基于损伤容限设计的钛合金层合接头制造
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摘要
钛合金层合结构因具有较高的损伤容限而获得重视,并成为超塑成形/扩散连接技术应用的一个新方向。本文提出一种含圆形扩散止焊区的层合板结构,通过与原始板材的疲劳裂纹萌生和扩展寿命相对比,结果表明含止焊区的层合板能改善钛合金的裂纹扩展特性,并以此为基础设计并制造了含止焊区的钛合金层合接头,验证了采用现有扩散连接工艺技术制造钛合金层合接头的工艺可行性,其微观组织和各项性能等基本能满足对一般钛合金的设计使用要求。该研究成果为高损伤容限性能钛合金扩散连接层合结构在机翼梁、框等异型截面构件上的应用奠定了技术基础。
The laminated structure of titanium alloy has achieved special attention for its high damage tolerance, and become a new application trend of SPF/DB technology. A laminated structure with circle diffusion no-weld region based on damage tolerance design is introduced. Compared with the original plank, it shows improved property of crack initiation and propagation tolerance. A titanium alloy laminated joint piece with no-weld region is designed and manufactured, which verifies the feasibility for making a laminated structure through applying diffusion bonding technology. The microstructure and mechanical property are satisfi ed with the general design requirements for application. The research achievements lay a technical foundation for the titanium alloy laminated structure application on the wing beam, box and other member with special section.
The laminated structure of titanium alloy has achieved special attention for its high damage tolerance, and become a new application trend of SPF/DB technology. A laminated structure with circle diffusion no-weld region based on damage tolerance design is introduced. Compared with the original plank, it shows improved property of crack initiation and propagation tolerance. A titanium alloy laminated joint piece with no-weld region is designed and manufactured, which verifies the feasibility for making a laminated structure through applying diffusion bonding technology. The microstructure and mechanical property are satisfi ed with the general design requirements for application. The research achievements lay a technical foundation for the titanium alloy laminated structure application on the wing beam, box and other member with special section.
引文
[1]王向明.飞机钛合金结构设计与应用.北京:国防工业出版社,2010.
[2]曹春晓.选材判据的变化与损伤容限钛合金的发展.金属学报,2002,38:125-128.
[3]朱知寿,王新南,童路,商国强.航空用损伤容限型钛合金研究与应用.中国材料进展,2010,29(5):14-17.
[4]Arriet A A J,Strizag.Optimal design of aircraft structures with damage tolerance requirements.Struct Multidisc Optim,2005,30(2):155-163.
[5]Bridier F,Villechaise P,Mendez J.Slip and fatigue crack formation processes in an a/b titanium alloy in relation to crystallographictexture on different scales.Acta.Materialia,2008,56:3951-3962.
[6]Atsushi S,Yoshihiko U,Masahiro J.Fatigue crack growth behavior on Ti-6Al-4V alloys under variable amplitude load sequences.In:Blom A F.Fatigue 2002,Proceedings of the Eighth International Fatigue Congress.Stockholm:EMAS,2002:2911.
[7]张纪奎,郦正能,邱志平,等.钛合金结构损伤容限设计可行性研究.航空学报,2009,30(4):763-767.
[8]李晓华,张军,韩秀全,等.钛合金层合梁SPF/DB制造工艺研究.航空制造技术,2011,16:66-69.
[9]李志强,郭和平.超塑成形/扩散连接技术的应用与发展现状.北京航空制造工程研究所,2004,11:50-52.
[10]侯红亮,王耀奇,李晓华,等.先进钣金成形技术在航空航天领域的应用(上).金属加工,2008,13:22-24.
[11]贺小帆,刘彦毛,刘文珽,等.含孔钛合金扩散连接止焊层合板裂纹扩展特性试验.航空材料学报,2011,31(5):77-80.
[12]周克印,徐来,林兆荣,等.TC4钛板扩散连接后的疲劳断裂特性.机械强度.1998,20(2):112-115.
[13]Tuppena S J,Bachea M R,Voice W E.A fatigue assessment of dissimilar titanium alloy diffusion bonds.International Journal of Fatigue,2005,27:651-658.
[2]曹春晓.选材判据的变化与损伤容限钛合金的发展.金属学报,2002,38:125-128.
[3]朱知寿,王新南,童路,商国强.航空用损伤容限型钛合金研究与应用.中国材料进展,2010,29(5):14-17.
[4]Arriet A A J,Strizag.Optimal design of aircraft structures with damage tolerance requirements.Struct Multidisc Optim,2005,30(2):155-163.
[5]Bridier F,Villechaise P,Mendez J.Slip and fatigue crack formation processes in an a/b titanium alloy in relation to crystallographictexture on different scales.Acta.Materialia,2008,56:3951-3962.
[6]Atsushi S,Yoshihiko U,Masahiro J.Fatigue crack growth behavior on Ti-6Al-4V alloys under variable amplitude load sequences.In:Blom A F.Fatigue 2002,Proceedings of the Eighth International Fatigue Congress.Stockholm:EMAS,2002:2911.
[7]张纪奎,郦正能,邱志平,等.钛合金结构损伤容限设计可行性研究.航空学报,2009,30(4):763-767.
[8]李晓华,张军,韩秀全,等.钛合金层合梁SPF/DB制造工艺研究.航空制造技术,2011,16:66-69.
[9]李志强,郭和平.超塑成形/扩散连接技术的应用与发展现状.北京航空制造工程研究所,2004,11:50-52.
[10]侯红亮,王耀奇,李晓华,等.先进钣金成形技术在航空航天领域的应用(上).金属加工,2008,13:22-24.
[11]贺小帆,刘彦毛,刘文珽,等.含孔钛合金扩散连接止焊层合板裂纹扩展特性试验.航空材料学报,2011,31(5):77-80.
[12]周克印,徐来,林兆荣,等.TC4钛板扩散连接后的疲劳断裂特性.机械强度.1998,20(2):112-115.
[13]Tuppena S J,Bachea M R,Voice W E.A fatigue assessment of dissimilar titanium alloy diffusion bonds.International Journal of Fatigue,2005,27:651-658.