Displacement Field Variable Modeling Method for Heterogeneous Materials in Wind Power Blade Core Plates

1  Introduction

According to the outline of the 14th Five-Year Plan and the proposal for 2035, China will be vigorously developing renewable energy and environmental protection industries accordingly. Wind power plays an important part of renewable energy’s irreplaceable role in modern society [1–4]. The core plate of a wind turbine has many applications in the whole blade and accounts for a relatively high cost in the whole wind turbine [5]. The blade core plate adopts a sandwich structure, the substrate is glass fiber laminate, and the core material is generally selected lightweight, high strength polyvinyl chloride foam. The adhesive combine substrate and material Affected by the on-site manufacturing process of PVC foam, the density of the produced PVC foam is inconsistent, resulting in a heterogeneous entity in the core plate of the processed wind turbine blades [6–8]. Therefore, there is an urgent need for better mechanical modeling of the blade core plate to study better the mechanical properties of the blade core plate, which can then provide a theoretical guarantee to improve the service life and safe operation of wind turbine blades.

At present, scholars at home and abroad have done a great deal of research on heterogeneous solid modeling methods. Kumar et al. [9] combined homogeneous units of structures and different material components into heterogeneous materials in the context of composite applications, but the model library needed to collect an even bigger amount of heterogeneous solid data and the workload was large. Qian et al. [10] proposed the S-set theory based on the R-set theory of solid modeling. Still, the model proposed according to its diffusion equation was difficult to represent the heterogeneous entities of biological materials. Gustafsson et al. [11] modeled the heterogeneous solids of the human femur based on the heterogeneous solid model of material feature representation. Yang et al. [12] reviewed the current status and development trends in the world of structural modeling techniques for heterogeneous composites. Although these research results have proved the effectiveness of the heterogeneous solid modeling method, the displacement field-based modeling method and its use in wind turbine blade testing have not been previously covered in any of the available work.

To solve the aforementioned problems, a heterogeneous solid model was established for the core material of wind turbine blades based on the displacement field theory. A three-point bending test was carried out on the wind power blade core plate sample to observe the distribution of strength, stress, and deformation. By comparing the load-displacement curve and deformation shape obtained from the experiment, the reliability of the modeling method for the displacement field of the heterogeneous material of wind turbine blade core plate the core can then be verified; it provides a theoretical data reference for the overall parameter performance of the wind turbine blade.

2  Modeling Theory

2.1 Core Plate Displacement Field Modeling

The blade core plate exists in the leading edge, trailing edge, and web, which has an irreplaceable role in increasing the strength of the structure, reducing the local instability, and improving the blade load resistance [13,14]. The problem of modeling the material properties of the blade core plate is a type of physical field modeling issue. Fig. 1 shows the comparison between heterogeneous material modeling and homogeneous material modeling. The suitable mathematical model is the fiber bundle model. This model can specify the display definition on the original geometry, constrain and control through differentiation and integration, and can maintain smoothness and analysis performance without discretizing and meshing the boundary and internal space of the entity, then express and calculate the core plate performance [15].

Figure 1: Comparison of homogeneous material modeling and heterogeneous material modeling

The core material property set are S and P(x,y,z), which is a point in space. S has a normalized distance field L and material property is F0(p), P∈S. The material function is F(l,x,y,z). F is only affected by the distance L. When P lies at the distance field boundary, L(P)=0, and when P is far from the boundary, the value of F(p) is expressed through a Taylor series expansion based on the F(0) value and the derivative, as in Eq. (1). L is the distance from the point P to F(0). Measure a set of s distances. It can be expressed as the m-order derivative of any function F(l) plus the remainder term lm+1, as in Eq. (2).

L=(x−x0)2+(y−y0)2+(z−z0)2(1)

F(l)=F0(0)+lF1(0)+∑K=2m1k!Fk(0)lk+lm+1Φ(2)

where, Fk is the kth order derivative of F.

Concerning the material function of the distance, the material standard form is obtained by repeating the integral or differential transformation of L. The material function is known to be used to control the shear modulus, F=e−1.5l, and an expression for the shear modulus of the core material can be obtained, as in Eq. (3). When k→∞, the material function converges to the original function. Only a tiny approximation can be used for any smooth materials.

F(l)=e(−1.5l)=1−1.5l+(−1.5)22!l2+(−1.5)33!l3+l4Φ(3)

Φ=∑i=1nCixi(4)

Due to the uncertainty of environmental factors in the core plate field manufacturing, it is far from sufficient to explicitly define core plate’s material properties, and only represent the distance standard form locally. The original function can only be approximated by ignoring the remainder term. To reduce the error, define the unknown function Φ of the remainder term um+1Φ through a series of linear combinations, as in Eq. (4). It is known that the basis function χi. In some sufficiently complete space, both the error and the basis function χi are functions of space variables. All modeling problems boil down to determining the unknown coefficients Ci, to satisfy the material function approximation constraint.

