in Figure 20.Te blades may experience wind load in a generalized manner from all directions by integrating along the length, as displayed in Figure 21.

Generalized Gravity Load.
Te gravitation exerted on the blade is decomposed along the blade's axial and tangential orientations.
In accordance with the law of virtual merit, the work performed by gravitation in the virtual displacement along the generalized degree of freedom is equal to δW g �  L 0 m(x)g sin ψ i δq i,in ϕ(x)dx, and then according to equation (33), the generalized gravitational force applied to the blade is Te generalized gravitation power obtained is displayed in Figure 22.
Assuming that the damping stress is proportional to the damping strain velocity, then the stress-strain relationship could be expressed as, σ � Ec_ ε, in which c is the damping coefcient and E stands for the elastic modulus.For the wind turbine structure in this article, the resistance coefcient of each blade can be expressed as c b � 2m b ω b ξ b and the drag factor of the tower stands for c n � 2m n ω n ξ n .Te virtual displacement induced by damping force is

Analysis of Factors Affecting Blade Damping Performance
Te vibration reduction system is built into the back-shaped frame between the blade's web and the main girder.Te peak value and standard deviation of the reaction are used as the evaluation indices.Te ratio of the frequency of the vibration damping system and the modal blade is set to 1.0 to explore the law of the mass ratio, damping ratio, and installation position of the device on the vibration damping efciency of the blade's tip displacement.

Infuence of Diferent Parameter Values on Blade
Vibration Reduction Performance

Efects of Installation Location and Mass Ratio.
Assuming that the damping ratio is ξ � 50%, the infuence law of installation position x 0 /L and mass ratio μ on the vibration attenuation efectiveness of blade tip displacement is explored.Figure 23 reveals the infuence trends of mass ratio and installation position on vibration reduction ratio.It is shown that when the mass ratio reaches in the range of 0.001∼0.01,the vibration damping ratio of peak displacement and standard deviation increase having the increase of installation position.When the mass ratio falls within the interval from 0.05∼0.10, the vibration reduction ratio of peak displacement as well as standard deviation rises frst and then falls as the increase of installation position.When the mass ratio is adjusted to be 0.03, the vibration reduction ratio of peak displacement as well as standard deviation increases frst and then decreases at a gentle stage with the increase of installation position.It is worth noting that the TMD is installed at 0.5, an infection point occurs in the curve with a large mass ratio.Tat is because blades made of lightweight and high-strength materials are variable-section cantilever rotating structures, and their stifness decreases as the size of the blades grows, which will cause the blades to be afected by the whipping efect.Tis leads to an infection point in the curve, which means that the damping ratio suddenly decreases.When the TMD having a large mass ratio is installed closer to the blade tip, it is challenging for the TMD to adjust the vibration frequency to the height frequency of the tip due to the limitation of the blade space, which leads to poor vibration damping efect for large mass Structural Control and Health Monitoring ratio.In the whole analysis process, when the mass ratio is between 0.01 and 0.03, the change level of the vibration damping ratio is relatively fat.Te closer the blade tip, the higher the vibration damping ratio is relatively.
Te vibration damping ratio of blade tip displacement of blades changes continuously with the value of mass ratio and installation position.When the vibration control device is designed, the maximum vibration reduction ratio is achieved with no loss of aerodynamic performance.Figure 24 shows the distribution range of the maximum vibration reduction ratio.Te fgure shows that when the mass ratio is about 0.01 and the installation position is in the range of 0.8∼1.0, the vibration damping ratio of the standard deviation of displacement may be up to 53.07%.When the mass ratio falls within the interval from 0.01 to 0.03 and the installation position is between 0.9 and 1.0, the peak vibration damping ratio of displacement can reach 49.73%.Terefore, when the damping ratio is selected as 50%, only considering the vibration damping ratio of blade tip displacement, the optimal mass ratio of the vibration suppression control device is 0.01 and the optimal installation position is around 0.9∼1.0.

Efects of Mass Ratio and Damping Ratio.
When the damping ratio is 50%, the relationship between the installation position x 0 /L and the mass ratio μ is investigated.Te relative parameter value of the mass ratio taken as 0.03 and the installation position taken as 0.84 is better.However, the optimal damping ratio of the vibration control design is not 50%.Terefore, when the installation position is 0.84, the correlation between the mass ratio and the damping ratio is explored.Figure 25 describes the impact of mass ratio and installation on the vibration reduction rate.Te fgure indicates that the vibration suppression ratio of the peak and standard deviation of the displacement frst show an increment of about 20%, then remain fat with the increase of the damping ratio, and fnally, the vibration damping ratio reaches the maximum when the damping ratio is about 20%.If the damping ratio is 20%, the vibration damping ratio of standard deviation and peak displacement increase frst and then fall as the mass ratio increases.
Figure 26 shows the distribution range of the maximum damping ratio.Te fgure shows that when the damping ratio ranges from 15% to 40%, the vibration damping ratio of the standard deviation at blade's tip displacement is 53.84%.When the mass ratio is close to 0.01, the vibration damping rate of peak displacement at the blade's tip is 49.92% when the mass ratio varies from 0.01 to 0.03.Terefore, it could be viewed from Figure 23, for the vibration suppression ratio of the tip displacement, the optimal mass ratio of the damping system is 0.01 and the optimal damping ratio range is 15%∼ 40% when the installation position is selected as 0.84.

