带制退器的膛口射流噪声数值模拟与实验研究
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摘要
为了研究膛口装置对膛口噪声气动特性的影响,对带膛口制退器的某小口径武器的膛口射流噪声进行了数值模拟和实验研究。采用计算流体力学CFD (computational fluid dynamics)-计算气动声学CAA(computational aeroacoustics)耦合算法对膛口噪声进行数值模拟,即对膛口流场进行瞬态CFD模拟,获取流场数据,然后利用所得到的结果采用声学方程模拟声源信息求解声场。基于数值模拟结果,分析了膛口流场变化及噪声的指向性分布,并与实验结果进行了对比。研究表明:膛口制退器的安装改变了膛口流场结构,影响了膛口射流噪声的指向性分布。计算结果与实验结果的误差小于9%,验证了该计算方法的可行性。研究结果可为膛口射流噪声的预测及膛口制退器的设计提供一定的参考。
In order to investigate the influence of the muzzle device on the characteristics of muzzle aeroacoustic noise, simulation analysis and experimental research were performed on the jet noise induced by the complex flows discharging from a small caliber rifle with a muzzle brake. A CFD(computational fluid dynamics)-CAA(computational aeroacoustics) hybrid method was applied. The muzzle flow field was calculated by using large eddy simulation and the jet noise was determined by the FW-H(Ffowcs WilliamsHawkings) equation based on the obtained source data. Based on the numerical results, the jet noise directivity was analyzed and the comparison to the experimental results was conducted. Results indicate that the muzzle flow field was changed by the muzzle brake and the directional distribution of the jet noise was also affected. The errors between the calculated and experiment results are less than 9%, therefore the numerical method applied in the paper is feasible. The research result can provide a reference for the prediction of muzzle noise and the design of muzzle brakes.
In order to investigate the influence of the muzzle device on the characteristics of muzzle aeroacoustic noise, simulation analysis and experimental research were performed on the jet noise induced by the complex flows discharging from a small caliber rifle with a muzzle brake. A CFD(computational fluid dynamics)-CAA(computational aeroacoustics) hybrid method was applied. The muzzle flow field was calculated by using large eddy simulation and the jet noise was determined by the FW-H(Ffowcs WilliamsHawkings) equation based on the obtained source data. Based on the numerical results, the jet noise directivity was analyzed and the comparison to the experimental results was conducted. Results indicate that the muzzle flow field was changed by the muzzle brake and the directional distribution of the jet noise was also affected. The errors between the calculated and experiment results are less than 9%, therefore the numerical method applied in the paper is feasible. The research result can provide a reference for the prediction of muzzle noise and the design of muzzle brakes.
引文
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[2]BOGEY C,MARSDEN O,BAILLY C.Influence of initial turbulence level on the flow and sound fields of a subsonic jet at a diameter-based Reynolds number of 105[J].Journal of Fluid Mechanics,2012,701(6):352-385.DOI:10.1017/jfm.2012.162.
[3]WAN Zhenhua,ZHOU Lin,YANG Haihua,et al.Large eddy simulation of flow development and noise generation of free and swirling jets[J].Physics of Fluids,2013,25(12):564-587.DOI:10.1063/1.4833215.
[4]WAN Zhenhua,ZHOU Lin,SUN Dejun.A study on large coherent structures and noise emission in a turbulent round jet[J].Science China:Physics,Mechanics and Astronomy,2014,57(8):1552-1562.DOI:10.1007/s11433-013-5291-2.
[5]BRèS G A,JAUNET V,RALLIC M L,et al.Large eddy simulation for jet noise:the importance of getting the boundary layer right[C]//Proceedings of 21st AIAA/CEAS Aeroacoustics Conference.American Institute of Aeronautics and Astronautics Inc,2015.DOI:10.2514/6.2015-2535.
[6]LORTEAU M,CLéRO F,VUILLOT F.Analysis of noise radiation mechanisms in hot subsonic jet from a validated large eddy simulation solution[J].Physics of Fluids,2015,27(7).DOI:10.1063/1.4926792.
[7]BIN J,KIM M,LEE S.A numerical study on the generation of impulsive noise by complex flows discharging from a muzzle[J].International Journal for Numerical Methods in Engineering,2010,75(8):964-991.
[8]LEE I C,LEE D J,KO S H,et al.Numerical analysis of a blast wave using CFD-CAA hybrid method[C]//Proceedings of12th AIAA/CEAS Aeroacoustics Conference.American Institute of Aeronautics and Astronautics,Inc.,2006.DOI:10.2514/6.2006-2701.
[9]REHMAN H,HWANG S H,FAJAR B,et al.Analysis and attenuation of impulsive sound pressure in large caliber weapon during muzzle blast[J].Journal of Mechanical Science and Technology,2011,25(10):2601-2606.DOI:10.1007/s12206-011-0731-2.
[10]王杨,姜孝海,杨绪普,等.小口径膛口射流噪声的数值模拟[J].爆炸与冲击,2014,34(4):508-512.DOI:10.11883/1001-1455(2014)04-0508-05.WANG Yang,JIANG Xiaohai,YANG Xupu,et al.Numerical simulation on jet noise induced by complex flows discharging from small caliber muzzle[J].Explosion and Shock Waves,2014,34(4):508-512.DOI:10.11883/1001-1455(2014)04-0508-05.
[11]路宽,赵俊利,雷红霞,等.高温高压大口径火炮膛口噪声场分布特性研究[J].河北农机,2014(1):59-60.DOI:10.3969/j.issn.1002-1655.2014.01.030.LU Kuan,ZHAO Junli,LEI Hongxia,et al.Distribution characteristics of muzzle noise field of high temperature and high pressure large caliber guns[J].Hebei Farm Machinery,2014(1):59-60.DOI:10.3969/j.issn.1002-1655.2014.01.030.
[12]LILLY D K.A proposed modification of the Germano subgrid-scale closure method[J].Physics of Fluids A:Fluid Dynamics,1992,4(3):633-635.DOI:10.1063/1.858280.
[13]王秉义.枪口噪声的声源和物理特性[J].兵工学报,1987,8(4):1-9.WANG Bingyi.The sound source and physical characteristics of the muzzle noise[J].Acta Armamentarii,1987,8(4):1-9.
[14]VEN T V D,LOUIS J,PALFREYMAN D,et al.Computational aeroacoustic analysis of a 1/4 scale G550 nose landing gear and comparison to NASA and UFL wind tunnel data[C]//Proceedings of 15th AIAA/CEAS Aeroacoustics Conference.American Institute of Aeronautics and Astronautics,Inc.,2006:33-45.DOI:10.2514/6.2009-3359.