航空发动机叶片裂纹扩展规律数值模拟研究

Numerical simulation of crack propagation for aero-engine blade

基于有限元分析软件ABAQUS联合裂纹分析软件Franc3D,开展了叶片裂纹扩展影响研究。建立压气机叶片有限元模型和裂纹扩展模型,发现叶片在振动载荷下的应力分布规律和不同裂纹位置、不同前缘形状、不同初始角度的叶片裂纹扩展规律。叶片背部裂纹扩展速率快于叶片前缘和后缘;初始裂纹前缘形状对叶片表面裂纹方向的扩展基本无影响,但对裂纹深度方向扩展存在明显影响;叶片初始裂纹方向与缘板面夹角越小,则裂纹扩展速率越快,且其他方向裂纹随着扩展会逐渐向缘板面方向偏转。

Based on the finite element analysis software ABAQUS and Franc3 D,the influence of blade crack propagation was studied.The finite element model and crack propagation model of compressor blade were established to obtain the stress distribution law of blade under vibration load,and then the crack propagation law of blade with different crack location,different leading edge shape and different initial angle was simulated.The results show that the crack extension rate of blade back is faster than that of blade leading edge and trailing edge.The shape of the initial crack front has no effect on the direction of crack propagation on blade surface,but has a significant effect on the direction of crack depth propagation.The smaller the angle between the initial crack direction and the edge plate surface,the faster the crack growth rate,and the cracks in other directions will gradually deflect towards the edge plate surface.