任意回转流面内叶型几何生成方法  

Geometric generating method of blade profiles on arbitrary rotary flow surfaces

作　　者：杨炯[1] 宁涛[1] 席平[1] 

机构地区：[1]北京航空航天大学机械工程及自动化学院,北京100191

出　　处：《航空学报》2015年第10期3483-3493,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(51075021)~~

摘　　要：传统的叶型设计方法对流道内的流面一般采用平面、柱面或锥面进行流面简化。提出了一种任意回转流面内的叶型几何生成方法,该方法基于中弧线加厚度分布的方式生成叶型。首先,在流面内生成中弧线,中弧线上的点可以看作由定义的基叠点开始,沿着子午面流线移动一段距离和沿周向回转一定弧长得到的,将中弧线分段,求得一系列回转流面内中弧线上的点;然后,在流面内加上厚度分布,获得叶盆和叶背曲线。基于叶盆、叶背曲线在前、尾缘处关于中弧线对称的假设,给出了一种兼容圆形和椭圆形前、尾缘造型方法,生成前、尾缘后通过调整叶盆、叶背曲线的起点、终点位置和切矢,保证连接处G1连续。使用MFC和NX8.0联合开发的方式,开发出了叶片快速造型系统,实现了回转流面内的叶型几何设计,与锥面内的叶型对比表明该方法生成的叶型更符合气流流动趋势。Generally,flow surfaces are reduced to planes,cylindrical surfaces or conical surfaces in traditional blade profile design method.A blade profiles geometric design method on arbitrary rotary flow surfaces is presented.In this method,blade＇s profiles are generated by traditionally distributing thickness along a camber line method.First,a camber line is generated on the flow surface.Points on the camber line are obtained by stacking point moving along meridional streamline at a distance and rotating circumferentially at the same time.The camber line is divided into series of segments,and arrays of points on flow surface are acquired.Then,thickness on each point is distributed,obtaining pressure line and suction line.Based on the assumptions of the symmetry of pressure and suction line about camber line at the leading edge and trailing edge point,a leading edge and trailing edge generating method is presented.After an elliptical or circular leading edge and trailing edge is created,by adjusting the position and tangent vector of the starting point and end point of suction line and pressure line,G1 continuity at junction points can be guaranteed.A blade geometric modeling system has been developed using MFC and NX8.0.The goal of generating blade profiles on arbitrary rotary flow surfaces is achieved.Compared with airfoils generating on conical surfaces,airfoils generated by this method is closer to airflow trend in flow passage.

关 键 词：任意回转流面 叶型 几何造型 任意中弧线 前缘 尾缘 

分 类 号：V263.1[航空宇航科学与技术—航空宇航制造工程] TP391.7[自动化与计算机技术—计算机应用技术]