航天发动机涡轮有限元结构和疲劳分析  

Finite Element Analysis of Structure and Fatigue for Aerospace Engines Turbine

作　　者：葛挺[1] 陆云凤[1] 王文渊[1] 

机构地区：[1]中国矿业大学机电工程学院,江苏徐州221116

出　　处：《中国制造业信息化（学术版）》2011年第8期25-27,共3页

摘　　要：运用Nastrsan对航天发动机涡轮进行有限元计算分析,得出应力屈服最先发生在涡轮与叶片交汇处、过渡曲线区域是疲劳损伤危险区域的结论,并给出15个疲劳损伤最危单元点,为提高发动机涡轮寿命提供了新的研究方法和参考依据。Based on Nastrsan, it establishes the model of the aerospace engines turbine, draws a conclusion. The simulation shows that stress yield is easily occurred in the interchange of turbine, leaf and transition curve area is the danger zone of fatigue damage, illustrates the list about 15 dangerous unit points of fatigue damage. This provides the reference to improve the engine turbine＇s service life.

关 键 词：涡轮 结构 疲劳 Nastrsan 

分 类 号：TH814[机械工程—仪器科学与技术]