摘要
以某大型铝合金航空锻件为对象,针对整体一次加载成形时载荷过大的问题,提出了局部加载成形工艺方案,利用有限元法对锻件分段局部加载成形充填和载荷、多道次之间变形量分配及各道次加载顺序进行了研究。结果表明:该铝合金大锻件采用整体加载方案时,最大成形载荷为400 MN,超过了现有设备能够提供的载荷;采用局部加载3段2道次成形时,每道次成形载荷均可控制在300 MN以内,第1道次上下模具停止距离为55 mm,且加载方式为从锻件中间往两边加载,能够获得填充完整的锻件,满足现有设备要求。
For a large aluminum - alloy aircraft forging, a local loading was proposed to solve the problem of the excessive loading during the integral deforming. Then, the filling and loading, the multi - pass deforming assignment and the loading order for the local loading were studied by the finite elements method. The results show that when the aluminum - alloy forging is loaded integrate, the maximum de- forming load 400 MN in integral forming is over the load provided by the existing equipment. While 3 - segment 2 - pass deforms by the local loading, the maximum deforming load can be controlled within the 300 MN for every pass, and the stop distance between the up die and the bottom die is 55 mm. Meanwhile, a complete filling forging can be achieved to meet the existing equipment requirements by load- ing from the middle towards both sides.
出处
《锻压技术》
CAS
CSCD
北大核心
2017年第9期1-5,共5页
Forging & Stamping Technology
基金
国家自然科学基金资助项目(51575067)
关键词
铝合金锻件
局部加载
有限元法
成形载荷
充填性
aluminum-alloy forging
local loading
finite elements method
forming load
filling
