超音喷流啸音发声机理的实验研究  

ON THE GENERATION MECHANISMS OF SUPERSONIC JET SCREECH TONES

作　　者：汪洋海[1] 李晓东[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《工程热物理学报》2006年第2期232-234,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金项目资助(No.10472010)高等学校博士学科点专项科研基金项目资助(No.2005006021)

摘　　要：啸音是超音速喷流噪声的三大成分之一,其特点是向上游传播的离散纯音,被认为是飞机部件声疲劳的重要因素之一。但到目前为止,啸音仍是喷流噪声研究中理解最少、预测能力最低的成分,研究表明这主要是因为啸音受环境的影响很大,如啸音的强度就受到喷流马赫数、喷流温度、喷嘴唇口厚度以及形状等的影响。本文通过实验研究了在超音速喷流情况下喷嘴唇口厚度对啸音幅值、模态等的影响。实验结果表明,随着喷嘴厚度的增加,啸音的幅值增加达到了10 db以上。啸音的频率则随着唇口厚度的增加有所减小。Screech is, so far, the least understood, least predictable component of supersonic jet noise. The main reason for this is its sensitivity to change in the surrounding environment, such as the jet Mach number, the jet temperature and the nozzle lip thickness. It has been regarded as a potential cause of sonic fatigue to jet engines. The goals of this work were to understand the amplitude and frequency of screech to be dependent on nozzle lip thickness. It was found that the screech intensity can be increased by lOdB simply by using a thicker lip nozzle and the frequency of screech was decreased by the variations.

关 键 词：喷流噪声 啸音 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]