Material selection is one of the important things in blade structural design process and should be considered first. The reason is that the manufacturing process and design of wind blade largely depend on me chanical, physical and chemical properties of used materials and that design should also be changed by used materials. Uniaxial and triaxial fabrics were applied in the blade design of this research as reinforcement and the balsa wood was applied as the core material to increase the buckling resistance. Moreover, the epoxy type of gel coat was used to reinforce the surface with environmental degradations such as moisture absorption, ultraviolet rays, and erosion.

Infusion process was selected as manufacturing process. The process has excellent price competiveness and good mechanical properties than other manufacturing processes of composite blade. Material properties of applied GFRP and CFRP laminate during structural design are indicated in Table 2.

The composites wind blade that this research designed is the stressed skin design that sustains the load from blade skin like Figure 1 indicates and it is a structure with coupled web. Moreover, to sustain the bending moments and torsion moments to blade length direction, reinforced the stiffness by designing spar cap on the location of 15~50% of total chord length. At the outside of blade, material to protect the skin from the environment is ordinarily laminated and fiber-reinforced composites to sustain the load from the wind are laminated at the inside.

Figure 1: 
Cross section of composite blade, applied in the analysis

The layer for skin protection in Table 3 corresponds to number 1 and 2. The gel coat has been laminated to protect skin from degradation due to operation of the blade and the random mat has been laminated to have durability of little skin damage. Layer number 3~5 are composed of sandwich structure and laminating structure of form core or uniaxial glass fabric inside the triaxial glass fabric [10].

Recently in developed turbine manufacturing company, applies some in blade with carbon fiber that is possible to have lighter design and more excellent fatigue characteristic than the glass fabric.

And as the blade gradually becomes larger, the concern about the weight has been issued and to solve this issue, application of the reinforcement like carbon fabric which can lessen the weight than the existing design by the material is required [11]. UD glass and UD carbon fabric is applied as reinforcement of spar cap in this research and three different models of material in spar cap part have been structured and designed (Table 4).

A finite element model of the blade was modeled by shell element, and the model was laid-up by using the lay-up pattern as shown in Table 3. The finite element model of the rotor blade was generated as a quad type mesh with about 9541 nodes and 9942 elements, and the material properties of Table 2 were used for generating the 3-D FE-model. The ANSYS-ACP was used as pre-processor for structural analysis of layered composite structures, and the fixed degrees of freedom boundary condition was applied on the end of blade root. The structural analysis was carried out using ANSYS Workbench. Indicated the weight distribution by section about “all glass design” in Figure 2 and confirmed the total weight, around 10.2 ton. Since this kind of structural design result should be provided with initial input in aero-elastic analysis of beam model, it is required to confirm whether the three dimension model is implemented as beam model or not. For this kind of design verification, the comparison of natural frequency between three dimensional and one dimensional model was performed. Indicated the result in Figure 3 and after comparing two models, even though the unique frequency was little different when it goes to higher, confirmed that the equivalent model was appropriately implemented.

Figure 2: 
Mass distributions at each of blade section

Figure 3: 
Comparison result of natural frequency

By applying the composite failure criterion of Puck’s failure criterion, confirmed the FF (Fiber Failure) and IFF (Inter Fiber Failure) and indicated the boundary of IFF damage decision by τ₂₁ (shear between resin and fabric) relation for σ₂ (resin stress direction) in Figure 4. To draw this graph, it is need to know the stress (resin direction and shear of resin and fabric), failure mode of A, B and C, and fracture angle. It implemented this part at common use structure analysis software with base of suggested equation from Puck [12]. Moreover, it performed the failure analysis by applying the applied material properties of safety factor (FF:2.205, IFF:1.764) in technical guideline of Korean Register of Shipping during the structural design.

Figure 4: 
Fracture envelop for combined stress

Blade stress and strain distributions were calculated by static analysis and the results in Figure 5~7 and Table 5. First, the stress distribution appeared to be high on blade longitudinal direction and, especially, it was able to confirm the high value of spar cap near blade root and leading Edge. It is because that the blade model is designed to sustain most of loads at skin. Therefore, the selection of material and lay-up pattern is really important in the structural design.

