摘要
本文采用局部应力一应变法,结合Coffin公式,忽略弹性应变。考虑应变速率的影响,导出了在给定的试验条件下,根据材料的拉伸性能估算其多冲疲劳裂纹起始寿命的表达式,经试验结果验证表明,对不同冲击能量,不同热处理状态以及不同缺口形状的多冲试样,估算式均具有较高的准确性。
Based on the analysis of local stress and strain at the notch root of specimen subjected to repeated impact load, and by applying Coffins strain fatigue formula and taking account of the effect of strain rate, a new formula for predicting the repeated impact fatigue crack initiation life from the tensile properties of 0. 4C-CrNiMoSi steel is developed.By checking with the authors'test results, the formula developed is applicable well to different conditions including some kinds of heat treatment, stress concentration factor and impact energy. And the developed formula can be applied to other steels during the selection of the corresponding fatigue parameter C(fatigue ductility exponent in Collins strain fatigue formula).
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第9期A487-A492,共6页
Acta Aeronautica et Astronautica Sinica
关键词
铬镍钼硅钢
疲劳
裂纹
寿命
0.4C钢
repeated impact fatigue,crack initiation life,austempering.
