大型铝合金框梁结构航空模锻件淬火残余应力分析  

Analysis of Quenching Residual Stress for Large-Size Aluminum Alloy Aircraft Forging With Frame and Beam Structure

作　　者：王少辉[1] 易幼平[1] 黄始全[1] 廖国防[1] 

机构地区：[1]中南大学机电工程学院,长沙410083

出　　处：《宇航材料工艺》2011年第4期85-88,共4页Aerospace Materials & Technology

基　　金：国家973计划资助项目(2010CB731701);国家重大专项资助项目(2009ZX04005-011)

摘　　要：开展了新型7085铝合金材料高温拉伸试验,得到了其基本性能参数与力学模型,运用ABAQUS有限元软件对7085铝合金框梁结构航空模锻件淬火过程进行了数值仿真,研究了淬火工艺参数与方式对残余应力分布规律的影响。研究表明:框梁结构航空模锻件淬火残余应力主要集中于腹板与筋板交汇处,呈现外压内拉的分布特点;淬火温度对残余应力有显著影响,提高淬火温度可有效降低残余应力;固溶温度对淬火残余应力的影响较小,对于大尺寸框梁模锻件,入水方式及转移时间对淬火残余应力的影响甚微。The mechanical properties of 7085 aluminum alloy have been obtained by high temperature tensile test.The quenching process of 7085 aluminum alloy aircraft forging with frame and beam structure has been simulated by FEM code ABAQUS.The influence of different quenching technologies on the magnitude and distribution of quenching residual stress has been investigated.The results show that the residual stresses of the forging are mainly concentrated on the interface of the rib and web with the characteristics of external compressive and inner tensile.The quenching temperature has significant influence on the magnitude of residual stress,and improvement of quenching temperature is beneficial to decreasing the residual stress.The solution treatment temperature,the method of entering water and the transfer time for large-size aircraft forging with frame and beam structure have little effect on residual stress.

关 键 词：7085铝合金 框梁模锻件 淬火残余应力 有限元 

分 类 号：TG156.3[金属学及工艺—热处理]