火箭发动机燃气射流驱动液柱降噪实验

张磊; 阮文俊; 王浩; 王政伟

doi:10.13224/j.cnki.jasp.2016.05.032

火箭发动机燃气射流驱动液柱降噪实验

doi: 10.13224/j.cnki.jasp.2016.05.032

南京理工大学能源与动力学院, 南京 210094

基金项目:

国家自然科学基金(51305204)

详细信息

作者简介:
张磊(1987-),男,湖北仙桃人,博士生,主要从事火箭燃气射流噪声及降噪研究.

中图分类号: V435;TJ711
计量
- 文章访问数: 785
- HTML浏览量: 3
- PDF量: 563
- 被引次数: 0
出版历程
- 收稿日期: 2014-08-30
- 刊出日期: 2016-05-28

Experiment on jet noise reduction with a liquid column driven by rocket engine gas jet

School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China

摘要

摘要: 为了研究单兵火箭燃气射流噪声抑制的方法,设计了液体水柱放置在尾管中,采用高速摄影系统观察了高温高压燃气驱动液体水柱在大气环境中的扩散过程,并对气液混合物射流噪声声压进行了测量,对比了有无液体水柱两种状态下射流的测试结果.实验结果表明,在尾管中放置液体水柱后,由于气液之间的相互作用,改变了燃气射流流场结构以及降低了射流特征参数.通过与无液体水柱的燃气射流对比,发现有液体水柱时整个测点区域的噪声声压级峰值均有较大幅度的降低,且地面对声波的反射也减弱,噪声声压级峰值随着测点偏离射流中心轴线角度的增大而逐渐减小.因此,放置液体水柱后起到了明显的降噪效果,在偏离角为45°位置声压级峰值降低了6.4dB,验证了此方案的可行性.
- 燃气射流 /
- 气动噪声 /
- 液体水柱 /
- 声学测量 /
- 气液相互作用
Abstract: In order to investigate the effective method of individual rocket burned gas jet noise reduction, a designed liquid column was placed in the tail tube. The dispersion processes of high-temperature high-pressure combustion-gas driving the liquid column in the air was observed by using a high-speed photographic system, and gas-liquid mixture jet noise was also measured; the test results of jet were compared under two conditions of no-water-column and water-column. The experimental results show that then liquid column was put in the tail tube, the jet flow structure was changed and the jet flow parameters were decreased due to the interaction of gas jet with water. It is concluded that the sound pressure level peak is reduced to some extent in whole test points region with the liquid column, compared with the result of no liquid column gas jet; and the impact of the ground on the acoustic wave is weakened. With the increasing angle of the measuring points deviating from the jet central axis, the sound pressure level peak decreases. So the liquid column plays an important role in suppressing noise, the peak sound pressure level decreases by 6.4dB at the angle of 45°, validating the feasibility of noise reducing scheme.
- combustion-gas jet /
- aeroacoustics /
- liquid column /
- acoustic measurement /
- gas-liquid interaction

HTML

参考文献(18)

[1]	Sutherland L C.Progress and prolems in rocket noise prediction for ground facilities[R].AIAA 1993-4383,1993.
[2]	Gely D,Elias G,Bresson C.Reduction of supersonic jet noise:application to the Ariane 5 launch vehicle[R].AIAA 2000-2026,2000.
[3]	李军.单兵火箭燃气射流冲击噪声场的形成与发展[J].南京理工大学学报,2006,30(6):679-683. LI Jun.Forming and developing of impact jet noise flow field of individual rocket[J].Journal of Nanjing University of Science and Technology,2006,30(6):679-683.(in Chinese)
[4]	徐强,廖光煊,李军,等.火箭燃气射流近场噪声特性实验研究[J].推进技术,2002,23(4):318-320. XU Qiang,LIAO Guangxuan,LI Jun,et al.Experimental study of near field rocket noise in exhausted flow field[J].Journal of Propulsion Technology,2002,23(4):318-320.(in Chinese)
[5]	张统.航天发射污染控制[M].北京:国防工业出社,2010.
[6]	谭兴良.武器与机械噪声及其控制[M].北京:北京理工大学出版社,1993.
[7]	乔渭阳.航空发动机气动声学[M].北京:北京航空航天大学出版社,2010.
[8]	张福祥.火箭燃气射流动力学[M].哈尔滨:哈尔滨工程大学出版社,2004.
[9]	Krothapalli A,Ven Katakrishnan L,Elavarasan R,et al.Supersonic jet noise suppression by water injection[R].AIAA 2000-2025,2000.
[10]	Kandula M,Lonergan M J.Effective jet properties for the estimation of turbulent mixing noise reduction by water injection[R].AIAA 2007-3645,2007.
[11]	Callender B,Gutmark E,Martens S.Far-field acoustic investigation into chevron nozzle mechanisms and trends[J].AIAA Journal,2005,43(1):87-95.
[12]	王兴, 郑刘,周月荣,等.不同喷嘴射流流场结构及噪声[J]. 推进技术,2011,32(3):365-369. WANG Xing,ZHENG Liu,ZHOU Yuerong,et al.Flow field structure and noise for different nozzles[J].Journal of Propulsion Technology,2011,32(3):365-369.(in Chinese)
[13]	胡声超,李昂,鲍福廷,等.多喷管燃气降噪方案可行性数值研究[J].固体火箭技术,2012,35(2):198-202. HU Shengchao,LI Ang,BAO Futing,et al.Numerical research on jet noise reducing with multi-nozzle geometry[J].Journal of Solid Rocket Technology,2012,35(2):198-202.(in Chinese)
[14]	Kurbjun M C.Limited investigation of noise suppression by injection of water into exhaust of afterburning jet engine[R].NACA-RM-L57L05,1958.
[15]	徐悦,周旭,张志成,等.火箭发动机燃气射流喷水降噪研究[J].航空动力学报,2010,25(4):816-820. XU Yue,ZHOU Xu,ZHANG Zhicheng,et al.Reduction of rocket engine jet noise by water injection[J].Journal of Aerospace Power,2010,25(4):816-820.(in Chinese)
[16]	陈钰,周旭,童丽,等.喷水对火箭射流噪声的影响研究[J].环境工程,2012,30(增刊):172-175. CHEN Yu,ZHOU Xu,TONG Li,et al.Estimation of rocket noise reduction by water injection[J].Environmental Engineering,2012,30(suppl.):172-175.(in Chinese)
[17]	Thomas D N.Reductions in multi-component jet noise by water injection[R].AIAA 2004-2976,2004.
[18]	汪海洋,李晓东.超声速喷流啸声的控制方法[J].推进技术,2007,28(2):211-215. WANG Yanghai,LI Xiaodong.Control methods for supersonic jet screech tones[J].Journal of Propulsion Technology,2007,28(2):211-215.(in Chinese)