变截面风扇管道快速声散射计算

王同庆; 张莉爽; 杨兵; 杨明绥

变截面风扇管道快速声散射计算

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
3.
中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015

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- 被引次数: 0
出版历程
- 收稿日期: 2011-04-15
- 修回日期: 2011-05-27
- 刊出日期: 2011-07-28

Aeroacoustic scattering via the fast scattering method

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
3.
Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China,Shenyang 110015,China

摘要

摘要: 针对航空发动机消声短舱声学设计的需要,发展了一种结合快速声散射和直接边界元计算发动机远场声散射的方法,用于计算包含了壁面声阻抗影响的复杂截面管道声散射问题.应用该方法针对某风扇实验台进行了管道消声的数值模拟,得到了远场声散射结果,进行了声衬声阻抗影响的计算,并通过与文献结果的对比表明该方法具有工程应用价值.
- 发动机短舱 /
- 变截面管 /
- 直接边界元方法 /
- 声衬 /
- 快速声散射
Abstract: The fast scattering method was developed in this paper, which could be used for predicting the acoustic propagation problems in the varying cross-section ducts with the acoustic liners. The method can handle the complex section relatively easily by using the direct boundary element method. The noise reduction of a real fan with the duct liners was predicted. The influence of the liner impedance and the sound scattering from the moving body was investigated by comparing the results with those given in the literature. The results illustrate that the present method can be used for the design of the duct liner in the engineering.
- aircraft engine nacelle /
- varying cross-section duct /
- direct boundary element method /
- acoustic liner /
- fast scattering

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参考文献(13)

[1]	Zorumski W E.Acoustic theory of axisymmetric multisec-tion ducts .NASA TR-R-419,1974.
[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(4):504-512.
[5]	Myers M K.Radiation of sound from a point source in a short duct .NASA CP-3352,1997.
[6]	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,1999,227(5):1019-1048.
[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 .AIAA-2005-3068,2005.
[9]	Wang T Q,Yang B.A study on the prediction of the ducted fan noise .AIAA-2005-3069,2005.
[10]	Myers M K.On the acoustic boundary condition in the presence of flow[J].Journal of Sound and Vibration,1980,71(3):429-434.
[11]	Rienstra W,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.
[12]	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)
[13]	Dunn M H,Tweed J,Farassat F.The prediction of ducted fan engine noise via a boundary integral equation method .AIAA Paper 96-1770,1996.