摘要
在计算分析含有角裂纹等厚空心盘应力强度因子基础上,针对某涡轮盘螺栓孔周向应力最大处建立孔边角裂纹的有限元模型;利用J积分法,计算得到不同尺寸裂纹前沿的应力强度因子;采用2自由度法描述扩展过程中裂纹前沿形状的发展,对角裂纹引起的轮盘裂纹扩展过程进行了有限元模拟;最后得到涡轮盘的裂纹扩展寿命。
Based on the calculation of stress intensity factors for the equal-thickness hollow turbine disk with the corner crack, a finite element model of the corner crack was established for an turbine disk bolt hole maximum circumferential stress. The stress intensity factors of the different size crack front were calculated by the J-integral method. The development of crack front shape in the propagation process was described by the two degree of freedom metho＆ the crack propagation process of the turbine disk caused by the corner crack was simulated by the finite element method. Finally, the crack propagation life of the turbine disk was predicted.
出处
《航空发动机》
2010年第2期35-38,共4页
Aeroengine
