带制退器的膛口射流噪声数值模拟与实验研究

赵欣怡; 周克栋; 赫雷; 陆野; 王佳

doi:10.11883/bzycj-2018-0279

带制退器的膛口射流噪声数值模拟与实验研究

doi: 10.11883/bzycj-2018-0279

赵欣怡^1,,
周克栋^1, ,,
赫雷¹,
陆野¹,
王佳²

1.
南京理工大学机械工程学院，江苏南京 210094
2.
中国兵器工业第208研究所，北京 102202

基金项目: 联合基金(6141B02040208)

详细信息

作者简介:
赵欣怡(1991－　)，女，博士研究生，x.zhao@njust.edu.cn

通讯作者:
周克栋(1964－　)，男，博士，教授，博士生导师，zkd81151@126.com

中图分类号: O389; TB533
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- 被引次数: 0
出版历程
- 收稿日期: 2018-08-08
- 修回日期: 2018-11-05
- 刊出日期: 2019-10-01

Numerical simulation and experimental study on jet noise from a small caliber rifle with a muzzle brake

ZHAO Xinyi^1
,,
ZHOU Kedong^{1
, ,},
HE Lei¹,
LU Ye¹,
WANG Jia²

1.
School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China
2.
No.208 Research Institute of China Ordnance Industries, Beijing 102202, China

摘要

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。
- 射流噪声 /
- 计算气动声学 /
- 膛口制退器 /
- 噪声指向性
Abstract: 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 Williams-Hawkings) 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.
- jet noise /
- computational aeroacoustics /
- muzzle brake /
- noise directivity

HTML全文

图 1 计算区域示意图及边界条件

Figure 1. Schematic diagram of computational domain and boundary condition

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图 2 初始条件

Figure 2. Initial conditions

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图 3 膛口制退器示意图

Figure 3. Schematic diagram of muzzle brake

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图 4 计算区域网格划分

Figure 4. Grid model of computational domain

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图 5 声监测点俯视示意图

Figure 5. Top schematic diagram of receiver locations

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图 6 实验方案示意图

Figure 6. Schematic diagram of experimental scheme

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图 7 膛口位置测点分布图

Figure 7. Layout of measurement points in the far field

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图 8 实验现场

Figure 8. Photos of experimental field

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图 9 t=0.5 ms时膛口制退器截面流线分布

Figure 9. Streamlines in muzzle brake at t=0.5 ms

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图 10 压力等值线(上半部分)和密度等值线(下半部分）

Figure 10. Pressure contours in the upper half and density contours in the lower half

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图 11 射流噪声总声压级指向分布

Figure 11. Directional distribution of overall sound pressure level (OASPL) of jet noise

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图 12 测点压力波形

1. Initial shock wave; 2. Muzzle blast; 3. Noise wave

Figure 12. Pressure-time curves at measurement points

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表 1 噪声总声压级的实测数据平均值

Table 1. Average of measured data for overall sound pressure level

测点	测点位置		L_oasp/dB	测点	测点位置		L_oasp/dB	测点	测点位置		L_oasp/dB
测点	r/m	θ/(°)	L_oasp/dB	测点	r/m	θ/(°)	L_oasp/dB	测点	r/m	θ/(°)	L_oasp/dB
P1	1.0	90	126.26	P5	1.0	45	131.73	P9	1.0	0	132.77
P2	1.5	90	124.83	P6	1.5	45	130.18	P10	1.5	0	131.01
P3	2.0	90	123.34	P7	2.0	45	128.65	P11	2.0	0	130.08
P4	2.5	90	121.82	P8	2.5	45	125.60	P12	2.5	0	128.64

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表 2 总声压级计算结果与实验结果的对比

Table 2. Comparison between calculated and experimental overall sound pressure levels

测点(θ=90°)	L_oasp/dB		误差/%	测点(θ=45°)	L_oasp/dB		误差/%	测点(θ=0°)	L_oasp/dB		误差/%
测点(θ=90°)	实验	计算	误差/%	测点(θ=45°)	实验	计算	误差/%	测点(θ=0°)	实验	计算	误差/%
P1	126.26	128.72	−1.9	P5	131.73	128.96	2.1	P9	132.77	125.89	5.2
P2	124.83	126.01	−0.9	P6	130.18	124.51	4.4	P10	131.01	121.57	7.2
P3	123.34	123.65	−0.3	P7	128.65	121.87	5.3	P11	130.08	119.23	8.3
P4	121.82	121.47	0.3	P8	125.60	119.44	4.9	P12	128.64	117.84	8.4

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参考文献(14)

[1]	BOGEY C, MARSDEN O, BAILLY C. Effects of moderate Reynolds numbers on subsonic round jets with highly disturbed nozzle-exit boundary layers [J]. Physics of Fluids, 2012, 24(10): 53. DOI: 10.1063/1.4757667.
[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 of 12th 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.