刷毛翼型尾缘噪声控制实验研究  

Experiment on Noise Control of Trailing Edge Brushes

作　　者：许影博[1] 李晓东[1] 何敬玉[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《南京航空航天大学学报》2011年第5期612-616,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家重点基础研究发展计划("九七三"计划)(2007CB714604)资助项目

摘　　要：利用具有全消声环境的低速开口风洞研究了采用翼型尾缘刷毛来控制翼型噪声的方法,研究了不同迎角情况下不同长度和间距刷毛对翼型远声场气动噪声的影响以及翼型表面压力的影响,并把该方法与锯齿尾缘降噪方法对比,研究了不同工况下两种降噪方案对降噪效果的影响。实验结果表明,翼型尾缘附加刷毛是一种可行的降噪方案,尤其对中低频段具有比较明显的降低效果;降噪效果与刷毛的间距和长度有关;尾缘刷毛与锯齿尾缘相比具有更优的降噪效果。附加刷毛对翼型壁面动态压力载荷的影响较小。Some experimental investigations are done on suppressing the airfoil noise by trailing edge brushes.All the experiments are carried out in the low-speed open jet wind tunnel which is in the anechoic chamber.The study is focused on the influence of the angle of attack of the airfoil on the far field noise and the airfoil surface pressure.In addition,the effect of the proposed method and that of the serrated trailing edge method on noise reduction are compared under different operating conditions.The result shows that the trailing edge brush is a feasible way to reduce the airfoil noise,especially for the low frequency component.It is revealed that the noise reduction is related to the length and interval of brush.And the trailing edge brushes are superior to a serrated trailing edge in noise reduction.Meanwhile,trailing edge brushes have little effect on the surface pressure of the airfoil.

关 键 词：尾缘噪声 刷毛型尾缘 远声场 翼型表面动态压力 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]