期刊文献+

应力比对S135钻杆钢腐蚀疲劳行为的影响 被引量:5

Influence of Stress Ratio on Corrosion Fatigue Behaviour of S135 Drill Pipe Steel
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摘要 利用疲劳试验机和扫描电镜研究了在弱碱性介质(质量分数为3.0%的KCl溶液)中不同应力比R(0.1,0.3,0.5,0.7)对S135钻杆钢腐蚀疲劳行为的影响,并得到了该钻杆钢腐蚀疲劳裂纹扩展表达式和疲劳裂纹临界撕裂点的应力强度因子幅值ΔK与R的关系式。结果表明:随着R的增大,试样裂纹扩展临界撕裂点和最终撕裂点对应的ΔK逐渐减小(R和临界撕裂点的ΔK值之间呈明显的线性关系),试样的腐蚀疲劳裂纹扩展速率增大,腐蚀疲劳相对寿命减小,裂纹开裂由疲劳条带扩展机制转化为解理扩展机制。 The influences of different stess ratios R (0.1,0.3,0.5,0.7) on the corrosion fatigue behaviour of S135 drill pipe steel in the weak alkali medium (3.0wt% KCl solution) were investigated by the fatigue tester and scanning electron microscope, and then the corrosion fatigue crack propagation rate expression and the relationship of R vs the stress intensity factor range △K at the fatigue crack critical tearing point were obtained. The results show that with the increase of R, the △K at the crack critical and final tearing points of the specimen decreased gradually (the relationship between R and the critical tearing point △K was obviously linear) ; the corrosion fatigue crack propagation rate also increased while corrosion fatigue relative life decreased and the crack mechanism changed from stripe to cleavage fracture.
出处 《机械工程材料》 CAS CSCD 北大核心 2016年第8期72-75,共4页 Materials For Mechanical Engineering
基金 陕西省材料科学与工程重点学科资助项目(YS32030203) 中国石油天然气集团公司石油管工程重点实验室预研及探索基金资助项目(Z12201)
关键词 S135钻杆钢 应力比 腐蚀疲劳裂纹扩展 疲劳寿命 S135 drill pipe steel stress ratio corrosion fatigue crack propagation fatigue life
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参考文献13

  • 1郑修麟,王泓,已晓伟,等.材料疲劳理论与工程应用[M].北京:科学出版社,2013.
  • 2MISCOM G F, DE MIRANDA P EV, NETTO T A, et al. Techniques to characterize fatigue behaviour of full size drill pipes and small scale samples [J]. International Journal of Fatigue, 2004, 26(6) : 578-584.
  • 3DALE B A. An experimental investigation of fatigue crackgrowth indrillsting tubulars [J]. SPE Drilling Engineering, 1998,3(4) :356-362.
  • 4王荣,左冬声,雒设计.S135钻杆钢的单轴疲劳性能对比[J].机械工程材料,2012,36(4):50-53. 被引量:1
  • 5宋全超,张建国,乙晓伟,王泓.有机玻璃裂纹扩展双参量驱动力模型[J].航空材料学报,2011,31(4):86-89. 被引量:4
  • 6刘岗,郑子樵,杨守杰,戴圣龙,李世晨.2E12铝合金的疲劳性能与裂纹扩展行为[J].机械工程材料,2007,31(11):65-68. 被引量:13
  • 7佘玲娟,郑子樵,钟警,林莉.6156铝合金疲劳裂纹的扩展速率[J].机械工程材料,2011,35(5):19-22. 被引量:8
  • 8LU M X, ZHENG X L. A new microcomputer-aided system for measuring fatigue crack propagation threshold and selecting testing parameters F J 1. Engineering Fracture Mechanics, 1993, 45(6) : 889-896.
  • 9BOYCE B 1,, ORITCHIE R. Effect of load ratio and maximum stress intensity on the fatigue threshold in Ti-6AI- 4V[J]. Engineering Fracture Mechanics,2001, 68: 129-147.
  • 10束德林,陈九磅,风仪.工程材料力学性能[M].北京:机械工业出版社,2009:106.

二级参考文献47

  • 1张君尧.美国铝业公司6013铝合金简介[J].轻合金加工技术,1995,23(3):24-26. 被引量:21
  • 2贾敬华,李亚智,肖健.YB-MD-3有机玻璃的疲劳裂纹扩展特性研究[J].航空材料学报,2006,26(5):109-112. 被引量:12
  • 3刘永刚,苏建文,林凯,冯耀荣.一例S135钻杆本体断裂原因分析[J].石油矿场机械,2007,36(5):58-61. 被引量:15
  • 4[1]Cassada W,Liu J,Taley J.Aluminum alloys for aircraft structure[J].Advanced Materials Processes,2002 (12):27 -29.
  • 5[2]Manabu Nakai,Takehiko Eto.New aspects of development of high strength aluminum alloys for aerospace applications[J].Materials Science and Engineering A,2000(1):62-68.
  • 6[3]Starke E A,Staleyt J T.Application of modem aluminum alloys to aircraft[J].Prog Aerospace Sci,1996,32 (2/3):131-172.
  • 7[4]Strivatsan T S,Kolar D,Magnusen P.The cyclic fatigue and final fracture behavior of aluminum alloy 2524[J].Materials & Design,2002(23):129-139.
  • 8[6]戈康达 S.Fatigue Failure of Metals[M].颜鸣皋,刘才穆,译.上海:上海科学技术出版社,1983:210-218.
  • 9[7]吴学仁.飞机结构金属材料力学性能手册[M].第2卷.北京:北京航空工业出版社,1996:146-156.
  • 10[8]Suresh S.Fatigue of Materials[M].王中光,译.北京:国防工业出版社,1993:193-214.

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