重型燃机叶片锻造过程数值模拟与工艺优化  

Numerical simulation and process optimization of forging process of a gas turbine compressor blade

作　　者：吕成[1] 张立文[1] 王照坤[2] 陈亚莉[2] 郑渠英 王丹[2] 

机构地区：[1]大连理工大学材料科学与工程学院,辽宁大连116024 [2]沈阳黎明航空发动机集团,辽宁沈阳110043

出　　处：《大连理工大学学报》2007年第3期353-357,共5页Journal of Dalian University of Technology

基　　金：国家"863"计划资助项目(2004AA503010)

摘　　要：高温锻造过程中,坯料内的温度场、应变场等热力参数对锻件内的裂纹损伤和微观组织有重要影响.利用刚粘塑性有限元法,对某重型燃机叶片的锻造过程进行了有限元数值模拟,得到了锻造过程中锻件内温度场、应变场以及锻造载荷随时间的变化规律,并在此基础上结合裂纹损伤和修复机制以及再结晶组织演化规律,提出了一种优化的锻造工艺方案.即在终锻尺寸上公差基础上欠压4 mm进行预锻,预锻温度1160℃,终锻温度1120℃.实际锻造工艺试验验证了工艺方案的可行性,为该工艺的工程应用奠定了科学基础.In high-temperature forging processes, the thermomechanical field variables, such as temperature and strain, have an important influence on the inner crack damage and microstructure in the forging part. The forging process of a gas turbine compressor blade is simulated using 3D rigid-viscoplastic finite element （FE） method. FE analysis provides detailed information on the thermomechanical field variables such as temperature and strain and forging loads, which can be incorporated into process design. On the basis of these results, an optimized process is put forward incorporated with the mechanism of crack damage and recovery and evolvement laws of reerystallized structure. The optimized parameters are 1 160 ℃ of preforging temperature and 1 120 ℃ of finish forging temperature, and the preforging is conducted under 4 mm forging stroke on the basis of finish forging. The feasibility of optimized process is verified through comparisons with industrial trials. The results can provide the scientific basis for engineering application of the process.

关 键 词：裂纹损伤 微观组织 叶片 锻造 工艺优化 数值模拟 

分 类 号：TG316[金属学及工艺—金属压力加工]