摘要
本文模拟航空发动机叶片在服役状态下的疲劳行为,研究了DZ—22定向凝固合金在不同试验温度、不同低循环应力下,高低循环复合疲劳特性。结果表明,在低循环载荷上叠加高循环振动载荷使复合疲劳寿命下降。但若高频振幅小于某一临界值时,其复合疲劳寿命反而会明显增长,这是由于高频小幅值振动起到次负荷锻炼作用使材料得到强化,且在高低循坏复合疲劳过程中抑制了疲劳损伤。
Fatigue behaviours of aeronautic engine blade on operating duty were imitated to research high-low cycle complex fatigue properties of directionally solidified high temperature DZ-22 alloy on the conditions of different test temperature,differenft low cycle stress. Results show thst complex fatigue life was shortened when a high cycle vibration load was added to low cycle load , but was distinctly longered when high frequent vibration amplitude was lowed to a boundary value. This due to the small vibration amplitude which take the function of secoondary load exercise and strengthen the material. Creep damage is restrained in the process it high - low cycle complex fatigue.
出处
《物理测试》
CAS
1995年第2期1-7,共7页
Physics Examination and Testing
关键词
定向凝固
耐热合金
疲劳
航空发动机
叶片
complex fatigue , directionally solodified ,high temperature alloy
