锻压技术

航空发动机铝合金筒体关键件锻造成形工艺

英文标题：Forging process of key parts in aluminum alloy cylinder for aero-engine

作者：邱磊蔡靖凯孙敏郑黎

分类号：TG386

出版年,卷(期):页码：2018,43(4):16-21

摘要：

以某航空发动机2A70铝合金筒体关键零部件为研究对象，此锻件在实际生产中经常出现毛边边角部开裂，且裂纹延伸至锻件本体，从而导致材料合格率不高。针对此问题，将压扁预制坯改进为挤压预制坯，再进行终锻，此外建立了现行的压扁+终锻工艺以及改进的挤压+终锻工艺的三维有限元模型，并对其成形过程进行分析。通过模拟结果显示，采用预挤压再进行锻压终成形的方式减少了角部的应力、应变集中以及出现裂纹和孔洞的问题，且变形分配更加合理。实验结果表明，采用挤压+终锻的工艺不仅减少了现行的压扁+终锻工艺成形过程中非加工表面折叠、毛边处开裂的问题，而且终锻件各部分晶粒大小分布均匀，并且将此锻件的材料利用率由51%提高到了79.5%以上。

Taking the key components of aluminum alloy 2A70 cylinder for an aero-engine as the research object, the forgings crack at the edge and corner usually in the actual production, and the cracks extend to the center of forgings, which leads to a low qualified rate of products. In order to solve the above problem, the preformed blank of flattening was replaced by extrusion and then followed by a final forging. In addition, three-dimensional finite element models of the current process of flattening+final forging and the promoted process of extrusion+final forging were built, and their forming processes were analyzed. The simulation results show that the process of extrusion+final forging reduces stress-strain concentration at the corner area and eliminates crack and hole defects, and the material flow is more reasonable. The experimental verification shows that the process of extrusion+final forging also reduces folding in the non-machined surface and crack at edge and corner occurred in the current process of flattening+final forging, and the grain sizes are uniformity in all area of final forgings. Thus, the material utilization of the forgings increases from 51% to more than 79.5%.

基金项目：

国家自然科学基金资助项目（51605307）；辽宁省教育厅一般项目（LGD2016020）

邱磊(1980-)，男，学士，工程师；E-mail：24801558@qq.com；通讯作者：郑黎（1981-），男，博士，讲师；E-mail:zhengli_1115@163.com

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