研究了典型的损伤容限型钛合金Ti-6A1-4V ELI(TC4-DT)的断裂韧度KIC、疲劳裂纹扩展速率da/dN以及疲劳门槛值△Kth等损伤容限性能与微观组织的关系,讨论了不同应力比(R值)条件下片状组织与双态组织的疲劳裂纹扩展特性,并与Ti-6A1-4V(TC4)钛合金进行了比较分析.研究结果为高损伤容限型钛合金的微观组织设计和探讨微观组织对损伤容限性能的影响机理奠定了基础.
参考文献
| [1] | 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 |
| [2] | Wanhill 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 |
| [3] | 中国航空材料手册编辑委员会.中国航空材料手册[M].北京:中国标准出版社,2002 |
| [4] | Campbell J E;Underwood J H;Gerberich W W;汪一麟,邵本逑.断裂力学在选材方面的应用[M].北京:冶金工业出版社,1992 |
| [5] | 陶春虎;曹春晓;张卫方.航空用钛合金的失效及其预防[M].北京:国防工业出版社,2002 |
| [6] | Atsushi Sugeta;Yoshihiko Uematsu;Masahiro Joho.Fatigue Crack Growth Behavior on Ti-6Al-4V Alloys under Variable Amplitude Load Sequences[A].Stockholm:EMAS,2002:2911. |
| [7] | Suresh S;王中光.材料的疲劳[M].北京:国防工业出版社,1993 |
| [8] | Yuen .Correlations between Fracture Surface Appearance and Fracture Mechanics Parameters for Stage-Ⅱ Fatigue Crack-Propagation in Ti-6Al-4V[J].Metallurgical and Materials Transactions,1996,5(08):1833. |
| [9] | Yoder G R;Cooley L A;Crooker T W .Quantitative Analysis of Microstructural Effects of Fatigue Crack Growthin Widmanstaetten Ti-6Al-4V and Ti-8Al-1Mo-1V[J].Engineering Fracture Mechanics,1992,11(04):805. |
| [10] | Nalla R K;Boyce B L;Campbell J P et al.Influence of Microstructure on High-cycle Fatigue of Ti-6Al-4V:Bimodal vs.Lamellar Structure[J].Metallurgical and Materials Transactions A:Physical Metallurgy and Materials Science,2002,33:899. |
上一张
下一张
上一张
下一张
计量
- 下载量()
- 访问量()
文章评分
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%