Crack path in aeronautical titanium alloy under ultrasonic torsion loading
作者: A. NikitinC. BathiasThierry Palin-LucA.A. Shanyavskiy
作者单位: 1LEME, University Paris Ouest Nanterre La Defense, 50, rue de Serves, Ville-d'Avray, 92410, France
2Arts et Metiers Paris Tech, I2M, CNRS University of Bordeaux, Esplanade des Arts et Metiers, Talence, 33405, France
3State Centre for Flights Safety, Sheremetievo-1 Airport, PO Box 54, Moscow region, Khimki State, 141426, Russia
刊名: Fracture and Structural Integrity, 2016, Vol.10 (35), pp.213 - 222
来源数据库: Gruppo Italiano Frattura
DOI: 10.3221/IGF-ESIS.35.25
关键词: Very-High Cycle Fatigue.Titanium alloyTorsionUltrasonicCrack initiationCrack growth
原始语种摘要: This paper discusses features of fatigue crack initiation and growth in aeronautical VT3-1 titanium alloy under pure torsion loading in gigacycle regime. Two materials: extruded and forged VT3-1 titanium alloys were studied. Torsion fatigue tests were performed up to fatigue life of 109 cycles. The results of the torsion tests were compared with previously obtained results under fully reversed axial loading on the same alloys. It has been shown that independently on production process as surface as well subsurface crack initiation may appear under ultrasonic torsion loading despite the maximum stress amplitude located at the specimen surface. In the case of surface crack initiation, a scenario of crack initiation and growth is similar to HCF regime except an additional possibility for...
全文获取路径: Gruppo Italiano Frattura 

  • torsion 扭转
  • loading 加负载
  • aeronautical 航空的
  • titanium 
  • crack 裂隙
  • ultrasonic 超音波的
  • alloy 合金
  • initiation 创始
  • subsurface 次表层的
  • branching 分枝