Fatigue Life Estimation for an Aircraft Engine Fan Blade

被引：0
|
作者：
尹珩苏 [1 ]
晏晶 [1 ]
陈浩 [1 ]
吕志强 [1 ]
黄洪钟 [1 ]
机构：
[1] School of Mechatronics Engineering,University of Electronic Science and Technology of China
来源：
JournalofDonghuaUniversity(EnglishEdition) | 2016年 / 33卷 / 02期
关键词：
fan blade; nominal stress method; fatigue notch factor; cumulative fatigue damage theory;
D O I：
10.19884/j.1672-5220.2016.02.004
中图分类号：
V232.4 [叶片];
学科分类号：
摘要：
In this paper,stress states under corresponding condition of an aero-engine fan blade using finite element stress-strain analysis for three work cycles in the 900 h load spectrum are obtained.Through the nominal stress method,we calculated the fatigue notch factor and combined the material characteristics of TC6 to correct the material curve to the fan blades curve. Finally,the fatigue life of a fan blade was estimated using the linear cumulative damage rule and nonlinear cumulative damage theory.
引用
收藏
页码：188 / 191
页数：4
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