摘要
以航空发动机压气机常用材料TC11钛合金的焊接构件为研究对象,基于损伤力学理论对其疲劳损伤演化规律进行了研究,应用分形几何理论定义损伤变量,建立了用分形损伤变量表达的损伤分形演化模型。通过疲劳寿命试验和疲劳断口分维数测量,建立了疲劳损伤分形演化方程,进一步研究疲劳损伤参数与外载荷的关系,给出了一种能够将结构宏观疲劳损伤寿命与反映结构细观损伤效应的分维数相联系的新的疲劳寿命预测方法。
Taking the welded work piece of TCll alloy which is the conventional material of aero engine compressor as research object based on damage mechanics theory, the fatigue damage evolution law was studied. Fractal damage variables were defined with fractal geometry. The fatigue fractal damage evolution model was set up, which can be expressed through fractal damage variables. According to the results of fatigue experiments and the measuring results of fractal dimension on the surface of rupture work piece, the welded joint fatigue damage fractal evolution equation was also set up. Through further studying the relation between fatigue damage parameters and exterior load, a new way of forcasting fatigue life is given, which can connect the maeroscopical fatigue damage life with the fractal dimension reflecting the microcosmic damage effect of structure.
出处
《机械工程材料》
CAS
CSCD
北大核心
2008年第11期86-89,92,共5页
Materials For Mechanical Engineering
基金
湖北省现代制造质量工程重点实验室基金资助项目(LMQ2005B02)
关键词
钛合金
疲劳强度
焊接
寿命预测
分形损伤模型
Ti alloy
fatigue strength
welding
life prediction
fractal damage model
