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航空发动机叶片具有复杂的加工边界,其电解加工的过程仿真是加工预测的重要手段。而传统基于有限元法的腐蚀过程仿真需要反复划分网格,且存在边界上计算精度不足的问题。提出利用等几何法原理提升叶片电解加工数值仿真精度的思路,采用NURBS基函数替代原有拉格朗日基函数建立加工间隙物理场的求解方程组,解决由于NURBS基函数在边界处非插值特性引起的Dirichlet边界条件施加误差。将阳极边界的腐蚀位移转化为其控制顶点位移,避免反复划分网格所占用的计算时间,提升过程仿真精度。最后,通过试验证明该方法的有效性。
Aeroengine blades have complex processing boundaries, and the process simulation of electrolytic machining is an important method of processing prediction. The traditional finite element method based on the corrosion process simulation needs repeated meshing, and there is the problem of insufficient computational accuracy on the boundary. The idea of using the geometric principle to improve the numerical simulation precision of the blade electrolysis is proposed. The NURBS basis function is used to replace the original Lagrange basis function to establish the equations for solving the physical field of the machining gap. As a result of the NURBS basis function at the boundary, The resulting Dirichlet boundary conditions impose errors. The corrosion displacement at the anode boundary is transformed into the control vertex displacement so as to avoid the calculation time occupied by repeatedly dividing the grid and improve the simulation accuracy of the process. Finally, the effectiveness of this method is proved through experiments.