| With the rapid development of science and technology,the application range of composite materials is becoming wider and wider,and the demand for composite materials in the aerospace technology field is also increasing.Co MPared with traditional metal blades,the advantages of composite blades are more obvious: such as quality Lightness,high specific modulus,strong designability.Therefore,the application of composite materials in engine blades is currently the most important development in the aerospace field.The composite blades of traditional layup structure have not kept up with the pace of the times.The single lay angle and lack of scientific inspiration are the bottlenecks encountered in the layup design of composite blades at this stage.Therefore,the light weight of composite blades,High-strength performance synergistic enhancement technology urgently needs to be resolved.This paper mainly combines the idea of bionics,through mechanical performance testing,finite element simulation and microscopic analysis,the layering design of different parts of the engine blade is studied.The main research contents are as follows:(1)First,based on the composite material layup design criteria,a set of layup methods for blade thickening and interlayer design is proposed,and then based on the Volume Fill module of Fibersim software,the volume filling layup design of the blade model constructed in this paper is carried out.According to the characteristics of the large-scale flow surface of the composite blade,the blade body of the composite blade is divided into three parts: the root,the middle and the tip.Based on the bionics idea,the three parts of the blade are designed and researched.(2)Utilizing the anti-bending and anti-torsion properties of large owl feathers,the i MPact resistance of coelacanth scales in marine organisms and the damage delay ability of lobster tongs,the fiber structure of the three organisms is combined in the blade layer structure designing.According to the characteristics of the leaf root being thinner and thinner than the tip,firstly,the bionic paving structure of the leaf root is designed,and the bionic structure sample and the traditional structure sample are prepared under the same manufacturing process.Next,through tensile,bending tests,bending and i MPact finite element simulation and microscopic analysis,it is learned from the aspects of damage form and mechanical properties that the bionic basic ply structure sample at the root of the blade has the effect of deflection cracks.(3)Based on the blade thickening and interlayer design method,the bionic thickening design of the layer structure at the root of the leaf is used to obtain the layer structure at the middle of the leaf.The mechanical performance test,finite element simulation analysis and micro-damage exploration of the bionic transition layer structure in the middle of the leaf show that the spiral layer structure in the middle of the leaf has the characteristics of improving the anti-damage ability of the fiber laminated material and reducing the damage.(4)In order to further improve the comprehensive performance of the composite blade,the bionic ply structure in the middle of the leaf is designed to increase the thickness of the interlayer to obtain the bionic complete ply structure at the tip.Through tensile and bending tests,bending and i MPact finite element simulation and microscopic analysis,it is concluded that the variable-angle double spiral layer structure has the best comprehensive mechanical properties at the root,middle and tip of the blade.The layer angle is: [ 0°,0°,30°,30°,45°,45°,60°,60°,90°,90°,-45°,-45°,-60°,-60°,0°,0 °,-30°,-30°,45°,45°,0°,0°,90°,90°].The above-mentioned bionic ply structure scheme can significantly improve the overall strength and rigidity of the blade,and provide new ideas for the optimal design of composite blades. |
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