摘要
为研究孔挤压强化工艺对Ti_(2)AlNb合金疲劳性能的影响,建立孔强化工艺残余应力仿真分析模型,讨论了孔挤压工艺后表层残余应力分布规律和强化机理;开展孔挤压与未挤压试样的高温低周疲劳性能测试,并对比两种试样的疲劳断口显微组织特征。结果表明:孔挤压工艺能够在小孔周围产生较强的残余压应力层,该残余压应力层有效延迟和抑制了疲劳裂纹的萌生和扩展,显著提升了Ti_(2)AlNb试件的高温低周疲劳性能。
In order to study the effect of hole extrusion strengthening process on the fatigue performance of Ti_(2)AlNb alloy,a simulation analysis model of residual stress of hole strengthening process was established.The distribution law of surface residual stress and strengthening mechanism after hole extrusion process were discussed.In this work,the hole extrusion experiments were carried out.The high temperature and low cycle fatigue performance of the compressed and un-compressed specimens were tested respectively.Meanwhile,the microstructure characteristics of the fatigue fracture of the two specimens were compared.The results show that the hole extrusion process can produce a strong residual compressive stress layer around the small hole,which effectively delays and inhibits the initiation and propagation of fatigue cracks,and significantly improves the high temperature and low cycle fatigue performance of Ti_(2)AlNb specimens.
作者
王彦菊
王欣
沙爱学
李兴无
WANG Yanju;WANG Xin;SHA Aixue;LI Xingwu(Materials Evaluation Center for Aeronautical and Aeroengine Application,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;Surface Engineering Institution,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China)
出处
《航空材料学报》
CAS
CSCD
北大核心
2021年第4期66-74,共9页
Journal of Aeronautical Materials
基金
国防科工局稳定支持重点项目(KZ0C191708)
工信部两机基础项目(KH1B191503)。
