摘要
采用光滑圆棒和中心孔板片试样,对GH901合金室温高低周复合疲劳进行了系统的研究。结果表明,如按一定方式分解复合循环波形,则利用线性累积损伤规律能较准确地预测复合循环疲劳寿命;复合循环下的疲劳裂纹扩展速率按线性迭加法和均方根应力强度因子变程法,能作出比较准确的预测。
The fatigue behaviours of Superalloy GH901 under major combined with minor cycle have been systematically studied at room temperature using smooth specimen and sheet with center hole.The results showed that if combined cyclic waves were with decomposed certain methods,the fatigue life can be accurately predicted by using the linear accumulative damage rule; the crack growth rates under major combined with minor cycle are also in good agreement with the linear summation prediction and the root mean sequare stress intensity range (K_(RMS)) prediction.
出处
《航空材料学报》
EI
CAS
CSCD
1990年第A09期35-43,共9页
Journal of Aeronautical Materials