Impact of Damping Ratio and Installation Location.
Based on the principle of the minimum mass ratio and making full use of the movement of the mass block running on the inside wall of the web, the mass ratio is assumed to be 0.02.From the analysis results in Figure 27, the correlation between the damping ratio and the installation position is analyzed.Figure 28 reveals the trend of the vibration suppression ratio with the damping ratio and installation position.It could be known from Figure 28 that the vibration damping ratio of standard deviation and peak displacement at blade's tip increase gradually with the installation position closer to the blade tip for a certain damping ratio.When the installation position x 0 /L is taken between 0.75 and 1.0, the changing trend of the damping ratio is relatively slow and maintains a relatively stable level.At the same time, for any fxed installation position, the vibration damping ratio of standard deviation and peak displacement rises frst and then falls as the damping ratio grows.In the whole process, when the damping ratio is 20%, the variation of damping ratio with the value of installation position is relatively fat.When the installation position x 0 /L is taken between 0.75 and 1.0, the vibration reduction ratio is relatively higher under each damping ratio.
Figure 27 shows the changing law of the damping ratio with the installation position and damping ratio.As seen in Figure 27, when the installation position x 0 /L of the vibration damping system is taken between 0.6 and 1.0, the vibration damping efciency of standard deviation and peak value of the blade tip will reach more than 40.06%, and the efect on the vibration damping rate is relatively small as the damping ratio rises.When the installation position is defned as 0.6 and the damping ratio ξ is set between 15% and 20%, the vibration damping efciency at the blade tip reaches 52.09%.Terefore, if the mass ratio becomes 0.02, the optimal parameter value to make the damping ratio maximum is as follows: the damping ratio is 20%, and the installation position is 0.60.

Parameter Optimization.
Figure 29 shows the variation pattern of peak displacement for the mass block.It could be clearly illustrated from the fgure that on the condition of the parameters μ � 0.01, ξ � 50%, and x 0 /L > 0.68, the mass block touches inside wall of the blade web when the vibration control device works, which cannot meet the design requirements.When the installation position is adjusted to 0.84 and the mass ratio exceeds 0.01, the mass block contacts just with the inside wall of the web in the operation.If the mass ratio is 0.03, the tendency of displacement about the mass block is relatively fat.While when the damping ratio is set to 50%, in order to guarantee that the mass block avoids contact with the inside wall of the web with the highest vibration damping efciency at blade tip displacement, the  Structural Control and Health Monitoring mass ratio μ could be set to 0.03 and the installation position x 0 /L should be set to 0.84 in combination with Figure 24. Figure 30 describes the variation pattern of peak displacement for the mass block as the mass ratio and damping ratio are varied.As shown in Figure 30, when the installation position is 0.84, the efective chord length of the relevant airfoil is constant, and the displacement of the mass block decreases as the mass ratio increases.If the mass ratio is above 0.02, the change law is relatively fat.In order to guarantee that the mass block avoids contact with the inside wall of the web in the operation process, in this analysis process, the mass ratio is not less than 0.02 and the damping ratio is greater than 50%, which can meet the design requirements.
For diferent parameter values, the displacement of mass blocks is diferent.Figure 31 shows the pattern of displacement variation for the mass block changed with damping ratio and installation position.From the fgure, the installation position is nearer to the blade's tip, and the displacement of the mass block is increased.By increasing the damping ratio, the displacement of the mass block falls gradually and the decrease values of each displacement decrease gradually.About the collision between the vibration control device and the inside wall of the web of the wind    Structural Control and Health Monitoring turbine, it can be found that when the damping ratio is set to 20% and the installation position of the vibration damping system is set as 0.65, as well as the peak displacement of the mass block in the operational process just touches with the inside wall of the web.Terefore, if the damping ratio is set as 20% and the installation position is set as 0.60 in the whole analysis process, there is no collision between the vibration control device during operation and the inside wall of the blade web, which satisfes the design demands.

Analysis of Vibration Absorption Performance under
Optimal Parameters.Te vibration control of the blade in the in-plane direction is carried out by a damping control device having a damping ratio of 20%, a mass ratio of 0.02, and an installation position of 0.60.Figure 32 reveals the displacement-time of the blade tip.Based on the data, the peak displacement at the blade tip reaches 2.46 m and the standard deviation reaches 0.81 for the without controlling the case.For the controlled case, the peak displacement of   Structural Control and Health Monitoring the blade tip is 1.22 m and the standard deviation reaches 0.36.In comparison with the uncontrolled condition, the peak displacement at the blade's tip experiences a reduction of 50.34% and the standard deviation experiences a reduction of 54.18% under the controlled condition.Figure 33 displays the time history of the base bending moment about the blade.It could be noted that the displacement at the blade's tip is reduced and the blade root bending moment is also efectively reduced during the period when the blade experiences elastic strain, which can avoid damage of the blade root.Based on the investigation of standard and peak values as the control criteria, the passive vibration damping device installed in the wind turbine blade has a positive efect on regulating the displacement at the blade tip.
Te TMD-based vibration reduction control device, which is installed on the inside wall of the blade web, aims to fully utilize the internal space of the blade during operation   Structural Control and Health Monitoring to avoid pounding.Te displacement of the mass block is shown in Figure 34.Te peak value of the operating movement of the mass block is 0.79 m, while the chord length of the radial position of the inside wall of the blade web is 3.26 m.After installing the vibration control device, the chord length for its operation is the net chord length, which is 0.84 m.Terefore, when the optimal parameter value is selected, the displacement of the mass block is not as much as the net chord length set above, which meets the requirements of vibration reduction analysis.

