波浪结构对圆柱-翼型湍流干涉噪声的影响研究

王大庆; 冯和英; 彭叶辉; 仝帆

doi:10.13433/j.cnki.1003-8728.20200584

波浪结构对圆柱-翼型湍流干涉噪声的影响研究

doi: 10.13433/j.cnki.1003-8728.20200584

1.
湖南科技大学机械设备健康维护湖南省重点实验室，湖南湘潭　411201
2.
湖南科技大学数学与计算科学学院，湖南湘潭　411201
3.
中国空气动力研究与发展中心气动噪声控制重点实验室，四川绵阳　621000

基金项目: 国家自然科学基金项目（51875194）、湖南省自然科学基金项目（2020JJ4306）及湖南省教育厅优秀青年基金项目（20B226）

详细信息

作者简介:
王大庆（1996−），硕士研究生，研究方向为叶轮机械气动噪声控制，1970529345@qq.com

通讯作者:
冯和英，副教授，博士生导师，博士，fengheying@hnust.edu.cn

中图分类号: V211.3
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- 被引次数: 0
出版历程
- 收稿日期: 2021-03-05
- 刊出日期: 2023-02-25

Research on Influence of Wave Structure on Turbulence Interference Noise of Cylinder-airfoil

1.
Hunan Key Laboratory of Mechanical Equipment Health Maintenance, Hunan University of Science and Technology, Xiangtan 411201, Hu'nan, China
2.
School of Mathematics and Computational Science, Hunan University of Science and Technology, Xiangtan 411201, Hu'nan, China
3.
Key Laboratory of Aerodynamic Noise Control, China Aerodynamics Research and Development Center, Mianyang 621000, Sichuan, China

摘要

摘要: 为探究波浪翼型的降噪效果，采用大涡模拟（LES）和边界元法（BEM）相结合的混合方法对3种不同波浪翼型进行模拟，并通过试验验证了仿真模型的可行性，进一步分析了3种不同波浪翼型（表面波浪Wavy airfoil-A、前缘波浪Wavy airfoil-B和前缘+表面波浪Wavy airfoil-C）对圆柱-翼型湍流干涉噪声的影响。研究结果表明：3种模型都能在一定程度上降低翼型湍流干涉噪声，其中Wavy airfoil-C模型降噪效果最好，降噪频率范围最广，其垂直流向方向总声压级降噪量可达6.7 dB；Wavy airfoil-C模型不仅能有效地降低翼型表面压力脉动、各截面上的湍流强度、升阻力系数波动、功率谱密度，还能利用其前缘波浪结构有效地减少前缘主声源区域的面积，且能利用其表面波浪结构的导流作用降低翼型后缘的声源振动幅值。
- 波浪结构 /
- 圆柱-翼型 /
- 边界元法 /
- 湍流干涉噪声
Abstract: In order to explore the noise reduction effect of wavy airfoil, the hybrid method of large eddy simulation (LES) and boundary element method (BEM) was used to study three different wavy airfoils. The feasibility of the simulation model was verified by experiment. Furthermore, the influence of three different wavy airfoils( wavy surface airfoil-A, wavy leading edge airfoil-B and wavy leading edge + wavy surfaceairfoil-C) on the cylinder-airfoil interaction noise is analyzed. The research results show that all the three models can reduce the turbulence-airfoil interference noise to a certain extent, and the Wavy airfoil-C model has the best noise reduction effect, the noise reduction frequency range is the widest, and the total sound pressure level noise reduction amount in the vertical flow direction up to 6.7 dB; Wavy airfoil-C model can effectively reduce airfoil surface pressure pulsation, turbulence intensity on each section, fluctuation of lift and drag coefficient, power spectral density, but also use its wavy leading edge structure to effectively reduce the leading edge The area of the main sound source area, and can use the diversion effect of the wavy surface structure to reduce the sound pressure amplitude of the trailing edge of the airfoil.
- wave structure /
- cylindric-airfoil /
- boundary element method /
- turbulent interference noise

HTML全文

图 1 远场声辐射示意图

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图 2 物理模型及其展向形状示意图

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图 3 流体域参数设置示意图

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图 4 圆柱-翼型周围计算域网格

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图 5 网格无关性验证

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图 6 B平面上的速度分布（x/c = −0.25）

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图 7 瞬时的涡量云图及Q-准则等值面

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图 8 翼型升阻力系数时间历程

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图 9 翼型升力系数和阻力系数功率谱密度随频谱的变化

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图 10 叶片吸力面压力脉动均方根值$P_{\rm{RMSE}}^{\prime}$云图分布

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图 11 流向方向上不同截面位置处的流向湍流强度（Turbulent Intensity_x，$\sqrt {{u^{\prime 2}}} /{U_0}$）分布

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图 12 远场监测点及指向性设置示意图

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图 13 N点处的声压级仿真结果与实验结果

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图 14 远场辐射噪声声压级云图分布

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图 15 检测点N声压级频谱分布

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图 16 总声压级指向性分布

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表 1 N点总声压级

模型 0° 90°

Straiight 76.400 101.700
Wavy airfoil-A 75.130 99.500
Wavy airfoil-B 74.510 95.870
Wavy airfoil-C 74.005 95.200

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参考文献(20)

