波浪前缘静子叶片对高速轴流风扇单音噪声的影响

doi:10.7527/S1000-6893.2019.23565

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

波浪前缘静子叶片对高速轴流风扇单音噪声的影响

同航, 黎霖, 卯鲁秦, 向康深, 乔渭阳

西北工业大学动力与能源学院, 西安 710129

收稿日期:2019-10-10 修回日期:2019-11-22 发布日期:2019-11-20
通讯作者: 同航 E-mail:tonghang@mail.nwpu.edu.cn
基金资助:
国家自然科学基金（51776174）；国家科技重大专项（2017-Ⅱ-0008-0022）

Tonal noise reduction of a high-speed single axial fan with wavy leading-edge stator

TONG Hang, LI Lin, MAO Luqin, XIANG Kangshen, QIAO Weiyang

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

Received:2019-10-10 Revised:2019-11-22 Published:2019-11-20
Supported by:
National Natural Science Foundation of China (51776174);National Science and Technology Major Project (2017-Ⅱ-0008-0022)

摘要/Abstract

摘要： 航空发动机压气机噪声与大型风洞压缩机噪声问题日益凸显，相关研究机构迫切需求新的降噪手段以指导大型叶轮机械降噪设计。为了探索波浪前缘静子叶片在大型叶轮机械降噪中的应用前景，采用非定常雷诺平均Navier-Stoke（URANS）方程与FW-H方程混合方法对基准静子叶片和3种波浪前缘静子叶片的降噪效果进行了数值模拟，研究对象静子来流平均马赫数约为0.49，基于静子叶片弦长的雷诺数约为1 040 000。数值预测结果显示：波浪前缘静子叶片可以显著降低高速轴流风扇单音噪声，但会对风扇的气动性能产生少许不利影响；相较于基准静子叶片，3种波浪前缘静子叶片可以在1BPF时降低风扇入口声功率级0.97~1.5 dB，2BPF时降低风扇入口声功率级2.89~4.9 dB，3BPF时降低风扇入口声功率级3.32~4.72 dB；同时，总压比降低0.1%~0.8%，等熵效率降低0.1%~0.3%。进一步研究表明：不同频率下声源振幅和相位关系是风扇单音噪声强度的主要影响因素，总的来说，幅值的增加会降低声源强度，然而通过改变声源相位关系的降噪方式则需要兼顾径向模态与波长两个方面。

关键词: 波浪前缘叶片, 单音噪声, 声类比理论, 风扇, FW-H方程, 混合模型, 降噪

Abstract: It is an urgent need for related research institutes to find new methods to guide large impeller mechanical noise reduction design when the noise problem of aero-engine and large wind tunnel compressor is becoming more and more prominent. To explore the application prospect of the wavy leading-edge stator for noise reduction of large turbomachinery, the noise reduction effect of the base stator and three kinds of wavy leading-edge stator are numerically simulated by the hybrid method of Unsteady Reynolds-Averaged Navier-Stokes (URANS) equation and FW-H equation. The inflow averaged Mach number at leading-edge of stator is about 0.49, and the corresponding stator blade chord based Reynolds number is about 1 040 000. Numerical prediction results show that the wavy leading-edge stator can substantially reduce the fan tonal noise but have certain adverse effects on the fan aerodynamic performance. Compared with base blade, the fan inlet sound power level could be reduced by about 0.97-1.5 dB at 1BPF, 2.89-4.9 dB at 2BPF, and 3.32-4.72 dB at 3BPF by using those wavy leading-edge stators, while the total pressure ratio reduced by about 0.1%~0.8%, and the isentropic efficiency reduced by about 0.1%~0.3%. Further study shows that the amplitude and phase relationship of sound source at different frequencies are the main influencing factors for fan tonal noise. In general, the sound source intensity will reduce with the increase of amplitude. However, the noise reduction method by changing the phase relationship of the sound source needs to balance both the radial mode and the wavelength.

Key words: wavy leading-edge blade, tonal noise, acoustic analogy theory, fan, FW-H equations, hybrid method, noise reduction

中图分类号:

V211.3

同航, 黎霖, 卯鲁秦, 向康深, 乔渭阳. 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): 123565-123565.

TONG Hang, LI Lin, MAO Luqin, XIANG Kangshen, QIAO Weiyang. Tonal noise reduction of a high-speed single axial fan with wavy leading-edge stator[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(10): 123565-123565.

