激光快速修复发动机叶片疲劳性能研究  

Fatigue Performance Study of Laser Rapid Repairing Turbine Blade

作　　者：贾晨雪 王奇志[1] 万华亮 张铮[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《计算机仿真》2017年第8期59-63,88,共6页Computer Simulation

摘　　要：发动机叶片激光快速修复可以有效且经济地延长叶片的使用寿命。准确预测不同激光快速修复扫描方向下叶片的疲劳行为,可以确保叶片的安全使用。激光快速修复结构的疲劳性能与制造工艺及微缺陷密切相关,由于其复杂性,目前尚没有可靠的定量分析方法;为解决上述问题,运用损伤力学有限元方法研究了不同扫描方向激光快速修复钛合金材料单胞模型的疲劳寿命;采用单胞模型仿真模拟了疲劳微裂纹的扩展过程,预测了不同扫描角度下,激光快速修复叶片的疲劳裂纹萌生寿命;仿真结果表明,上述方法的计算结果与现有文献中的实验数据吻合较好,为激光快速修复工艺参数的选择提供了有价值的参考数据。Laser rapid repairing of the turbine blade is an effective and economical way to extend its service life. Accurate prediction of the blade fatigue behavior under different laser scanning direction will ensure the safety of the blade. The fatigue performance of the laser rapid repairing structure is closely related to the manufacturing process and micro defects, due to its complexity, there is no reliable method of quantitative analysis. In order to solve the problems above, the damage mechanics - finite element method is applied to predict the fatigue life of titanium alloy in varying laser rapid repairing directions. The fatigue micro crack propagation process is simulated by using the unit cell. The crack initiation life of the laser rapid repairing blade in different directions is predicted. The simulation re- suits show that the computational results fit well with the experimental results. Valuable reference data is provided for the selection of the laser rapid repairing process parameters

关 键 词：激光快速修复 扫描方向 疲劳寿命 损伤力学 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]