开口风洞声阵列测量的剪切层修正方法
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摘要
开口风洞中的相位传声器阵列测量,必须进行剪切层修正才能得到真实的噪声源位置信息。在0.55m×0.40m声学风洞中开展了剪切层修正的实验研究,得到了不同风速条件下的剪切层速度剖面、声波传播延迟时间和声源定位的结果。根据实验结果,对剪切层速度剖面的Gortler理论解进行了验证,并对比分析了4种剪切层修正方法。研究结果表明:选择自相似参数σ=9,ξ0=0.2时剪切层速度剖面测量值与理论值符合较好;剪切层厚度与轴向距离的关系为y=0.15x;马赫数Ma≤0.3、测量角θm在40°～140°范围内,不同剪切层修正方法对声波延迟时间计算结果的相对误差在1%以内。提出了射线追踪快速计算方法,该方法较常规射线追踪法的计算速度可提高2个数量级,从而使其适用于声阵列在线测量。
To identify the true location of the noise sources,the shear layer effect must be taking into account when conducting the microphone array test in open-jet wind tunnels.An experimental study for the shear layer correction was performed in the 0.55 m×0.40 maero-acoustic tunnel of China Aerodynamics Research and Development Center(CARDC).The shear layer velocity profiles,source-receiver delay times and source identification results were obtained.The Gortler's velocity-profile solution was validated and four different shear layer correction methods were compared and analyzed on the basis of the experimental results.The research results show that:the velocity-profile experimental data agrees well with calculations when the self-similar parametersσ=9,ξ0=0.2 are chosen,and the relationship between the fitted shear layer thickness and the axial distance data can be presented by the equation y=0.15 x;Ma≤0.3 and the measurement angleθm within 40°～140°,the relative calculation error of the delay time of different shear layer correction methods is smaller than 1%;the accuracy of the other three methods are quite close to the Amiet 2 Dmethod.A fast ray tracing method that is 100 times faster than the conventional ray tracing method is proposed,which makes the ray tracing method applicable for on-line microphone array data processing.
To identify the true location of the noise sources,the shear layer effect must be taking into account when conducting the microphone array test in open-jet wind tunnels.An experimental study for the shear layer correction was performed in the 0.55 m×0.40 maero-acoustic tunnel of China Aerodynamics Research and Development Center(CARDC).The shear layer velocity profiles,source-receiver delay times and source identification results were obtained.The Gortler's velocity-profile solution was validated and four different shear layer correction methods were compared and analyzed on the basis of the experimental results.The research results show that:the velocity-profile experimental data agrees well with calculations when the self-similar parametersσ=9,ξ0=0.2 are chosen,and the relationship between the fitted shear layer thickness and the axial distance data can be presented by the equation y=0.15 x;Ma≤0.3 and the measurement angleθm within 40°～140°,the relative calculation error of the delay time of different shear layer correction methods is smaller than 1%;the accuracy of the other three methods are quite close to the Amiet 2 Dmethod.A fast ray tracing method that is 100 times faster than the conventional ray tracing method is proposed,which makes the ray tracing method applicable for on-line microphone array data processing.
引文
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[12]Candel M,Julienne A,Guedel A.Refraction and scattering of sound in an open wind tunnel flow[C]//Proc of the 6th international congress on instrumentation in aerospace simulation facilities.Ottawa:Institute of Electrical and Electronics Engineers,Inc.,1975.
[13]Oerlemans S.Detection of aeroacoustic sound sources on aircraft and wind turbines[D].Enschede:University of Twente,2009.
[14]张军,陈鹏,张俊龙,等.基于简化射线模型的剪切层相位修正方法[J].航空动力学报,2018,33(10):2459-2465Zhang J,Chen P,Zhang J L,et al.Shear layer phase shift correction method based on a simplified ray model[J].Journal of Aerospace Power,2018,33(10):2459-2465.
