期刊文献+

热处理对TC4-DT钛合金组织性能的影响 被引量:18

Effect of Heat Treatment on Microstructure and Mechanical Properties of TC4-DT Alloy
下载PDF
导出
摘要 研究了φ300 mm的TC4-DT钛合金几种热处理工艺参数对显微组织和室温性能的影响。研究表明α+β区锻造φ300 mm的棒材晶粒较大,低倍呈现模糊晶,局部区域有明显的清晰晶,表明大规格棒材锻造均匀性较差。大规格的棒材+双重退火热处理后,拉伸性能和断裂韧性均能达到Rm≥825MPa,RP0.2≥750MPa,A(纵向)≥8%,Z ≥15%;KIC(T-L)≥90 MPa.m12,具有良好的强度塑性匹配性能。α+β相区锻造的φ300 mm棒材经965℃/1h AC+550℃/6h AC和940℃/1h AC+570℃/6h AC处理后,疲劳裂纹扩展速率在ΔK=11MPa.m21时,分别达到2.833036×10-6mm/cycle和7.294209×10-6mm/cycle。 Effect of series heat treatment on microstructure and room temperature mechanical properties of TCA - DT alloy bar in diameter 300mm was investigated. The results show that in the microstructure of 300mm bar forged in α + β region, the grains are coarse and vague with obvious grain bindery in some field, which suggests that the big TCA -DT bars has poor uniform inforgings. The tensile properties and fracture toughness of big bars being treated after α + β double annealing can reach to Rm≥825 MPa,RP0.2 ≥ 750 MPa, A ≥ 8 %, Z≥15% ; KIC ( T - L) ≥ 90MPa · m1/2, indicating excellent match properties between strength and plasticity . The fatigue crack propagation vacuity can reach 2. 833036 ×10^-6mm/cyde and 7. 294209 ×10^-6mm / cycle respectively after heat treated at 965℃/lh AC +550℃/6h AC and 940℃/lh AC +570℃/6h AC heat treatments.
出处 《材料开发与应用》 CAS 2009年第2期13-16,共4页 Development and Application of Materials
基金 国家重点基础研究发展计划"973"项目资助(2007CB613807 2007CB613805)
关键词 TC4-DT钛合金 热处理工艺 显微组织 力学性能 Titanium alloy Heat treatment processing Microstrueture Medical properties
  • 相关文献

参考文献9

  • 1Martin Patrick Lyle. Titanium alloy having enhanced noteh toughness and method of producing same[ P]. American Invention Patent, USP6190473,2001.
  • 2张永强 陶海林 冯永琦.稀有金属材料与工程,2005,34(3):498-498.
  • 3朱知寿,马少俊,王新南,童路,吴学仁,赵永庆,曲恒磊.TC4-DT损伤容限型钛合金疲劳裂纹扩展特性的研究[J].钛工业进展,2005,22(6):10-13. 被引量:50
  • 4李辉,曲恒磊,赵永庆,冯亮,郭红超,周伟.Ti-6Al-4V ELI合金板材的显微组织与力学性能研究[J].钛工业进展,2005,22(6):24-27. 被引量:6
  • 5张延生,胡洋海,马英,徐祝萍.热处理对Ti-6Al-4V棒材固溶时效性能的影响[J].钛工业进展,2005,22(6):18-23. 被引量:8
  • 6ATI Allegheny Technology. Technical Data Sheet TI - 040 - Allvac Titanium 6AI - 4VAIIoy [ M ]. Monroe,NC 281 10 · 5030, USA . ATI Properties Inc, 2004.1.
  • 7ATI Allegheny Technology. Technical Data Sheet TI - 020 - AHvae Titanium 6AI. 4V , Alloy [ M ]. Monroe, NC281 10 - 5030, USA: ATI Properties Inc, 2004.1.
  • 8恒磊,赵永庆,朱知寿,等.一种低成本损伤容限钛合金及其制备方法[P].CNP200510001210.3,2005.
  • 9郭萍 赵永庆 吴玮璐.稀有金属材料与工程,2005,34(3):526-526.

二级参考文献13

  • 1曹春晓.选材判据的变化与高损伤容限钛合金的发展[J].金属学报,2002,38(z1):4-11. 被引量:104
  • 2吴学仁.飞机结构金属材料力学性能手册[M].北京:航空工业出版社,1996..
  • 3Rodney Boyer,Gerhard Welsch,Coilings E W.Material Properties Handbook:Titanium Alloy[M].PA:ASM International Materials Information Society,1994:256.
  • 4BK亚力山大etal (宁兴龙译).钛合金半成品加工[M].西安:稀有金属杂志社,1984.203.
  • 5Wanhill R J H.Damage Tolerance Engineering Property Evaluations of Aerospace Aluminium Alloys with Emphais on Fatigue Crack Growth[M].New York:NLR Technical Publication,1990.
  • 6中国航空材料手册编辑委员会.中国航空材料手册(第二版)[M].北京:中国标准出版社,2002..
  • 7CampbellJE UnderwoodJH GerberichWW (汪一麟 邵本逑译).断裂力学在选材方面的应用[M].北京:冶金工业出版社,1992..
  • 8Atsushi Sugeta,Yoshihiko Uematsu,Masahiro Joho.Fatigue Crack Growth Behavior on Ti-6Al-4V Alloys under Variable Amplitude Load Sequences[C].In:Blom A F.Fatigue 2002,Proceedings of the Eighth International Fatigue Congress.Stockholm:EMAS,2002:2911.
  • 9SureshS(王中光译).材料的疲劳[M].北京:国防工业出版社,1993..
  • 10Yuen.Correlations between Fracture Surface Appearance and Fracture Mechanics Parameters for Stage-Ⅱ Fatigue Crack-Propagation in Ti-6Al-4V[J].Metallurgical Transactions,1996,5(8):1833.

共引文献57

同被引文献101

引证文献18

二级引证文献138

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部