期刊文献+

钛合金双片层组织对性能的影响 被引量:2

Effects of Bi-lamellar Microstructure on the Properties of Titanium Alloy
下载PDF
导出
摘要 研究了通过热处理制度调整,在合金α片层之间形成细小的条状次生α相,形成一种新型的钛合金显微组织——双片层组织。通过对比等轴组织、双态组织、片层组织和双片层组织的性能,结果表明,在合金的强度和塑性不损失的条件下,双片层组织进一步提高了裂纹在合金中的扩展阻抗,使得合金的断裂韧性得到改善,疲劳裂纹扩展速率得到降低。双片层组织提高了疲劳裂纹扩展路径,使得大量的次生裂纹萌生。 A new type of microstructure, named bi-lamellar microstructure of titanium alloy comes out of precipitated small secondary α needles in the β matrix through modification heat treatment. A comparison of microstructure and property of titanium alloy between equaixed, bi-model and lamellar microstructure is made. The results manifest that bi-lamellar microstructure improves the fracture toughness and fatigue crack propagation behavior of TA15 alloys remarkably, increases the length of fatigue crack propagation and brings about large secondary cracks.
作者 李士凯
出处 《材料开发与应用》 CAS 2011年第6期17-21,共5页 Development and Application of Materials
关键词 显微组织 损伤容限 疲劳裂纹扩展速率 断裂韧性 Microstructure Damage tolerance Fatigue crack propagation rate Fracture toughness
  • 相关文献

参考文献9

  • 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
  • 2Arrieta A J. Multidiseiplinary design optimization of a fighter aircraft with damage tolerance constraints and a prcbabilistic model of the fatigue environment [ D ]. USA: University of Oklahoma Graduate College, 2001.
  • 3Lutjering G,Williams J C. Titanium[ M]. 2003, Germany: Springer: 182 - 185.
  • 4Lutjering G. Influence of processing on microstructure and mechanical properties of ( α + β) Titanium alloys [J]. Material Science and Engineering, 1998, A243 : 32 - 45.
  • 5Hunter L J, Strangwood M, Bowen P. Effects of microstructure on the fracture behavior of the α+ β Titanium alloy Ti-4Al-dMo-2Sn-0. 5Siwt. % ( IMI 550 ) [ C]. Proceedings of the 8rd world conference on Titanium, UK, 1995, 925-932.
  • 6Peters O, Lutjering G. Comparison of the fatigue and fracture of α+β and β titanium alloys [ J ]. Metallurgical and materials transactions A, 2001,32A : 2805 -2818.
  • 7张旺峰,曹春晓,李兴无,马济民,朱知寿.钛合金断裂韧性与屈强差的关系初探[J].稀有金属材料与工程,2005,34(4):549-551. 被引量:11
  • 8军用飞机疲劳/损伤容限/耐久性设计手册(第三册)[M].北京:中国航空研究院,1994.
  • 9张旺峰,曹春晓,李兴无,马济民,朱知寿.加载方式与初生α相对钛合金裂纹扩展行为的影响[J].钛工业进展,2004,21(4):26-29. 被引量:7

二级参考文献38

  • 1[3]吴学仁主编.飞机结构金属材料力学性能手册,第二卷(损伤容限).北京:航空工业出版社,1996
  • 2[4]Pearson H S, Pachman P F. Fracture Prevention and Control. Calif. : Los Angeles, 1972:21
  • 3[5]Tuppor N G. Fracture Prevention and Control. Calif. :Los Angeles, 1972:159
  • 4[8]Rolfe S T. ASM Seminar on Fracture Control. Philadelphia: 1970
  • 5[9]Shults J M. SAE 730884. 1973
  • 6[13]Journal of Aircraft, 1974; 3
  • 7[14]AMS 4905A, U.S.A: Society of Automotive Engineers,1988
  • 8[15]Ferguson R R, Berryman R G. AFML-TR-76-137, vol.1.Rockwell International: Los Angeles, 1976
  • 9[16]Harigan M J, Kaplan M P, Sommer A W. Fracture Prevention and Control. Calif.: Los Angeles, 1972: 225
  • 10[17]Alloy Digest of TIMETAL 622. Orange, U.S.A: TIMET,1993

共引文献116

同被引文献14

引证文献2

二级引证文献15

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