针对航空发动机某级静子叶片表面加工形状复杂、导致叶片变形量控制困难的现状，通过高阶拟合曲线方法建立模具和叶片毛坯的三维模型，利用ANSYS/LS-DYNA 软件对叶片的辊轧过程进行模拟。根据模拟结果在叶片截面内选取节点，研究了由轧制摩擦系数、轧制速度、轧制下压量所引起的叶片型面在法向和横向的变形情况，得出了辊轧过程中叶片在不同参数下叶片型面变形的影响规律。研究表明：叶片最大变形区域在叶盆弧面斜率较大位置处，此区域叶片表面的曲率变化较大，应变所产生的误差也最大；变形量总体上随辊轧摩擦系数的增大而增大，随轧制速度的增大而减小，随轧制下压量的增大而增大。研究结果可为航空发动机某级静子叶片加工工艺的方案设计提供理论参考。
For a certain grade of the aviation engine stator blade surface machining, complex shapes may cause a difficult situation of blade deformation control. Through the high-order curve fitting method, the three-dimensional model of blank moleds and blades are established, and ANSYS/LS-DYNA software is used to simulate the blade rolling process. According to the results of the simulation of the blade cross section, nodes are select to study the blade surface's normal and lateral deformations caused by the rolling friction coefficient, the rolling speed, the rolling amount of pressure. Different parameters influencing the deformation of blade surface and the laws of the rolling process are obtained. The results show that the maximum deformation area of the blade is in the dorsal arc position of the steep slope, where the blade surface curvature is large. The error is also generated by the maximum strain. The deformation amount of the blade increases with the rolling friction coefficient decreasing, reduces with the rolling speed increasing, and increases with the rolling amount of pressure increasing. The results can provide a theoretical reference for a certain grade aircraft engine stator blade processing design.
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