喷丸强化对TC11合金模拟叶片高周疲劳寿命影响的试验  

Experiment of effect of shot peening strengthening on TC11 alloy simulation blade's HCF life

作　　者：王梅[1,2] 陆山[1] 古远兴[2] 刘亮[2] 张欢[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空工业集团公司中国燃气涡轮研究院,成都610500

出　　处：《航空动力学报》2013年第3期507-512,共6页Journal of Aerospace Power

摘　　要：针对三种叶片:钢丸强化、二次强化和未强化的钛合金叶片进行了振动特性测量和高周疲劳对比试验.通过试验结果,结合断口分析,对三种叶片的固有频率、振型阻尼比、高周疲劳极限及裂纹起源等方面进行了对比研究.研究表明:喷丸后叶片1阶振型阻尼比增大40%～50%,高周疲劳极限提高40%以上,叶片的高周疲劳寿命也相应地提高.从强化机理方面分析了高周疲劳极限得到提高的原因.该积累的试验数据及研究成果可为TC11喷丸叶片的高周疲劳工程设计提供参考.The vibration characteristic measurement and high cycle fatigue（HCF） comparison test were applied out to unstrengthened,steel grit strengthened and double strengthened blades.Through experimental results and fracture analysis,the three kinds of blades’ natural frequency,damping ratio crack origin and HCF limit were studied and compared.The study indicates that the first order damping ratio is improved about 40%—50%,and HCF limit is improved more than 40%,and HCF life is improved accordingly.The article also give the reason of HCF limit improvement was also analyzed from strengthening mechanism.The experimental data accumulated and the study result can offer references to engineering design.

关 键 词：喷丸强化 高周疲劳 强化机理 振动 寿命 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]