ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Blade boundary layer instability noise with trailing edge serrations
Received date: 2015-12-31
Revised date: 2016-08-10
Online published: 2016-08-12
Supported by
National Natural Science Foundation of China (51276149, 51476134); State Key Laboratory of Aerodynamics Research Fund (SKLA20140201)
The effect of three trailing edge serrations of the same wavelength (4% of the chord length) and different amplitudes (5%, 10% and 15% of the chord length) on blade laminar boundary layer instability noise is investigated experimentally at low to moderate Reynolds number (2×105-8×105) and different angle of attacks. It can be concluded that at zero angle of attack, trailing edge serrations can reinforce or even induce boundary layer instability noise to lead to an increase of the blade self-noise. At larger angle of attack, instability noise is reduced or even totally suppressed by the trailing edge serrations, resulting in a maximum noise reduction of 40 dB. The noise reduction mechanism can be attributed to the destruction of the acoustic feed-back loop, which is essential for the generation of instability noise, by the trailing edge serrations. Trailing edge serrations will decrease the instability tonal noise frequency, and the instability noise frequency is lower with larger serration amplitude.
CHEN Weijie , QIAO Weiyang , TONG Fan , DUAN Wenhua , LIU Tuanjie . Blade boundary layer instability noise with trailing edge serrations[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(11) : 3317 -3327 . DOI: 10.7527/S1000-6893.2016.0232
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