Moreover, through the result of strain contour indicated in Figure 6, it was able to confirm that there were deflections of 4.51m at the blade tip.

Figure 5: 
Stress contour of blade longitudinal axis

Figure 6: 
Stress contour of blade transverse axis

Figure 7: 
Tip displacement contour of the blade

Confirmed whether there was failure in FF and IFF by the part by applying Puck’s failure criterion and indicated the result in Table 6. As you see the table, FF and IFF Criteria indicated criteria numerical value less than 1 and can know that no failure occurred in all part of the blade. Moreover, implemented high value in skin section for FF and shear web and spar cap for IFF. However, since the failure between fabrics do not directly affect to the structural safety of the blade, there will be no need for changing the structural design like increasing number of lamination. Rather, it is required to decrease the number of lamination excluding the shear web.

Linear and non-linear buckling analysis was accomplished by applying the ultimate load, and buckling stability was evaluated by the analysis results. The results were summarized in Table 7. The table shows that load factors of linear and non-linear buckling were exceeded ultimate load, and all load factors had the margin of more than 20%. Therefore, the designed blade has sufficient buckling stability under wind loads.

Figure 8 shows linear buckling shape of 1st, 3rd, and 5th mode. Buckling of 1st, 3rd mode was observed at spar cap, trailing edge, and that of 5th mode was shown at shear web. Moreover, linear buckling was occurred at the inboard section of blade.

Figure 8: 
Mode shapes of linear buckling

Non-linear buckling analysis was accomplished by using mode shape of 1st mode shape. Figure 9 shows the shape of non-linear buckling, and the buckling was appeared at spar cap of the blade inboard section. In conclusion, it is thought that enhancing buckling strength at inboard section of wind turbineblade is one of the important things by using core materials. Also, it is worth considering new materials at skin of inboard section to reinforce stiffness of wind turbine blade.

Figure 9: 
Mode shape of non-linear buckling

To inquire the possibility of applied model of UD carbon fabric in the section of spar cap, changed the structural design in spar cap part of existing “all glass design”. Moreover, to implement appropriate number of lamination in spar cap part of the two models, designed the 100%, 80%, and 68% models about the weight of “all glass design” and implemented the number of lamination in spar cap part through the result of IFF Criteria. From the behaviors of hybrid blade (GFRP & CFRP) and CFRP in Figure 10, the minimum mass ratios by comparing GFRP spar cap were calculated. Moreover, two kinds of carbon spar cap model were designed by using the mass ratios.

Figure 10: 
Comparison result of two types of blade models

In Figure 11, indicated the weight, price, and tip deflection of blade of three models. All results are indicated as ratio of “all glass model”. First, the weight of hybrid spar cap was 78% of GFRP spar cap and the weight of CFRP spar cap was 53% of the spar cap that is designed as GFRP. Moreover, the price, with the standard of GFRP spar cap, of hybrid spar cap was 270% and of CFRP spar cap was 240%.

Figure 11: 
Comparison of mass, cost and displacement by changing types of blade spar cap

The tip deflection of the blade was 4.51m of GFRP spar cap, 3.20m of hybrid spar cap, and 3.39m of CFRP spar cap. From here, we confirmed that hybrid spar cap has less tip deflection than CFRP spar cap. The reason was that the standard of selecting a number of lamination was IFF Criteria value which is decided by strength but the tip deflection relates with stiffness. So this kind of aspect could be happened.

Through this result, the carbon spar cap is 2.7 times more expensive than the glass fabric spar cap. But the weight can be lighter, deflection is less, and the fatigue characteristic is relatively excellent. So, it is possible to apply by the design target specification of blade. Moreover, it could be a good choice to apply new blade materials, such as S-2 glass fabric because their material properties and price is between E-glass and Carbon.