2.2 Fiberglass Panels Modeling

The upper and lower panels in the core plate are laminate structures composed of glass fibers, whose properties are mainly determined by the glass fiber monolayers’ mechanical properties, geometry, and boundary conditions [16,17]. It is known that the material elastic constants of each layer of glass fiber are (E1, E2, V12, G12), and the lay-up angle is θ. The laminate has a total of players, and the thickness of each layer is f. Each layer of glass fiber is an orthogonal anisotropic material; the intrinsic structure relationship in the plane stress state is as follows:

{σ1σ2σ3}=[Q11Q120Q12Q22000Q66]{ε1ε2ε3}(5)

where, σ1, σ2, σ3, ε1, ε2, ε3 are the stress and strain in the XYZ direction of the orthotropic material of the panels.

The positive axis stiffness matrix Q can be derived from the single-layer glass fiber engineering elastic constants as follows:

{Q11=E1/(1−V12V21)Q12=E1V21/(1−V12V21)Q22=E2/(1−V12V21)Q66=G12(6)

Convert the main direction of the single-layer glass fiber composite material with the ply angle of 45° to the overall coordinate system XYZ, and obtain the coordinate conversion matrix of each layer:

T=[q2p22pqp2q2−2pq−pqpqq2−p2](7)

Among them, q=cos⁡θ; p=sin⁡θ.

The stress correspondence for each glass fiber layer is:

{σ1σ2σ3}=T{σxσyσxy}(8)

Using the same method, the strain-stress relationship under coordinate transformation can be found as follows:

{ε1ε2ε3}=T−T{εxεyεxy}(9)

The in-plane stiffness coefficient of the upper and lower panels is calculated as:

Aij=∑k=1n(Qij¯)sf(i=1,2,3;j=1,2,3)(10)

where, the subscript s represents the sth layer; n means there are n layers in total. Q¯ is the transformation stiffness matrix of Q:

Q¯=T−1QTT(11)

where, Q¯ is a symmetric matrix, and the calculation method of each coefficient is shown in the following formulas:

Q11¯=q4Q11+2p2q2(Q12+2Q66)+p4Q22(12)

Q12¯=p2q2(Q12+Q22−4Q66)+(m4+n4)Q12(13)

Q22¯=p4Q11+2p2q2(Q12+2Q66)+q4Q22(14)

Q16¯=pq3(Q11−Q12)+p3q(Q12−Q22)−2pq(p2−q2)Q66(15)

Q26¯=p3q(Q11−Q12)+pq3(Q12−Q22)+2pq(p2−q2)Q66(16)

Q66¯=p2q2(Q12+Q22−2Q12−2Q66)+(m4+n4)Q66(17)

In-plane flexibility λ of upper and lower panels see the formula:

λ=A−1(18)

λ=[a11a12a13a12a22a23a31a32a33](19)

The modulus of elasticity in the x-direction of the panels after regularization is:

Ex=1ha11(20)

where, h represents the thickness of the panel.

3  General Scheme and Finite Element Analysis

3.1 Program Overview

As shown in Fig. 2, the three-point bending static test of blade core plate consists of mechanical structure, hydraulic system, electrical control cabinet, and PC end. The mechanical network consists of a loading bracket, driveshaft, filament bar, and upper beam. The blade core plate is precisely placed on the fixture through the measuring device. The indenter is in contact with the core plate under the reaction of the lead screw for testing, and the other end of the indenter is connected to the upper beam through the force sensor. When working, the servo motor of the hydraulic system at the bottom of the mechanical structure drives the hydraulic pump to convert the mechanical energy into hydraulic energy, and the hydraulic oil enters the servo motor to work through the servo valve. At the same time, the force sensor converts the power into an electric signal through the transmitter and feeds it back to the upper computer.

Figure 2: Design scheme drawing of three-point bending test machine for blade core plate

3.2 Lamination of Composite Materials

The blade core layup needs to add material properties, build a model, define the coordinate tool system, and define the direction selection set and layup parameters. It is set in the ACP-Pre module of the finite element analysis software Ansys workbench. Firstly, material properties were added. The orthotropic anisotropic glass fiber monomorphic strip material and heterogeneous solid material properties were added to the model. The material parameters are detailed in Table 1.

In Table 1: E is the modulus of elasticity; PR is Poisson’s ratio; G is shear modulus; X, Y, Z respectively represent the three directions of the material coordinate system.

