前缘锯齿对边界层不稳定噪声的影响
收稿日期: 2016-01-13
修回日期: 2016-03-29
网络出版日期: 2016-04-08
基金资助
国家自然科学基金（51276149，51476134）；空气动力学国家重点实验室研究基金（SKLA20140201）
Effect of leading-edge serrations on boundary layer instability noise
Received date: 2016-01-13
Revised date: 2016-03-29
Online published: 2016-04-08
Supported by
National Natural Science Foundation of China (51276149, 51476134); State Key Laboratory of Aerodynamics Research Fund (SKLA20140201)
陈伟杰 , 乔渭阳 , 仝帆 , 段文华 , 刘团结 . 前缘锯齿对边界层不稳定噪声的影响[J]. 航空学报, 2016 , 37(12) : 3634 -3645 . DOI: 10.7527/S1000-6893.2016.0104
In order to explore the noise reduction law of the bionics leading-edge serrations, the effect of nine leading-edge serrations on blade laminar boundary layer instability noise has been investigated experimentally at low to moderate Reynolds number (Re=(2-8)×105) and different angle of attacks. It can be concluded that leading-edge serrations can decrease and even totally suppress blade laminar boundary layer instability noise. The noise reduction effect is very sensitive to both serration amplitude and serration wavelength, and the blade with larger amplitude and smaller wavelength has better noise reduction effect, which can reach a maximum of 30 dB. The noise reduction mechanism is attributed to the stream-wise vortices induced by the leading-edge serrations, which can affect blade downstream boundary layer flow and then destroy the acoustic feed-back loop. The leading-edge serrations have no effect on the instability noise peak frequency.
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