钛合金断裂韧性与屈强差的关系初探

1.北京航空材料研究院,北京,100095;兰州理工大学甘肃省省部共建有色金属新材料国家重点实验室,甘肃,兰州,730050

2.北京航空材料研究院,北京,100095

3.北京航空材料研究院,北京,100095

4.北京航空材料研究院,北京,100095

5.北京航空材料研究院,北京,100095

基金项目: 国家高技术研究发展计划(863计划)(2002AA305107)

Relationship between Fracture Toughness and Proof-Ultimate Strength Difference of Ti Alloy

研究了近αβ型TA15,α+β型Ti6Al4V及亚稳定β型TB8 3种钛合金断裂韧性与屈服强度、强度极限的关系,提出了屈强差的概念.结果表明:屈强差增大,断裂韧性增加,且对Ti6Al4V和TB8两者之间有线性关系:β热变形或β热处理是提高屈强差和断裂韧性的有效方法.

[1]	Tuppor N G.Fracture Prevention and Control[M].Calif:Los Angeles,1972:159.
[2]	束德林.金属力学性能[M].北京:机械工业出版社,1987:116.
[3]	黄明志.金属力学性能[M].西安:西安交通大学出版社,1986:130.
[4]	储武扬.断裂与环境断裂[M].北京:科学出版社,2000:231.
[5]	Lttjering G .Influence of Processing on Microstructure and Mechanical Properties of α+β Titanium Alloys[J].Materials Science and Engineering,1998,A243:32-45.
[6]	Wanhill R J H .Ambient Temperature Crack Growth in Titanium Alloys and its Significance for Aircraft Structures[J].Aeronautical Journal,1977,81:68-82.
[7]	王金友;葛志明;周彦邦.航空用钛合金[M].上海:上海科学技术出版社,1985:208-231.
[8]	Jafee R I;Burte H M ed.Titanium Science and Technology[M].New York;London:Plenum Press,1973:1257-1270.
[9]	Semiatin S L.Metals Handbook[M].Ohio:ASM,1988:267-287.
[10]	朱知寿;钟鸣等.Optimizing Relationship between Strength and Fracture Toughness of Ti-15Mo-2.7Nb-3Al-0.2Si Titanium Alloy[J].金属学报,1999,35(01):157-159.

上一张下一张

计量

作者相关

文章评分