摘要
压气机叶片极易出现各类损伤缺陷,因此研究其修复技术有十分重大的意义。利用某有限元软件,使用顺序热-力耦合模型对受损叶片氩弧焊堆焊修复过程进行了数值模拟,同时使用Inconel718合金进行单道堆焊试验。结果表明,数值仿真结果与试验结果吻合良好,所用有限元模型能有效模拟氩弧焊堆焊修复过程。分析不同堆焊层数、不同堆焊方案下叶片温度场、热变形和残余应力情况,模拟过程中熔池形状与实际熔池形状较为吻合,热源中心温度达到堆焊要求;通过对比不同层数下热变形量和残余应力值发现,变形量和残余应力值会随着堆焊层数的增加而增大;顺序堆焊在冷却后的变形和残余应力均大于往复堆焊;为了减小叶身残余应力,应该在保证修复质量的前提下,尽量减少叶尖修复的长度和堆焊层数,并采用往复堆焊。最后对比修复后叶片和完好叶片的固有频率,分析发现二者频率几乎相等,表明使用堆焊对损伤叶片进行修复具有较高的修复质量。
Compressor blades are very prone to various types of damage defects,so the study of its repair technology is of great significance.The process of repairing damaged blade by argon arc welding was numerically simulated by using the sequential thermo-force coupling model with a finite element software,and the single pass welding experiment was carried out by using Inconel 718 alloy.The results show that the numerical simulation results are in good agreement with the experimental results,and the finite element model can effectively simulate the repair process of argon arc surfacing welding.The temperature field,thermal deformation and residual stress of the blade under different surfacing layers and different surfacing schemes were analyzed.The shape of the molten pool in the simulation process was consistent with the actual shape of the molten pool,and the central temperature of the heat source met the requirements of surfacing welding.By comparing the thermal deformation and residual stress under different layers,it is found that the deformation and residual stress will increase with the increase of the number of surfacing layers.The deformation and residual stress of sequential surfacing welding after cooling are greater than reciprocating surfacing welding.In order to reduce the residual stress of the blade body,the length of blade tip repair and the number of surfacing layers should be reduced as far as possible under the premise of ensuring the repair quality,and reciprocating surfacing should be used.Finally,the natural frequency of repaired blades and intact blades were compared,and the two frequencies were almost equal,indicating that surfacing repair had no significant effect on blade performance.
作者
张莹
罗睿敏
梁帅
Zhang Ying;Luo Ruimin;Liang Shuai(Civil Aviation University of China,Tianjin 300300,China;Flight Test Center,Commercial Aircraft Corporation of China,Shanghai 200232,China)
出处
《航空科学技术》
2024年第7期76-86,共11页
Aeronautical Science & Technology
基金
国家自然科学基金(52172360)
先进航空动力创新工作站项目(HFY-KZ-2022-J09023)。
关键词
航空发动机叶片
堆焊修复
温度场
残余应力与变形
振型分析
aero engine blade
surfacing repair
temperature field
residual stress and deformation
vibration modal analysis
