喷管间距及偏角对超声速喷流噪声特性影响研究  

Impact Study of Nozzle Distance and Nozzle Angle on Supersonic Jet

作　　者：张津泽 王国辉[2] 徐珊姝 ZHANG Jin-ze;WANG Guo-hui;XU Shan-shu(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]中国运载火箭技术研究院,北京100076

出　　处：《强度与环境》2022年第1期42-47,共6页Structure & Environment Engineering

基　　金：装发预研领域基金(6140206040116HT19001)。

摘　　要：为研究喷管间距、喷管偏角对超声速喷流噪声特性的影响,设计了超声速喷流噪声试验系统,对不同喷管间距、不同喷管偏角下喷流噪声进行了分析。实验结果表明,超声速喷流噪声具有很强的指向性,随着测点与喷流轴向夹角从30度增加到150度,噪声声压级峰值从132.4dB下降到110.0dB,峰值频率基本不变,随着喷管间距的从25mm增大到35mm,噪声声压级峰值下降20dB以上,峰值频率从10250Hz上升到11130Hz;随着喷管偏角从-5度增大到10度,噪声峰值频率从10300Hz上升到10900Hz。To investigate the effect of nozzle distance and nozzle on supersonic jet noise characteristic,a supersonic jet noise experimental system was designed.Jet noise under different working condition was analyzed.The result shows that supersonic jet noise has a strong directionality,with the angle between measuring point and jet-axis direction increases from 30°to 150°,the peak of the sound pressure level decreases from 132.4dB to 110.0dB,and the peak frequency changes little.With the nozzle distance increase from 25mm to 35mm,the peak of the sound pressure level decreases more than 20dB,and the peak frequency increases from 10250Hz to 11130Hz.With the nozzle angle increase from-5°to 10°,the peak frequency increases from 10300Hz to 10900Hz.

关 键 词：喷流噪声 喷管间距 喷管偏角 峰值频率 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]