After the material properties were added, it created a cloth layer; and gave its glass fiber and core unit thickness. That thickness is thoroughly detailed in Table 2. The glass fiber units were layered to form a unit set; and were laminated according to the + 45°/−45 direction. Finally, the coordinate system was defined, and the zero direction of the ply was established; the bottom panel, the top panel, and the core material then was packed to be formed.

3.3 Numerical Simulation of Three-Point Bending Test

The explicit dynamic algorithm solved the finite element model of the three-point bending structure. The finite element model was pre-processed [18,19], including the elemental and material definition, mesh division, boundary condition definition and external load application. Linear condition constraints modeled homogeneous solids, and heterogeneous solids were modeled by laying up composite materials. The geometric dimensions in the finite element modeling were consistent with the experiments. The finite element model of the three-point bending structure is shown in Fig. 3.

Figure 3: Three-point bending load-bearing solid model of glass fiber-polyvinyl chloride core plate

Numerical simulation of three-point bending structure was carried out after the composite material was laminated. The ACP preprocessing module and explicit dynamics were associated and shared in Ansys workbench to solve. For the analysis of three-point bending, referring to the work of Fries et al. [20,21], the Level set method global tracking algorithm was introduced. With this algorithm, the finite element model’s sensitivity to the mesh’s orientation was expected to be eliminated. For the pretreatment of the numerical simulation of the three-point bending structure, the material of the indenter and the support was first specified as high-strength alloy steel, namely 38CrMoAL.

The material parameters are shown in Table 3. A custom material method was taken and input into the following engineering material database.

Secondly, set the contact relationship. The contact relationship between the indenter and the core plate was “surface-to-surface” friction contact, and the friction coefficient was 0.2. The contact relationship between the support and the core plate was frictionless contact. Since the fineness of meshing greatly influence the results of finite element analysis, high-quality mapped meshes were used for meshing. Its total number of nodes was 51813 and the total number of cells was 44905.

The finite element model obtained after meshing is shown in Fig. 4. Finally, added boundary conditions and applied external loads, where both the indenter and the support were set to rigid body.

Figure 4: Three-point bending finite element model of glass fiber-polyvinyl chloride core material

By analyzing the working conditions involved, it became understood that the contact surface between the indenter and the blade core plate was the force-bearing surface. Finally, an external load was applied, a speed of 5 m/s was set, the direction was positioned to be straight down, and the end time was 0.04 s. There were only degrees of freedom to move in regarding of speed. In the analysis process, the rate of the indenter in the finite element analysis was much greater than the speed of the indenter movement in the experiment. The purpose was to eliminate the inertial force caused by the increase in speed. Perform dynamic solution after setting according to parameters.

After the finite element was pre-processed and solved, post-processing was then performed. The accuracy of the numerical simulation results was also verified according to the grid independence [22]. In Ansys workbench, the mesh-independent solution could be determined by setting the target value and having the software automatically perform multiple calculations. After each solution, the software automatically re-divided the mesh in the area that required further refinement, calculated the corresponding equivalent stress and compared it with the previous result. After completion, the computer solved again until the result difference met the set requirements. Therefore, the convergence was inserted in the result equivalent stress, setting a difference of 0%. After four calculations, the calculated failure load was 1.62 kN, which was only 0.08% different from the third calculation result, which met the calculation requirements. The obtained deformation shape is shown in Fig. 5.

Figure 5: Three-point bending simulation deformation shape of glass fiber-polyvinyl chloride core plate

4  Test Platform Construction and Testing

4.1 Platform Construction

To study the bending mechanical properties of the wind turbine blade core plate, the relationship between the mid-span deflection of the blade core plate and the loading load was measured through a three-point bending test. The test consisted of an Instron5969 universal testing machine, a PC terminal, and an image acquisition system; those test parameters are shown in Table 4. During the test, the PC end controlled the indenter installed on the upper beam to contact the sample for the test. When a load was applied to the core plate in a three-point bending mode, the interface formed between the panel and its foam core material on the side close to the indenter mainly bore compressive stress. In contrast, the interface formed between the panel and its foam core material on the side far away from the indenter mainly bore tensile stress.

The PC terminal had the work of designing the control algorithm, collecting data, as well as storing and displaying the strain curve. The test site is shown in Fig. 6. The test took 5 test specimens for the test. The numbering rule was “the thickness of the upper panel-the thickness of the core board-the thickness of the lower panel-the repeatability test label”. For example in the test piece “2-30-2-A”, the repeatability number was A. The bending strength was calculated according to Eq. (14). The test referred to the standard GB/T 1456-2005 “Test Method for Flexural Performance of Sandwich Structures” [23]. In the test, the indenter adopted the control method of displacement loading and force unloading. The test object is shown in Fig. 7.

