尾缘锯齿结构对叶片边界层不稳定噪声的影响

doi:10.7527/S1000-6893.2016.0232

流体力学与飞行力学

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尾缘锯齿结构对叶片边界层不稳定噪声的影响

陈伟杰, 乔渭阳, 仝帆, 段文华, 刘团结

西北工业大学动力与能源学院, 西安 710129

收稿日期:2015-12-31 修回日期:2016-08-10 出版日期:2016-11-15 发布日期:2016-08-12
通讯作者: 乔渭阳,男,博士,教授,博士生导师。主要研究方向:叶轮机气体动力学,航空发动机气动声学。Tel.:029-88482195,E-mail:qiaowy@nwpu.edu.cn E-mail:qiaowy@nwpu.edu.cn
作者简介:陈伟杰,男,博士研究生。主要研究方向:叶轮机械气动声学。Tel.:13468775824,E-mail:cwj@mail.nwpu.edu.cn;乔渭阳,男,博士,教授,博士生导师。主要研究方向:叶轮机气体动力学,航空发动机气动声学。Tel.:029-88482195,E-mail:qiaowy@nwpu.edu.cn
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）

Blade boundary layer instability noise with trailing edge serrations

CHEN Weijie, QIAO Weiyang, TONG Fan, DUAN Wenhua, LIU Tuanjie

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710129, China

Received:2015-12-31 Revised:2016-08-10 Online:2016-11-15 Published:2016-08-12
Supported by:
National Natural Science Foundation of China (51276149, 51476134); State Key Laboratory of Aerodynamics Research Fund (SKLA20140201)

摘要/Abstract

摘要：

实验研究了不同雷诺数（2×10⁵~8×10⁵）、不同攻角状态下，3种相同波长（4%弦长）不同振幅（分别为5%、10%、15%弦长）尾缘锯齿结构对叶片层流边界层不稳定噪声的影响。研究表明，在0°攻角状态下，尾缘锯齿会增强甚至诱导产生新的不稳定噪声，显著增大叶片自噪声；在大攻角状态下，尾缘锯齿会减弱甚至完全抑制不稳定噪声，降噪量高达40 dB，降噪机制在于尾缘锯齿结构破坏了不稳定噪声产生所需的声学反馈回路。尾缘锯齿会降低不稳定噪声频率，且锯齿振幅越大，不稳定噪声频率越低。

关键词: 尾缘锯齿, 层流边界层, 不稳定噪声, 声学反馈回路, T-S波

Abstract:

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.

Key words: trailing edge serrations, laminar boundary layer, instability noise, acoustic feed-back loop, T-S wave

中图分类号:

V231

陈伟杰, 乔渭阳, 仝帆, 段文华, 刘团结. 尾缘锯齿结构对叶片边界层不稳定噪声的影响[J]. 航空学报, 2016, 37(11): 3317-3327.

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.

参考文献

[1] HOWE M S. A review of the theory of trailing edge noise:NASA CR-3021[R]. Washington, D.C.:NASA, 1978.
[2] BROOKS T F, POPE D S, MARCOLINI M A. Airfoil self-noise and prediction:NASA RP-1218[R]. Washington, D.C.:NASA, 1989.
[3] PATERSON R W, VOGT P G, FINK M R, et al. Vortex noise of isolated airfoils[J]. Journal of Aircraft, 1973, 10(5):296-302.
[4] TAM C K W. Discrete tones of isolated airfoil[J]. Journal of the Acoustical Society of America, 1974, 55(6):1173-1177.
[5] ARBEY H, BATAILLE J. Noise generated by airfoil profiles placed in a uniform laminar flow[J]. Journal of Fluid Mechanics, 1983, 134:33-47.
[6] LOWSON M V, FIDDES S P, NASH E C. Laminar boundary layer aeroacoustic instabilities[C]//32nd Aerospace Sciences Meeting & Exhibit. Reston:AIAA, 1994.
[7] NASH E C, LOWSON M V, MCALPINE A. Boundary-layer instability noise on aerofoils[J]. Journal of Fluid Mechanics, 1999, 382:27-61.
[8] KINGAN M J, PEARSE J R. Laminar boundary layer instability noise produced by an aerofoil[J]. Journal of Sound and Vibration, 2009, 322:808-828.
[9] PLOGMANN B, HERRIG A, WURZ W. Experimental investigations of a trailing edge noise feedback mechanism on a NACA 0012 airfoil[J]. Experiments in Fluids, 2013, 54:1480.
[10] GOLUBEV V V, NGUYEN L, MANKBADI R R, et al. On flow-acoustic resonant interactions in transitional airfoils[J]. International Journal of Aeroacoustics, 2014, 13(1):1-38.
[11] DESQUESNES G, TERRACOL M, SAGAUT P. Numerical investigation of the tone noise mechanism over laminar airfoils[J]. Journal of Fluid Mechanics, 2007, 591:155-182.
[12] ARCONDOULIS E J G, DOOLAN C J, ZANDER A C, et al. A review of trailing edge noise generated by airfoils at low to moderate Reynolds number[J]. Acoustics Australia, 2010, 38(3):129-133.
[13] INASAWA A, NINOMIYA C, ASAI M. Suppression of tonal trailing-edge noise from an airfoil using a plasma actuator[J]. AIAA Journal, 2013, 51(7):1695-1702.
[14] HOWE M S. Noise produced by a sawtooth trailing edge[J]. Journal of the Acoustical Society of America, 1991, 90(1):482-487.
[15] HOWE M S. Aerodynamic noise of a serrated trailing edge[J]. Journal of Fluids and Structures, 1991, 5:33-45.
[16] FINEZ A, JONDEAU E, ROGER M, et al. Broadband noise reduction of a linear cascade with trailing edge serrations[C]//7th AIAA/CEAS Aeroacoustics Conference. Reston:AIAA, 2011.
[17] GRUBER M, JOSEPH P F, CHONG T P. Experimental investigation of airfoil self-noise and turbulent wake reduction by the use of traling edge serrations[C]//16th AIAA/CEAS Aeroacoustics Conference. Reston:AIAA, 2010.
[18] MOREAU D, DOOLAN C J. Noise-reduction mechanism of a flat-plate serrated trailing edge[J]. AIAA Journal, 2013, 51(10):2513-2522.
[19] BROOKS T F, MARCOLINI M A, POPE D S. Airfoil trailing-edge flow measurements[J]. AIAA Journal, 1986, 24(8):1245-1251.

E-mail：hkxb@buaa.edu.cn

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尾缘锯齿结构对叶片边界层不稳定噪声的影响

Blade boundary layer instability noise with trailing edge serrations

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