摘要
针对残余应力导致某型直升机锻件表面裂纹萌生问题,系统研究了35Cr2Ni4MoA飞行安全件表面裂纹形成机理与防治方法。结果表明,35Cr2Ni4MoA锻后冷却方式对残余应力影响显著,空冷残余应力明显高于缓冷(坑冷),坑冷残余应力均值为1080 MPa。另外,残余应力受终锻温度影响显著,残余应力随终锻温度升高基本呈现增大趋势。锻后退火和吹砂可有效降低35Cr2Ni4MoA锻件残余应力。残余应力大于600 MPa时,35Cr2Ni4MoA锻件在盐酸下易产生应力腐蚀,且裂纹长度、宽度和深度与残余应力和腐蚀时间呈正相关。未进行退火处理以降低残余应力时,35Cr2Ni4MoA锻件不能进行酸洗处理。
Aiming at the problem of surface crack initiation caused by residual stress in a helicopter forging,the surface crack formation mechanism and prevention methods of 35Cr2Ni4MoA flight safety parts were investigated systematically.The results show that the post-forging cooling methods of 35Cr2Ni4MoA have a significant effect on the residual stress.The residual stress of air cooling is significantly higher than that of slow cooling(pit cooling).The average residual stress of pit cooling is 1080 MPa.In addition,the residual stress is significantly affected by the final forging temperature,and the residual stress basically increases with the increase of final forging temperature.Both post-forging annealing and shot blasting can effectively reduce the residual stress of 35Cr2Ni4MoA forgings.When the residual stress is greater than 600 MPa,35Cr2Ni4MoA forgings are prone to stress corrosion under hydrochloric acid condition.And the crack length,width and depth are positively correlated with residual stress and corrosion time.When annealing is not performed to reduce the residual stress,acid treatment can not be carried out on 35Cr2Ni4MoA forgings.
作者
孙朝远
谢静
宁永权
周杰
SUN Chao-yuan;XIE Jing;NING Yong-quan;ZHOU Jie(Chongqing Key Laboratory of Advanced Mold Intelligent Manufacturing,College of Materials Science and Engineering,Chongqing University,Chongqing 400044,China;China National Erzhong Group Deyang Wanhang Die Forging Co.,LTD.,Deyang 618000,China;School of Materials Science&Engineering,Northwestern Polytechnical University,Xi′an 710072,China)
出处
《塑性工程学报》
CAS
CSCD
北大核心
2023年第3期107-112,共6页
Journal of Plasticity Engineering
基金
国家重点研发计划(2022YFB3400143)。
