曲率连续的压气机叶片前缘设计方法

推进技术 ›› 2013, Vol. 34 ›› Issue (11): 1474-1481.

曲率连续的压气机叶片前缘设计方法

宋寅,顾春伟

清华大学热能工程系/热科学与动力工程教育部重点实验室,北京 100084;清华大学热能工程系/热科学与动力工程教育部重点实验室,北京 100084

发布日期:2021-08-15
作者简介:宋寅(1987—),男,博士生,研究领域为叶轮机械气动热力学。 E-mail:song-y04@mails.tsinghua.edu.cn
基金资助:
国家自然科学重点基金(51136003)。

Continuous Curvature Leading Edge of Compressor Blading

Key laboratory for Thermal Science and Power Engineering of Ministry of Education/Department of Thermal Engineering, Tsinghua University, Beijing 100084, China;Key laboratory for Thermal Science and Power Engineering of Ministry of Education/Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

Published:2021-08-15

摘要/Abstract

摘要： 为优化压气机叶片前缘形状以改善叶型性能,提出了一种曲率连续叶片前缘的设计方法。前缘设计过程基于三次Bezier曲线,只需引入三个设计变量。使用该方法对可控扩散叶型前缘进行了重新设计,并采用计算流体力学方法比较了不同前缘形状对于叶型气动性能的影响。计算结果表明新型前缘在来流马赫数0.2和0.6两种下均能够有效抑制前缘分离泡的产生和发展,与圆弧形和椭圆形前缘相比叶型攻角范围分别扩大约1.2°和2.5°。对跨声转子叶片的前缘进行重新设计后,提高了动叶效率,扩大了稳定工作范围。 

关键词: 压气机; 前缘; 曲率; 气动性能 

Abstract: A design method for continuous curvature leading edge was proposed in order to optimize the leading edge shape of compressor blade and to improve the performance. The design method was based on cubic Bezier spline and only required three independent design variables. The leading edge of a controlled diffusion airfoil compressor blade was redesigned with the above method, and the effects of leading edge on blade performance were analyzed by computational fluid dynamic method. It is found that the leading edge separation bubble is effectively suppressed by the new type of leading edge at Mach numbers ranging from 0.2to 0.6. Compared with circular and elliptical leading edge, the working range is enlarged by 1.2° and 2.5°, respectively. Furthermore, the leading edge of a transonic rotor was also redesigned, and the improvement of efficiency and working range was achieved.

Key words: Compressor;Leading edge;Curvature;Aerodynamic performance

宋寅,顾春伟. 曲率连续的压气机叶片前缘设计方法[J]. 推进技术, 2013, 34(11): 1474-1481.

SONG Yin, GU Chun-wei. Continuous Curvature Leading Edge of Compressor Blading[J]. Journal of Propulsion Technology, 2013, 34(11): 1474-1481.

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