超声速喷流啸声的控制方法  

Control methods for 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：《推进技术》2007年第2期211-215,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(10472010);高等学校博士学科点专项科研基金(2005006021)资助项目

摘　　要：通过实验比较了几种超声速喷流啸声的控制方法,包括附加三角凸台和开V形槽的收敛喷嘴。实验结果表明,带三角凸台和V槽的喷嘴对啸声幅值有明显的抑制,尤其是凸台喷嘴对啸声的模态也产生了明显的影响,但是啸声成分仍然存在,并且在上游方向依然占主导地位。在此基础上提出了一种新的控制方法——凸台加V槽的组合喷嘴,实验结果表明,组合喷嘴完全抑制了啸声,而且对于其它超音速喷流噪声成分的幅值也有一定程度的降低。最后还对各种结构喷嘴的气动推力损失进行了综合评估,结果表明组合喷嘴的推力损失介于V槽喷嘴和三角凸台喷嘴之间,平均推力损失在3%左右。Several methods on controlling supersonic jet screech tones are experimentally compard. The tested nozzle configuration consists of Delta-Tabs and chevrons. The experimental results show that the nozzles, with Delta-Tabs or Chevrons, distinctly decrease the amplitude of screech tones. The Delta-Tab nozzle also influences the modes of screech tones. However, screech tones still exist and dominate in the upstream direction. Based upon the experimental investigation, the compound nozzle, Delta-Tab plus chevron, is proposed. It is demonstrated that the compound nozzle totally eliminates screech tones. Furthermore, the compound nozzle can also reduce,to some extent, the intensities of other components of supersonic jet noise. In addition, thrust losses of nozzles in the paper have been evaluated. The results show that the thrust loss of compound is about 3% between the chevron and Delta-Tabs.

关 键 词：喷流噪声 啸声 控制 推力损失 

分 类 号：V216.5[航空宇航科学与技术—航空宇航推进理论与工程]