锻压技术

预拉变形量对2219铝合金固溶处理后晶粒度的影响

英文标题：Influence of pretension deformation amount on grain size of aluminum alloy 2219 after solution treatment

分类号：TG146.2

出版年,卷(期):页码：2018,43(6):162-165

摘要：

针对运载火箭贮箱2219铝合金瓜瓣拉形成形过程中的粗晶问题，为制定合理的2219铝合金瓜瓣多道次拉形成形工艺，将退火态平板拉伸试件预拉到不同变形量后进行固溶处理，然后测定其晶粒度，建立固溶处理前预拉变形量和晶粒度之间的关系曲线，研究固溶处理前预拉变形量对2219铝合金固溶处理后晶粒度的影响。结果表明，不同固溶处理前预拉变形量对固溶热处理后晶粒尺寸影响显著，且存在一个临界变形量，预拉变形量小于3%时，晶粒尺寸与原始晶粒尺寸相当；当预拉变形量处于3%~5%区间时，随着预变形量的增大，晶粒尺寸不断增大。

For the problem of coarse grain in the stretch forming process of aluminum alloy 2219 scalloped segment of carrier rocket tank, in order to develop a reasonable multipass forming process, the solution treatment was conducted after the tensile specimens with annealing state were prestretched under different deformation amounts, and the grain size was measured. Then, the relationship curve between the pretension deformation before solution treatment and the grain size was established, and the influence of pretension deformation before solution treatment on the grain size of aluminum alloy 2219 after solution treatment was studied. The results show that the influences of different prestretch deformation amount on the grain size after solution treatment are significant, and there is a critical deformation amount. When the pretension deformation amount is less than 3%, the grain size is equal to the original grain size. However, when the pretension deformation amount is within 3%-5%, with increasing of the deformation amount, the grain size increases.

基金项目：

天津市科技支撑项目（17YFZCGX00530）

张杰刚（1980-），男，硕士研究生；Email：664217923@qq.com；通讯作者：李继光（1981-），男，博士，高级工程师；Email：jiguangli2008@126.com

参考文献：

［1］O′Donnell M, Leacock A G, Banabic D, et al. The effect of prestrain and solution heat treatment on the formability of a 2024 aluminium alloy
［J］. International Journal of Material Forming, 2008, 1(1):257-260.

［2］O′Donnell M, Banabic D, Leacock A G, et al. The effect of prestrain and inter-stage annealing on the formability of a 2024 aluminium alloy
［J］. International Journal of Material Forming, 2008, 1(S1): 253-256.

［3］Wisselink H H, Van Den Boogaard A H. Finite element simulation of the stretch forming of aircraft skins
［A］. Proc. Numisheet’05
［C］. Detroit: American Institute of Physics, 2005.

［4］Straatsma E N, Velterop L. Influence of heat treatments and straining steps on mechanical properties in the stretch forming process
［A］. Proceedings of 9th International Conference on Aluminium Alloys
［C］. Brisbane: Institute of Materials Engineering Australasia Ltd., 2004.

［5］崔忠圻. 金属学与热处理
［M］. 北京:机械工业出版社，1999.

Cui Z Q. Metallography & Heat Treatment
［M］. Beijing: China Machine Press, 1999.

［6］李小强, 李东升, 周贤宾,等. 预变形对LY12 铝合金板热处理后晶粒度的影响
［J］. 材料科学与工艺，2010，18(2)：238-241.

Li X Q, Li D S, Zhou X B, et al. Effect of predeformation on the grain size of LY 2024 aluminium alloy sheet after heat treatment
［J］. Material Science ＆ Technology, 2010，18(2)：238-241.

［7］李丁, 刘旭东. 蒙皮零件拉伸粗晶的控制研究
［J］. 航空制造技术, 2011, (18):81-83.

Li D, Liu X D. Research of controlling coarsegrain of stretching skin part
［J］. Aeronautical Manufacturing Technology, 2011, (18)：81-83.

［8］王昆, 万敏. 铝合金拉形粗晶临界预应变曲线的建立及应用
［J］. 北京航空航天大学学报，2013，39(4)：508-511.

Wang K, Wan M. Determination and application of coarsegrain critical prestrain curve to aluminium alloy stretch forming
［J］. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(4)：508-511.

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