仿生学翼型尾缘锯齿降噪机理

doi:10.7527/S1000-6893.2015.0084

流体力学与飞行力学

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仿生学翼型尾缘锯齿降噪机理

仝帆¹, 乔渭阳¹, 王良锋¹, 纪良¹, 王勋年²

1. 西北工业大学动力与能源学院, 西安 710129;
2. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000

收稿日期:2014-08-26 修回日期:2015-03-25 出版日期:2015-09-15 发布日期:2015-04-09
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:仝帆男, 博士研究生。主要研究方向: 叶轮机械气动声学。 Tel: 029-88482195 E-mail: nwputongfan@163.com
基金资助:
国家自然科学基金 (51276149);空气动力学国家重点实验室研究基金(SKLA20140201)

Noise reduction mechanism of bionic airfoil trailing edge serrations

TONG Fan¹, QIAO Weiyang¹, WANG Liangfeng¹, JI Liang¹, WANG Xunnian²

1. Schoole of Power and Energy, Northwestern Polytechnical University, Xi'an 710129, China;;
2. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2014-08-26 Revised:2015-03-25 Online:2015-09-15 Published:2015-04-09
Supported by:
National Natural Science Foundation of China (51276149); State Key Laboratory of Aerodynamics Research Fund (SKLA20140201)

摘要/Abstract

摘要：

采用大涡模拟与声类比的方法研究了尾缘锯齿对翼型自噪声的影响。以SD2030翼型为研究对象,设计的尾缘锯齿幅值为10%弦长,周期为4%弦长。模拟了来流速度为31 m/s、0° 攻角下直尾缘翼型与锯齿尾缘翼型的流场,对应的基于弦长的雷诺数约为310 000。详细分析了尾缘锯齿对翼型尾缘湍流流场的影响,并通过FW-H方程计算大涡模拟提取的声源项,得到直尾缘翼型与锯齿尾缘翼型的声场。研究发现,锯齿尾缘可以明显降低翼型中低频范围内的噪声,在4 000 Hz以下,窄带噪声最多可降低约16 dB。但尾缘锯齿对翼型气动性能有着不利影响。进一步研究表明,该状态下翼型噪声主要由层流边界层引起的涡脱落噪声主导,尾缘锯齿可以抑制层流边界层引起的涡脱落现象,降低翼型升力脉动与尾缘附近的表面压力脉动,减弱尾缘处的低频湍流脉动与涡量,并有效降低尾缘附近涡的展向相关性,这些因素的综合作用使得翼型自噪声降低。

关键词: 翼型自噪声, 涡脱落噪声, 宽频噪声, 仿生学, 尾缘锯齿

Abstract:

Large eddy simulation and acoustic analogy are performed to investigate the effects of trailing edge serrations on airfoil self-noise. A SD2030 airfoil is used for study. The trailing edge serrations' amplitude is 10% of airfoil chord while the serrations' wavelength is 4% of airfoil chord. The fluid field of SD2030 airfoil at 0° angle of attack with incoming flow velocity of 31 m/s is simulated and the corresponding Reynolds number based on airfoil chord is about 310 000.The effect of trailing edge serrations on the turbulence flow field near the airfoil trailing edge is analyzed in detail. Then FW-H equation is used to calculate the sound field of the straight/serrated trailing edge airfoil with the help of the sound source information obtained by the large eddy simulation. It is found that trailing edge serrations can significantly reduce airfoil noise in low to middle frequency range. The noise reduction can reach up to 16 dB in narrow band in the frequency range smaller than 4 000 Hz. However, the airfoil aerodynamic performance is adversely affected by the trailing edge serration. Further results show that the airfoil noise is dominated by laminar boundary layer-vortex shedding noise under the current condition. It is found that the trailing edge serrations can suppress the laminar boundary layer-vortex shedding phenomenon and reduce the surface pressure fluctuation near the airfoil trailing edge as well as airfoil lift fluctuation. In addition, the turbulent fluctuation at low frequency and the vorticity near the trailing edge are reduced. The vortex spanwise correlation is also decreased near the trailing edge. These factors work jointly and lead to the final airfoil self-noise reduction.

Key words: airfoil self-noise, vortex shedding noise, broadband noise, bionics, trailing edge serrations

中图分类号:

V231

仝帆, 乔渭阳, 王良锋, 纪良, 王勋年. 仿生学翼型尾缘锯齿降噪机理[J]. 航空学报, 2015, 36(9): 2911-2922.

TONG Fan, QIAO Weiyang, WANG Liangfeng, JI Liang, WANG Xunnian. Noise reduction mechanism of bionic airfoil trailing edge serrations[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2911-2922.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

仿生学翼型尾缘锯齿降噪机理

Noise reduction mechanism of bionic airfoil trailing edge serrations

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