参考文献

[1] ENVIA E. Fan noise reduction:An overview[J].International Journal of Aeroacoustics, 2001, 1(1):43-64.
[2] NESBITT E. Towards a quieter low pressure turbine:design characteristics and prediction needs[J].International Journal of Aeroacoustics, 2010, 10(1):1-15.
[3] BATARD H. Aircraft noise reduction:AIRBUS industrial needs in terms of new materials for nacelle liners[R]. Toulouse:AIRBUS, 2003.
[4] MALDONADO A L P, MISERDA R F B, PIMENTA B G. Computational tonal noise prediction for the advanced noise control fan:AIAA-2012-2128[R]. Reston:AIAA, 2012.
[5] BRōS G A, PÉROT F, FREED D. Properties of the Lattice-Boltzmann method for acoustics:AIAA-2009-3395[R]. Reston:AIAA, 2009.
[6] MORIN B L. Broadband fan noise prediction system for gas turbine engines:AIAA-1999-1889[R]. Reston:AIAA, 1999.
[7] SODERMAN P T. Aerodynamic effects of leading-edge serrations on a two-dimensional airfoil:NASA-TM-X-2643[R]. Washington, D.C.:NASA, 1972.
[8] SODERMAN P T. Leading edge serrations which reduce the noise of low-speed rotors:NASA-TN-D-7371[R]. Washington, D.C.:NASA, 1973.
[9] HERSH A S, SODERMAN P T, HAYDEN R E. Investigation of acoustic effects of leading-edge serrations on airfoils[J].Journal of Aircraft, 1974, 11(4):197-202.
[10] FISH F E, BATTLE J M. Hydrodynamic design of the humpback whale flipper[J].Journal of Morphology, 1995, 225(1):51-60.
[11] JOHARI H, HENOCH C, CUSTODIO D, et al. Effects of leading-edge protuberances on airfoil performance[J].AIAA Journal, 2007, 45(11):2634-2642.
[12] CUSTODIO D. The effect of humpback whale-like leading edge protuberances on hydrofoil performance[D]. Worcester:Worcester Polytechnic Institute, 2007.
[13] YOON H S, HUNG P A, JUNG J H, et al. Effect of the wavy leading edge on hydrodynamic characteristics for flow around low aspect ratio wing[J].Computers & Fluids, 2011, 49(1):276-289.
[14] SKILLEN A, REVELL A, PINELLI A, et al. Flow over a wing with leading-edge undulations[J].AIAA Journal, 2015, 53(2):464-472.
[15] CORSINI A, DELIBRA G, SHEARD A G. On the role of leading-edge bumps in the control of stall onset in axial fan blades[J].Journal of Fluids Engineering, 2013, 135(8):1-9.
[16] CORSINI A, DELIBRA G, SHEARD A G. The application of sinusoidal blade-leading edges in a fan-design methodology to improve stall resistance[J].Proceedings of the Institution of Mechanical Engineers Part A Journal of Power & Energy, 2013, 228(3):255-271.
[17] CLAIR V, POLACSEK C, Garrec T L, et al. Experimental and numerical investigation of turbulence-airfoil noise reduction using wavy edges[J].AIAA Journal, 2013, 51(11):2695-2713.
[18] LAU A S H, HAERI S, KIM J W. The effect of wavy leading edges on aerofoil-gust interaction noise[J].Journal of Sound and Vibration, 2013, 332(24):6234-6253.
[19] CHONG T P, VATHYLAKIS A, MCEWEN A, et al. Aeroacoustic and aerodynamic performances of an aerofoil subjected to sinusoidal leading edges:AIAA-2015-2200[R]. Reston:AIAA, 2015.
[20] 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.
[21] CHEN W J, WANG X N, QIAO W Y, et al. Rod-airfoil interaction noise reduction using leading edge serrations:AIAA-2015-3264[R]. Reston:AIAA, 2015.
[22] REBOUL G, CADER A, POLACSEK C, et al. CAA prediction of rotor-stator interaction using synthetic turbulence:application to a low-noise serrated OGV:AIAA-2017-3714[R]. Reston:AIAA, 2017.
[23] 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.
[24] 蒋永松, 郑文涛, 赵航, 等. 风扇出口导向叶片低噪声设计Ⅰ:方法与优化[J].航空学报, 2019, 40(10):122955. JIANG Y S, ZHENG W T, ZHAO H, et al. Low noise design of fan outlet guide vane, part Ⅰ:Method and optimization[J].Acta Aeronautica et Astronautica Sinica, 2019, 40(10):122955(in Chinese).
[25] 郑文涛, 蒋永松, 赵航, 等. 风扇出口导向叶片低噪声设计Ⅱ:数值验证[J].航空学报, 2019, 40(10):122956. ZHENG W T, JIANG Y S, ZHAO H, et al. Low noise design of fan outlet guide vane, part Ⅱ:Numerical verifications[J].Acta Aeronautica et Astronautica Sinica, 2019, 40(10):122956(in Chinese).
[26] GOLDSTEIN M E. Aeroacoustics[M]. New York:McGraw-Hill, 1976.
[27] TSUCHIYA N, NAKAMURA Y, YAMAGATA A, et al. Fan noise prediction using unsteady CFD analysis:AIAA-2002-2491[R]. Reston:AIAA, 2002.
[28] 郭鑫. 叶轮机仿生学降噪的气动与声学机理研究[D]. 西安:西北工业大学,2019:69-71. GUO X. Research on the aerodynamic and acoustic mechanism of bionic noise reduction method in turbomachinery[D]. Xi'an:Northwestern Polytechnical University, 2019:69-71(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

