基于热-力耦合的航空发动机叶片堆焊修复数值模拟OA

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.