航空学报 > 1987, Vol. 8 Issue (3): 171-177

恒幅加载下7475-T7351铝合金的疲劳裂纹扩展行为

张诗捷1, Nowack2   

  1. 1. 北京航空材料研究所;2. 西德宇航院材料研究所
  • 收稿日期:1986-08-11 修回日期:1900-01-01 出版日期:1987-03-25 发布日期:1987-03-25

FATIGUE CRACK GROWTH BEHAVIOUR OF 7475-T7351AI ALLOY UNDER CONSTANT AMPLITUDE LOADING

Zhang Shijie1, Nowack2   

  1. 1. Institute of Aeronautical Material, Beijing;2. Institute for Materials Research, DFVLR, FRG
  • Received:1986-08-11 Revised:1900-01-01 Online:1987-03-25 Published:1987-03-25

摘要: 本文进行了7475-T7351铝合金板材中心开裂试样恒幅加载宽范围应力比下的疲劳裂纹扩展试验。考虑到裂纹张开应力的确定是基于裂纹闭合概念进行裂纹扩展寿命预测的基础,且在工程应用中需要方便地确定有效应力强度因子变程△K_(ett)。本文通过疲劳裂纹扩展速率da/dN的试验数据导出了所研究材料的裂纹张开应力的经验表达式,进而用有效应力强度因子变程△K_(ett)来联系试验数据,得到对于不同应力比下裂纹扩展行为的统一描述。试验发现,无量纲裂纹张开应力S_(op)/S_(max)随所加最大毛应力水平的提高而降低。 断口分析表明,对于所试验的材料由拉伸型平断口向剪切型斜断口的转变主要受△K_(ett)控制,并注意到由拉伸型向剪切型裂纹增长的过渡对应着S_(op)/S_(max)增加的趋势。

Abstract: Constant amplitude fatigue crack growth tests were performed on center cracked 8mm thick specimens over a wide range of R-ratios.tn consideration of that it is important to determine the crack opening stress for the crack growth life prediction based on the crack closure concept and it is necessary to find a convenient way to determine the range of effective stress intensity factor Keff in engineering practice, this paper derived an empirical expression for the crack opening stress of the material tested in this investigation from the crack growth rate data da/dn. Consequently the crack growth behaviour over a wide range of R ratios can be expressed unitedly by the range of effective stress intensity factor Keff, tt is found that dimensionless crack opening stresses decrease as the applied maximum stress level increases.The results of fracture analysis indicated that the transition of fracture from tensile mode to shear mode during the tests was controlled mainly by Keff and the values of Sop/Smax increase as the cracks growth transi-tting, from the tensile mode to the shear mode.