航空学报 > 1989, Vol. 10 Issue (12): 649-652

LY12CZ板材疲劳损伤及裂纹形成研究

李长春1, 赵慧霞1, 李光霞1, 郑旻仲2   

  1. 1. 华中理工大学;2. 航空强度研究所
  • 收稿日期:1989-04-01 修回日期:1900-01-01 出版日期:1989-12-25 发布日期:1989-12-25

A STUDY ON FATIGUE DAMAGE AND CRACK INITIATION OF LY12CZ ALLOY

Li Changchun1, Zhao Huixia1, Li Guangxia1, Zheng Minzhong2   

  1. 1. Huazhong University of Science and Technology;2. Institute of Aeronautical strength
  • Received:1989-04-01 Revised:1900-01-01 Online:1989-12-25 Published:1989-12-25

摘要: 受交变载荷的构件,其疲劳损伤裂纹形成阶段在全寿命中占有相当大的比例。已有的疲劳损伤分析要求给出明确的应力或应变控制条件。只有光滑构件才能满足该条件,而缺口构件的疲劳损伤经常发生在缺口根部附近,这里的控制条件是难以准确模拟的。因此对缺口构件的疲劳损伤分析须进行细致的实验观测。

Abstract: In this paper, fatigue tests were carried out for different type and size of specimens to study fatigue damage and crack initiation of LY12CZ plate. Using microscopy observation and strain analysis, we have studied tension-tension low cycle fatigue damage. The experimental results show that small crack initiation damage zones exist in the regions of high strain. The size of damage zone is a characteristic value related to material and specimen geometry. Some small cracks in th damage zone merge into a macro-crack and others become non-propagation small cracks. The fatigue damage evolution law describing damage change along with fatigue cycles has been obtained.