任意回转流面内叶型几何生成方法

doi:10.7527/S1000-6893.2014.0336

材料工程与机械制造

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任意回转流面内叶型几何生成方法

杨炯, 宁涛, 席平

北京航空航天大学机械工程及自动化学院, 北京 100191

收稿日期:2014-10-10 修回日期:2014-12-07 出版日期:2015-10-15 发布日期:2014-12-23
通讯作者: 宁涛, Tel.: 010-82316747 E-mail: ningtao@buaa.edu.cn E-mail:ningtao@buaa.edu.cn
作者简介:杨炯男, 博士研究生。主要研究方向: 计算机辅助设计与制造, 复杂曲线曲面造型。 Tel: 010-82316747 E-mail: jiong_yang@foxmail.com;宁涛男, 博士, 副教授, 硕士生导师。主要研究方向: 计算机辅助设计与制造。 Tel: 010-82316747 E-mail: ningtao@buaa.edu.cn;席平女, 博士, 教授, 博士生导师。主要研究方向: 飞行器数字化设计与制造, 复杂曲线曲面造型。 Tel: 010-82316768 E-mail: xiping@buaa.edu.cn
基金资助:
国家自然科学基金 (51075021)

Geometric generating method of blade profiles on arbitrary rotary flow surfaces

YANG Jiong, NING Tao, XI Ping

School of Mechanical Engineering and Automation, Beihang University, Beijing 100191, China

Received:2014-10-10 Revised:2014-12-07 Online:2015-10-15 Published:2014-12-23
Supported by:
National Natural Science Foundation of China (51075021)

摘要/Abstract

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。

关键词: 任意回转流面, 叶型, 几何造型, 任意中弧线, 前缘, 尾缘

Abstract:

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.

Key words: arbitrary rotary flow surface, blade profile, geometric modeling, arbitrary camber line, leading edge, trailing edge

中图分类号:

杨炯, 宁涛, 席平. 任意回转流面内叶型几何生成方法[J]. 航空学报, 2015, 36(10): 3483-3493.

YANG Jiong, NING Tao, XI Ping. Geometric generating method of blade profiles on arbitrary rotary flow surfaces[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3483-3493.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

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

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