σ=3P⋅S2W⋅B2(21)

where, σ is the bending strength, P is the ultimate load, S is the span, W is the sample width, and B is the sample thickness.

Figure 6: Three-point bending test of glass fiber-polyvinyl chloride core plate

Figure 7: Schematic diagram of three-point bending experiment device

4.2 Experimental Results

At the end of the test, the load-displacement curves fed back by the digital image system and the force sensor are shown in Fig. 8. The core plate could be divided from the curves into three stages in the whole bending deformation process: elasticity, yield, and failure [24–26]. The data of the three-point bending test are shown in Table 5.

Figure 8: Load-displacement curves

The deformation of the core board is shown in Fig. 9.

(1)   The first stage was the elastic stage. The load-displacement curve increased linearly and the core plate did have elastic deformation. The deformation of the core plate could restore to its original state after unloading.

(2)   The second stage was the yield stage, in which the load remained stable and did not change obviously with the displacement increase. The upper ultimately plate completely failed and the core layer near the upper panel was gradually compacted.

(3)   The third stage was the destruction stage, which showed that the upper panel had a sizealy local deformation, and the core material was compacted in the indenter area. The responses of each stage of the panel, core material, and the interface layer were not synchronized, and face-core delamination occurred.

Figure 9: Physical image of core plate deformation

Fig. 10 reveals the internal failure mechanism of the blade core. After observation, it was found that the most likely failure modes of the core board were plastic deformation and core material collapse. At the same time, the face-core interface delamination occurred, and the delamination process extended from the indenter to both sides along the face-core interface.

Figure 10: Core plate failure sample

By comparing the results of the finite element analysis of the core plate with the test results, the correctness of the simulation analysis method was verified from the core plate deformation form and load-displacement curve. From the deformation profile of the core plate shown in Fig. 11, it can be seen that the deformation shape obtained by the simulation is almost consistent with the test.

Figure 11: The simulation analysis and experimental comparison of three-point bending deformation of the core plate

Fig. 12 demonstrates the comparison of the load-displacement curves obtained from the finite element analysis and the test, and the obtained curves are basically in agreement. After the pross of numerical calculation, the average value of the load in the curve platform area shows the failure load in Table 6. The failure load of the blade core plate obtained by the finite element analysis was 1.62 kN. The actual failure load of the core plate measured by the test was 1.59 kN. The deviation between the simulation and the test results was 1.9%. It was concluded that the modeling method based on the displacement field was highly reliable.

Figure 12: Simulation analysis and test comparison of core plate load-displacement curves

5  Conclusion

This paper took the wind turbine blade core board as the research object and proposed a modeling method for displacement field variables of heterogeneous materials. Furthermore, it established a heterogeneous solid model of blade core plate, performed finite element analysis on it, and conducted static force tests. The main conclusions are as follows:

(1)   The shear modulus of the core board and the glass fiber panel was expressed by establishing a heterogeneous model of the core board of the wind turbine blade. Based on the established model, the finite element method was used to analyze the displayed dynamics, and the failure load of the core plate was 1.62 kN. And the deformation shape of the core board was obtained through simulation.

(2)   The failure modes of the core plate included elasticity, yield, and failure stages. In the elastic stage, the deformation of the core board could restore to its original state; in the yield stage, the glass fiber panel yielded, and the core layer near the upper panel was gradually compacted; in the failure stage, the upper panel was partially deformed, and the central area of the core layer was compacted.

(3)   The main failure modes of the core board were plastic deformation, core material collapse and delamination of the panel-core material interface. The indenter expanded along the surface-core interface on both sides during delamination, and bending deformation was more likely to occur at the delamination position.

(4)   The three-point bending test was verified by building a test platform, and the test measured the damage load of 1.59 kN, with a difference of 1.9%. The load-displacement curve obtained by the numerical simulation was basically consistent with the experimental results, and the finite element analysis’s deformation patterns were consistent with the experimental results. The validity and reliability of the displacement field variable modeling were verified. It has important guiding significance for the design of wind power blades and related structures, and at the same time provides detailed experimental control data for related numerical simulation work.

Funding Statement: This research was funded by National Natural Science Foundation of China (Grant No. 52075305), Natural Science Foundation of Shandong Province (Grant No. ZR2019- MEE076) and Zhoucun District School City Integration Development Project (Grant No. 2020ZCXCZH01).

Conflicts of Interest: The authors declare that they have no conflicts of interest to report regarding the present study.

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