Conclusions
In this study, a TMD-based device is designed for vibration damping of the blade in the in-plane direction in the rotating state.Under the condition of resonance, the efect law of the parameters including mass ratio, damping ratio, and installation position of the device on the vibration suppression performance of tip displacement is investigated, and the following conclusions are obtained: (1) By comparing the Von-Karman spectrum having the rotating sample spectrum obtained using the Von-Karman spectrum as the source spectrum, it can be found that the energy distribution of the rotating sample spectrum in the high-frequency part is obviously diferent from that of the Von-Karman spectrum.(2) Te parameters, e.g., the mass ratio μ, damping ratio ξ, and installation position x 0 /L, show a strong improvement on the vibration damping performance of the blade tip displacement.As the mass ratio rises, that efectiveness frst increases and then decreases.Meanwhile, as the installation position is closer to the blade tip, the vibration reduction ratio frst increases and then gradually fattens.In addition, as the damping ratio increases, the vibration decreasing ratio frst rises rapidly and then decreases gently.(3) Te operation displacement of the mass block decreases frst and then remains stable as mass ratio increases and decreases as the damping ratio increases.In the meantime, the displacement increases when the installation position approaches the blade's tip.Te mass ratio should be minimised so as to ensure satisfactory performance of the vibration reduction control device and to prevent colliding phenomena between the mass block and the inside wall of the blade web during run time, and the installation position should be as far away as possible from the blade's tip while increasing the damping ratio.(4) Using the optimal parameter values, the vibration reduction control device designed in this paper could be efective in suppressing the peak displacement of the tip and the bending moment at the blade root under the condition of ensuring mass block against colliding with the inside wall of the blade's web.If the relative optimal settings of mass ratio μ � 0.03, damping ratio ξ � 15%, and installation position x 0 /L � 0.55, the largest peak vibration damping ratio of blade tip attains 52.28%, and the maximum standard vibration damping ratio attains 53.75%.In addition, the smallest gap between the lateral movement of the mass block and web is 0.02 m when the device is at operation, which meets the conditions for the operation of the device.In addition, the minimum distance between the horizontal displacement of mass block and web is 0.02 m when the device is at operation, which meets the conditions for the operation of the device.

Figure 2 :
Figure 2: Schematic diagram of vibration reduction control device.(a) Tree-dimensional sketch of the device.(b) Elevation view of the device.(c) Section view of device 1-1.(d) Section drawing of device 2-2.

Figure 3 :
Figure 3: Parameter sketch of damping control device.

Figure 6 :
Figure 6: Diagram showing the calculation of axial blade's displacement.

Figure 7 :
Figure 7: Gravitation decomposition diagram of the blade.

Figure 8 :
Figure 8: Simplifed diagram of the vibration control device.

Figure 9 :Figure 10 :
Figure 9: Distribution of sampling points in the rotating plane of wind turbine blade.

1 αFigure 11 :Figure 12 :
Figure 11: Geometrical relationship of sampling points of the wind turbine blade.

Figure 14 :
Figure 14: Distribution of sampling points for individual blades.

Figure 16 :Figure 17 :
Figure 16: Turbulent wind speed at P1 on the blade.

Figure 18 :Figure 19 :Figure 20 :Figure 21 :
Figure 18: decomposition diagram of the airfoil surface of the blade element.

Figure 24 :
Figure 24: Distribution of maximum vibration reduction ratio under efects of installation location and mass ratio.

Figure 25 :
Figure 25: Efect of mass ratio and installation position on the vibration reduction ratio.(a) Vibration reduction ratio of the peak displacement.(b) Vibration reduction ratio of the standard deviation of displacement.

Figure 26 :
Figure 26: Distribution of maximum vibration reduction ratio under efects of mass ratio and damping ratio.

Figure 27 :
Figure 27: Distribution of maximum vibration reduction ratio under damping ratio and installation location.

Figure 28 :
Figure 28: Infuence of damping ratio and installation position on vibration reduction ratio.(a) Vibration reduction ratio of peak displacement.(b) Vibration reduction ratio of the standard deviation of displacement.

Figure 29 :
Figure 29: Law of variation of the peak displacement of the mass block under efects of installation location and mass ratio.

Figure 30 :Figure 31 :Figure 32 :Figure 33 :
Figure 30: Law of variation of the peak displacement of the mass ratio.