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

波浪前缘静子叶片对高速轴流风扇单音噪声的影响

Tonal noise reduction of a high-speed single axial fan with wavy leading-edge stator

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	尧少波, 蒋励剑, 赵文文, 卢铮, 吴昌聚, 陈伟芳. 耦合聚类的数据驱动稀薄流非线性本构计算方法[J]. 航空学报, 2022, 43(S2): 40-53.
[2]	张星雨, 高正红, 雷涛, 闵志豪, 李伟林, 张晓斌. 分布式电推进飞机气动-推进耦合特性地面试验[J]. 航空学报, 2022, 43(8): 125389-125389.
[3]	郑覃, 杨小贺, 叶俊, 冯锦璋. 内涵工况对风扇增压级双涵匹配的影响[J]. 航空学报, 2022, 43(7): 125477-125477.
[4]	查建平, 王风娇, 郭俊贤, 李明强. 直升机主减速器噪声源控制技术概述[J]. 航空学报, 2022, 43(6): 526123-526123.
[5]	霍施宇, 杨嘉丰, 邓云华, 燕群. 全尺寸短舱排气道声衬声学设计与试验验证[J]. 航空学报, 2022, 43(6): 526736-526736.
[6]	李航行, 胡迪科, 吴邵庆. 复合材料整流罩减振降噪的动力吸振器设计[J]. 航空学报, 2022, 43(5): 225249-225249.
[7]	桂幸民, 金东海, 张健成, 宋满祥, 赵洋, 胡大权. 计及叶片前缘周向不均匀源项的弯掠叶片流动机理[J]. 航空学报, 2022, 43(10): 527371-527371.
[8]	史磊, 杨光, 丁光华, 林文俊. 风扇转子叶片前缘精细维修方案及流动特性分析[J]. 航空学报, 2020, 41(9): 423446-423446.
[9]	陈浩, 袁先旭, 毕林, 华如豪, 司芳芳, 唐志共. 基于RANS/LES混合方法的分离流动模拟[J]. 航空学报, 2020, 41(8): 123642-123642.
[10]	王小东, 秦一凡, 季宏丽, 陆洋, 裘进浩. 基于声学黑洞效应的直升机驾驶舱宽带降噪[J]. 航空学报, 2020, 41(10): 223831-223831.
[11]	蒙超恒, 裴海龙, 程子欢. 涵道风扇式无人机的优先级控制分配[J]. 航空学报, 2020, 41(10): 324017-324017.
[12]	史朝印, 吕震宙, 李璐祎, 王燕萍. 基于自适应Kriging代理模型的交叉熵重要抽样法[J]. 航空学报, 2020, 41(1): 223123-223123.
[13]	王刚, 张彬乾, 张明辉, 桑为民, 袁昌盛, 李栋. 翼身融合民机总体气动技术研究进展与展望[J]. 航空学报, 2019, 40(9): 623046-623046.
[14]	李保珠, 董云龙, 丁昊, 关键. 基于高斯混合模型的航迹抗差关联算法[J]. 航空学报, 2019, 40(6): 322650-322650.
[15]	史磊, 杨光, 林文俊. 前缘侵蚀对风扇转子叶片气动特性的影响机理[J]. 航空学报, 2019, 40(10): 123007-123007.