[15]张俊龙,李征初,卢翔宇.开口风洞剪切层对传声器及其阵列测量影响试验研究[J].实验流体力学,2018,32(1):71-77.Zhang J L,Li Z C,Lu X Y.Experimental research on the influence of open jet shear layer on microphone and microphone array measurement[J].Journal of Experiments in Fluid Mechanics,2018,32(1):71-77.
[16]Humphreys W M,Hunter W W,Meadows K R.Design and use of microphone directional arrays for aeroacoustic measurement[R].AIAA-98-0471,1998.
[17]Sijtsma P,Oerlemans S,Tibble T G,et al.Spectral broadening by shear layers of open jet wind tunnels[R].AIAA-2014-3178,2014.
[2]陈正武,王勋年,李征初,等.基于声学风洞的麦克风阵列测试技术应用研究[J].实验流体力学,2012,26(3):84-90.Chen Z W,Wang X N,Li Z C,et al.Application investigation of microphone array measuring and testing technique in anechoic wind tunnel[J].Journal of Experiments in Fluid Mechanics,2012,26(3):84-90.
[3] Miles J W.On the reflection of sound at an interface of relative motion[J].Journal of the Acoustical Society of America,1957,29(2):226-228.
[4] Ribner H S.Reflection,transmission,and amplification of sound by a moving medium[J].Journal of the Acoustical Society of America,1957,29(4):435-441.
[5] Schlinker R H,Amiet R K.Refraction and scattering of sound by a shear layer[R].NASA-CR-3371,1980.
[6] Amiet R K.Correction of open jet wind tunnel measurements for shear layer refraction[C]//Proc of AIAA 2nd Aero-acoustics Conference.1975.
[7] Amiet R K.Refraction of sound by a shear layer[J].Journal of Sound and Vibration,1978,58(4):467-482.
[8] Candel S M,Guedel A,Julienne A.Radiation,refraction,and scattering of acoustic waves in a free shear layer flow[R].AIAA-1976-544,1976.
[9] Ahuja K K,Tanna,H K,TesterB J.An experimental study of transmission,reflection and scattering of sound in a free jet flight simulation facility and comparison with theory[J].Journal of Sound and Vibration,1981,75(1):51-85.
[10] Wang Y G,Yang J S,Jia Q,et al.An improved correction method for sound source drift in a jet flow and its application to a wind tunnel measurement[J].Acta Acustica united with Acustica,2015,101(3):642-649.
[11]Zana S.Effect of open jet shear layers on aeroacoustic wind tunnel measurements[D].Mekelweg:Delft University,2011.
[12]Candel M,Julienne A,Guedel A.Refraction and scattering of sound in an open wind tunnel flow[C]//Proc of the 6th international congress on instrumentation in aerospace simulation facilities.Ottawa:Institute of Electrical and Electronics Engineers,Inc.,1975.
[13]Oerlemans S.Detection of aeroacoustic sound sources on aircraft and wind turbines[D].Enschede:University of Twente,2009.
[14]张军,陈鹏,张俊龙,等.基于简化射线模型的剪切层相位修正方法[J].航空动力学报,2018,33(10):2459-2465Zhang J,Chen P,Zhang J L,et al.Shear layer phase shift correction method based on a simplified ray model[J].Journal of Aerospace Power,2018,33(10):2459-2465.
[15]张俊龙,李征初,卢翔宇.开口风洞剪切层对传声器及其阵列测量影响试验研究[J].实验流体力学,2018,32(1):71-77.Zhang J L,Li Z C,Lu X Y.Experimental research on the influence of open jet shear layer on microphone and microphone array measurement[J].Journal of Experiments in Fluid Mechanics,2018,32(1):71-77.
[16]Humphreys W M,Hunter W W,Meadows K R.Design and use of microphone directional arrays for aeroacoustic measurement[R].AIAA-98-0471,1998.
[17]Sijtsma P,Oerlemans S,Tibble T G,et al.Spectral broadening by shear layers of open jet wind tunnels[R].AIAA-2014-3178,2014.