利用环面工具加工过渡曲面时经常发生整体干涉,主要原因是缺乏对复杂环面工具加工复杂曲面时刀位可行域的研究。虽然采用常规的优化方法在大范围内对可行刀位进行搜索是可行的,但是需要耗费大量时间。为了避免刀具与过渡曲面的干涉并同时提高加工效率,研究了一种更加符合此区域结构特点的刀位优化算法,使得叶根过渡曲面得以无干涉地整体宽行加工。通过对典型叶根过渡曲面的可行刀位进行研究,发现其可行域形状为盾形,且行宽最大的刀位位于该盾形区域的两个底部边界上,有时位于该边界的端点上。根据该原理提出一种最优刀位搜索方法——沿着盾形区域底部边界搜索,应用最优化的刀位可行域以获得高的加工效率。以某航空发动机叶片的叶根过渡曲面为例进行了刀位优化计算、仿真和加工实验,验证了该方法在叶根过渡曲面加工中的有效性。 The main reason is that there is a lack of research on the feasible region of the tool bit when machining complex curved surfaces with toric tools. Although it is possible to search viable routines on a large scale using conventional optimization methods, it takes a lot of time. In order to avoid the interference between the tool and the transitional surface and improve the machining efficiency at the same time, a tool position optimization algorithm that is more in line with the structural characteristics of the region is studied. The blade root transition surface can be widened without interference. By researching the feasible blade position of the typical blade root transition surface, the feasible shape of the blade is found to be shield-shaped, and the location with the largest line width is located on the two bottom boundaries of the shield region, sometimes at the end of the boundary. According to this principle, an optimal cutter search method is proposed - searching along the bottom boundary of shield-shaped area and applying the optimal cutter-bit feasible area to obtain high machining efficiency. Taking the blade root transition surface of an aeronautic engine blade as an example, the tool position optimization calculation, simulation and machining experiment are carried out to verify the effectiveness of this method in the machining of blade root transition surface.