有限厚度变截面管道噪声的数值研究

王同庆; 张莉爽; 杨兵

有限厚度变截面管道噪声的数值研究

1.
北京航空航天大学能源与动力工程学院, 北京 100191
2.
中国科学院工程热物理研究所, 北京 100190

计量
- 文章访问数: 2106
- HTML浏览量: 67
- PDF量: 671
- 被引次数: 0
出版历程
- 收稿日期: 2011-06-19
- 修回日期: 2011-10-17
- 刊出日期: 2012-04-28

Numerical simulation of the ducted-fan noise with finite thickness

1.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
Institute of Engineering Thermophysics Chinese Academy of Sciences, Beijing 100190, China

摘要

摘要: 为了研究航空发动机消声短舱声传播的物理机制,采用快速声散射方法计算管道风扇远场散射问题,使用该方法不但可计算变截面管道风扇的噪声,还可计算有限厚度对声散射的影响.通过数值模拟分析了两种不同简化管道形状(等截面圆管、变截面圆管)中管道厚度对散射声场的影响,当管道厚度超过半径的2%时,管道厚度对散射声场的影响不能忽略,研究成果为声学预测中管道厚度的选择提供了参考依据.
- 发动机短舱 /
- 管道厚度 /
- 散射声场 /
- 快速声散射方法 /
- 直接边界元方法
Abstract: To analyze the acoustic propagation of aircraft engine nacelle,predicting the acoustic propagation of a varying cross-section ducted-fan with finite thickness,the fast scattering method was discussed.The ability of the method in application to the sound propagation problems with different pipeline thickness of ducted-fan shapes,including the equal circular tube and variable cross-section tube has been demonstrated.If the pipeline thickness is more than 2 percents of the radius,the pipeline thickness should not be ignored in the prediction of the scattering sound field.The present method provides the theory basis for choosing the ducted-fan thickness in the engineering.
- aircraft engine nacelle /
- pipeline thickness /
- scattering field /
- fast scattering method /
- direct boundary element method

HTML

参考文献(12)

[1]	Tyler J M,Sofrin T G.Axial flow compressor noise studies[J].Society of Automotive Engineers,1962,70:309-332.
[2]	Alfredson R J.The propagation of sound in a circular duct of continuously varying cross-sectional area[J].Journal of Sound and Vibration,1972,23(4):433-442.
[3]	Ozyoruk Y,Long L N,Jones M G.Time-domain numerical simulation of a flow-impedance tube[J].Journal of Computational Physics,1998,146(1):29-57.
[4]	Mankbadi R R.Review of computational aero acoustics in propulsion systems[J].AIAA Journal of Propulsion and Power,1999,15(40):504-512.
[5]	Myers M K.Radiation of sound from a point source in a short duct.NASA CP-3352,1997.
[6]	Myers M K.Boundary integral formulations for ducted fan radiation calculations.CEAS/AIAA Paper 1995-076,1995.
[7]	Dunn M H,Tinetti A F.Aeroacoustic scattering via the equivalent source method.AIAA-2004-2937,2004.
[8]	Yang B,Wang T Q.An approach to predict ducted fan noise by boundary integral equation method[R].AIAA-2005-3068,2005.
[9]	王晓宇,杜林,孙晓峰.考虑变截面影响的航空发动机短舱声学模型及数值结果[J].航空学报,2006,27(6):1073-1079. WANG Xiaoyu,DU Lin,SUN Xiaofeng.A new approach for the acoustic design of aeroengine nacelle with the effect of varying cross-section aera[J].Acta Aeronautica et Astronautica Sinica,2006,27(6):1073-1079.(in Chinese)
[10]	王同庆,张莉爽,杨兵,等.变截面风扇管道快速声散射计算[J].航空动力学报,2011,26(7):1569-1574. WANG Tongqing,ZHANG Lishuang,YANG Bing,et al.Aeroacoustic scattering via the fast scattering method[J].Journal of Aerospace Power,2011,26(7):1569-1574.(in Chinese)
[11]	Dunn M H,Tweed J,Farassat F.The application of a boundary integral equation method to the prediction of ducted fan engine noise[J].Journal of Sound and Vibration,1999,277(5):1019-1048.
[12]	Rienstra W S,Eversman W.A numerical comparison between the multiple-scales and finite-element solution for sound propagation in lined flow ducts[J].Journal of Fluid Mechanics,2001,437:367-384.