[1]	WILLIAMSON C H K. Vortex dynamics in the cylinder wake[J]. Annual Review of Fluid Mechanics, 1996, 28: 477-539 doi: 10.1146/annurev.fl.28.010196.002401
[2]	JACOB M C, BOUDET J, CASALINO D, et al. A rod-airfoil experiment as a benchmark for broadband noise modeling[J]. Theoretical and Computational Fluid Dynamics, 2005, 19(3): 171-196 doi: 10.1007/s00162-004-0108-6
[3]	CASALINO D, JACOB M, ROGER M. Prediction of rod-airfoil interaction noise using the Ffowcs-Williams-Hawkings analogy[J]. AIAA Journal, 2003, 41(2): 182-191 doi: 10.2514/2.1959
[4]	ZHU W Q, XIAO Z X, FU S. Numerical modeling screen for flow and noise control around tandem cylinders[J]. AIAA Journal, 2020, 58(6): 2504-2516 doi: 10.2514/1.J058636
[5]	DA SILVA G P G, EGUEA J P, CROCE J A G, et al. Slat aerodynamic noise reduction using dielectric barrier discharge plasma actuators[J]. Aerospace Science and Technology, 2020, 97: 105642 doi: 10.1016/j.ast.2019.105642
[6]	FOSHAT S. Numerical investigation of the effects of plasma actuator on separated laminar flows past an incident plate under ground effect[J]. Aerospace Science and Technology, 2020, 98: 105646 doi: 10.1016/j.ast.2019.105646
[7]	GEYER T F, SARRADJ E. Circular cylinders with soft porous cover for flow noise reduction[J]. Experiments in Fluids, 2016, 57(3): 30 doi: 10.1007/s00348-016-2119-7
[8]	陈伟杰, 乔渭阳, 王良锋, 等. 基于LES与FW-H方程的圆柱-翼型干涉噪声数值研究[J]. 航空动力学报, 2016, 31(9): 2146-2155 doi: 10.13224/j.cnki.jasp.2016.09.013 CHEN W J, QIAO W Y, WANG L F, et al. Investigation of rod-airfoil interaction noise using large eddy simulation and FW-H equation[J]. Journal of Aerospace Power, 2016, 31(9): 2146-2155 (in Chinese) doi: 10.13224/j.cnki.jasp.2016.09.013
[9]	陈伟杰, 乔渭阳, 仝帆, 等. 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 CHEN W J, QIAO W Y, TONG F, et al. Effect of leading-edge serrations on boundary layer instability noise[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(12): 3634-3645 (in Chinese)
[10]	WANG J, ZHANG C C, WU Z Y, et al. Numerical study on reduction of aerodynamic noise around an airfoil with biomimetic structures[J]. Journal of Sound and Vibration, 2017, 394: 46-58 doi: 10.1016/j.jsv.2016.11.021
[11]	CLAIR V, POLACSEK C, LE GARREC T, et al. Experimental and numerical investigation of turbulence-airfoil noise reduction using wavy edges[J]. AIAA Journal, 2013, 51(11): 2695-2713 doi: 10.2514/1.J052394
[12]	LIN Y F, LAM K, ZOU L, et al. Numerical study of flows past airfoils with wavy surfaces[J]. Journal of Fluids and Structures, 2013, 36: 136-148 doi: 10.1016/j.jfluidstructs.2012.09.008
[13]	TONG F, QIAO W Y, CHEN W J, et al. Numerical analysis of broadband noise reduction with wavy leading edge[J]. Chinese Journal of Aeronautics, 2018, 31(7): 1489-1505 doi: 10.1016/j.cja.2018.03.020
[14]	TONG F, QIAO W Y, XU K B, et al. On the study of wavy leading-edge vanes to achieve low fan interaction noise[J]. Journal of Sound and Vibration, 2018, 419: 200-226 doi: 10.1016/j.jsv.2018.01.017
[15]	同航, 黎霖, 卯鲁秦, 等. 波浪前缘静子叶片对高速轴流风扇单音噪声的影响[J]. 航空学报, 2020, 41(10): 92-105 TONG H, LI L, MAO L Q, et al. Tonal noise reduction of a high-speed single axial fan with wavy leading-edge stator[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(10): 92-105 (in Chinese)
[16]	同航, 丁松, 向康深, 等. 分布式波浪前缘静子叶片对单级轴流风扇单音噪声影响的数值研究[J]. 推进技术, 2021, 42(10): 2237-2248 doi: 10.13675/j.cnki.tjjs.190899 TONG H, DING S, XIANG K S, et al. Numerical study on tonal noise reduction of single axial fan with distributed wavy leading-edge stator[J]. Journal of Propulsion Technology, 2021, 42(10): 2237-2248 (in Chinese) doi: 10.13675/j.cnki.tjjs.190899
[17]	HAO T. LMS Virtual. Lab Fluid acoustics solutions[R]. LMS International, 2010
[18]	杨燕丽, 杨爱玲, 董锐, 等. 安装角对压气机叶栅气动噪声特性的影响[J]. 航空学报, 2012, 33(4): 588-596 YANG Y L, YANG A L, DONG R, et al. Influence of stagger angle on aerodynamic sound performance of compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(4): 588-596 (in Chinese)
[19]	SMAGORINSKY J. General circulation experiments with the primitive equations I The basic experiment[J]. Monthly Weather Review, 1963, 91(3): 99-164 doi: 10.1175/1520-0493(1963)091<0099:GCEWTP>2.3.CO;2
[20]	杨德全, 赵忠生. 边界元理论及应用[M]. 北京: 北京理工大学出版社, 2002: 250-254 YANG D Q, ZHAO Z S. The theory and application of boundary element method[M]. Beijing: Beijing Institute of Technology Press, 2002: 250-254 (in Chinese)