首页 | 本学科首页   官方微博 | 高级检索  
     检索      

1种新型增推喷管的数值研究
引用本文:林卉,李志强.1种新型增推喷管的数值研究[J].航空发动机,2012,38(2):51-54.
作者姓名:林卉  李志强
作者单位:北京航空航天大学能源与动力工程学院,北京,100191
摘    要:针对轴对称喷管,利用数值方法研究了其出口形成的气动喉道的控制射流参数对喷管推力系数的影响。计算结果表明:射流控制能在喷管出口处形成气动喉道,即所研究喷管成为新型的固-气双喉道喷管,减小了喷管的有效出口面积,使其膨胀更完全,从而能够有效增大过膨胀喷管的推力系数。同时,射流角度对喷管出口实际面积和流场有一定的影响,顺向射流能获得更好的增推效果。

关 键 词:喷管  推力系数  气动喉道  射流  航空发动机

Numerical Research of a New Increasing Thrust Nozzle
Authors:LIN Hui  LI Zhi-qiang
Institution:(School of Jet Propulsion, Beihang University, Beijing 100191, China)
Abstract:The effect of the fluidic injection parameters of gas throat at the outlet on axisymmetric nozzle thrust coefficient were investigated by the numerical method. The results show that the fluidic injection creates a gas throat at the outlet of nozzle, it can be called solid-gas dual throat nozzle which can reduce the outlet area effectively, and improve the expansion of nozzle. The fluidic injection can raise the thrust ratio of over expansion nozzle effectively. The injection angle influences the real outlet area and flow of the nozzle, the forward injection can get the better thrust improvement.
Keywords:nozzle  thrust coefficient  gas throat  fluidic injection  aeroengine
本文献已被 CNKI 维普 万方数据 等数据库收录!
点击此处可从《航空发动机》浏览原始摘要信息
点击此处可从《航空发动机》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号