基于刀轨调整的叶片前后缘几何自适应加工  

Adaptive Machining for Blade Leading and Trailing Edges Based on Tool Path Adjustment

作　　者：陈振林 罗贵敏 朱正清 CHEN Zhenlin;LUO Guimin;ZHU Zhengqing(AECC Shenyang Liming Aero-Engine Co.,Ltd.,Shenyang 110043,China;AECC South Industry Co.,Ltd.,Zhuzhou 412002,China;Beihang University,Beijing 100191,China)

机构地区：[1]中国航发沈阳黎明航空发动机有限责任公司,沈阳110043 [2]中国航发南方工业有限公司,株洲412002 [3]北京航空航天大学,北京100191

出　　处：《航空制造技术》2023年第4期78-83,89,共7页Aeronautical Manufacturing Technology

摘　　要：航空发动机压气机叶片在前期净近成形工艺中,其前后缘曲率变化剧烈,形状特殊,无法直接成形,需要进行二次加工。然而,前期工艺会使叶片产生变形,理论数模已经无法适用于其二次加工。因此,为了解决因变形带来的前后缘加工问题,实现前后缘与叶身的光滑转接加工,提出了一种基于刀轨修改的叶片前后缘几何自适应的加工方法。首先,在前后缘附近的已成形区域上提取特征测量点并对其进行实测;然后,通过特征点实测数据分析叶片前期工艺变形情况,并基于变形数据建立叶片截面Z坐标值与变形规律的映射关系函数;最后,根据变形映射函数,相应地调整原始理论刀位文件,以调整完的刀轨实现叶片前后缘的自适应加工。以某型号航空发动机精锻叶片为例进行仿真试验验证,试验结果表明该方法优化效果显著,原理论刀位文件与调整后的刀位文件的加工误差相比,后者偏差基本在0.01 mm以内,极大程度地减少了加工误差。该方法能有效解决精锻叶片进排气边的光滑转接加工问题。In the net-near forming process of aero-engine compressor blade,the leading and trailing edges which have sharply changing curvature and cannot be directly formed need to be processed using NC machining.However,blade will be deformed in the early stage of the process,and the theoretical digital model can no longer be applied to the secondary processing.Therefore,in order to solve the problem of edges machining caused by blade deformation and realize the smooth transfer between blade edge and body,this manuscript presents an adaptive machining method for blade leading and trailing edges based on tool path adjustment.Firstly,the characteristic measurement points are extracted from the formed area near blade edges.And then,the deformation condition of blade in the early process is analyzed by the measurement data.Moreover,the mapping function between the Z coordinate value of the blade section and the deformation law is established according to deformation condition.Finally,the original nominal tool paths are adjusted according to the deformation mapping function and to realize the adaptive machining of blade edges using adjusted tool path.Taking the precision forging blade of a certain aero-engine as an example,the simulation results show that the optimization effect of proposed method is significant.Compared with the machining error using theoretical tool path,the adjusted tool path greatly reduces the machining error.The proposed method can effectively solve the problem of smooth transfer machining between blade edge and body of precision forging blades.

关 键 词：叶片 自适应加工 变形映射 刀轨修改 前后缘 

分 类 号：V263[航空宇航科学与技术—航空宇航制造工程]