中文摘要：

利用传统线性损伤累积模型对航空发动机叶片进行疲劳研究,由于不能准确描述损伤与载荷之间的关系,导致计算结果不能令人满意。而对于一般的非线性损伤模型,由于忽略扭转振动的影响而易导致在计算中引入误差。为此,基于连续损伤理论,在钛合金TC4（Ti-6Al-4V）疲劳试验中获得叶片材料的S-N曲线的基础上,对CHABOCHE提出的非线性损伤累积模型进行修正,提出适用于航空发动机叶片的连续非线性损伤模型,并验证了模型的正确性。通过与试验数据及线性损伤累积模型的结果进行比对,证明所建立的非线性损伤累积模型能够更准确地反映叶片的损伤累积过程,并利用该模型对某航空发动机叶片进行疲劳寿命预测。

英文摘要：

The traditional linear damage model cannot accurately describe the relationship between damage and load in the fatigue study of the aero-engine blade,thus causing unsatisfactory calculation result.The common non-linear damage model is easy to bring in error in the calculation due to neglecting the influence of torsional vibration.Therefore,based on the continuum damage theory,the non-linear damage model proposed by CHABOCHE is modified according to the blade material S-N curve obtained from the TC4（Ti-6Al-4V）fatigue testing,and the non-linear continuum damage model is proposed and its correctness is verified.In comparison with the experimental data and the linear damage model results,the non-linear continuum damage model shows better accuracy in reflecting the damage accumulation process.Finally,the non-linear continuum damage model is used to predict the fatigue life of a certain aero engine blade.