采用电子束物理气相沉积方法(EB-PVD)成功制备了直径为1000 mm,厚度为0.10~0.13 mm的镍基合金薄板.利用光学显微镜(OM)、扫描电子显微镜(SEM)和透射电子显微镜(TEM)等测试方法,对时效热处理前后试样形貌、析出相组成、高温拉伸性能进行了研究.结果表明,镍基合金薄板材料时效热处理后,晶粒长大,随时效时间延长,晶粒长大速率明显降低.在时效过程中,有细小碳化物颗粒在晶界析出,衍射花样分析表明,碳化物为FCC结构的(Cr,Fe)23C6.时效热处理后,镍基合金薄板材料高温拉伸性能有了很大提高,延伸率有一定的降低.
参考文献
[1] | Christopher L. Clay .High Speed Flight Vehicle Structures: An Overview[J].Journal of aircraft,2004(5):978-985. |
[2] | Sami M.High Performance RX2(tm) Ti 6242S Titanium for Re-useable Launch Vehicles Metallic Thermal Protection Systems[M].Long Beach,CA:AIAA,2000:5147. |
[3] | Kelly J Murphy et al.[J].Journal of Spacecraft and Rockets,2001,38(05):670. |
[4] | 康福伟,孙剑飞,张国庆,李周,敖洪峰,沈军.喷射成形镍基高温合金短期时效γ'相长大动力学[J].稀有金属材料与工程,2007(07):1205-1209. |
[5] | 张小明,田锋.日本超高温结构用金属材料的研究现状[J].稀有金属快报,2007(07):12-15. |
[6] | Yoo Y S .[J].Scripta Materialia,2005,53(03):81. |
[7] | 韩鸿硕 .[J].宇航材料工艺,1994,24(06):1. |
[8] | John T Dorsey.Metallic Thermal Protection System Technology Development:Concepts,Requirements and Assessment Overview[M].Nevada:Reno,2002:1. |
[9] | Krupp U et al.[J].Materials Science and Engineering A,2004,387-389:409. |
[10] | Krupp U.;Kane WM.;Liu XY.;Dueber O.;Laird C.;McMahon CJ. .The effect of grain-boundary-engineering-type processing on oxygen-induced cracking of IN718[J].Materials Science & Engineering, A. Structural Materials: Properties, Misrostructure and Processing,2003(1/2):213-217. |
[11] | Dymek S et al.[J].Scripta Materialia,200,43:343. |
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%