二元混压式进气道窄缝形射流调节结构参数设计  

Structural parameter design of slot injection control for rectangle mix-compression inlet

作　　者：游进[1] 夏智勋[1] 刘冰[1] 吕仲[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2012年第7期1562-1570,共9页Journal of Aerospace Power

基　　金：武器装备预研基金(9140A28030309KG01)

摘　　要：针对窄缝形主动射流用于二元混压式超声速进气道再起动特性调节的结构参数设计,开展了大量定常数值模拟研究,得到了窄缝位置、宽度及喷射角度等结构参数对再起动特性的影响趋势,利用少量非定常算例验证了定常计算结果的准确性.结果表明:射流的注入使进气道产生超声速溢流,并出现可动气动喉道等新的再起动流场特征.约进气道流量1%的射流流量能产生约5%的溢流量,在溢流作用下,4.5%～11%的射流流量使进气道实现了再起动,射流流量越大,射流分离区也越大,进气道越难实现再起动.研究还发现:窄缝位置及宽度对射流溢流效率的影响很小,但窄缝位置存在一个有效作用范围,只有在距唇口35～65mm的位置注入射流,进气道才能实现再起动.射流喷射角对射流溢流效率的影响较大.射流喷射角越大,射流的溢流效率越高,再起动所需的射流流量及其范围也越小.Numerical simulation on structural parameter design of slot injection control restarting characteristics of rectangle mix-compression supersonic inlet was conducted. Effects of the slot position, width and injection angle on restarting characteristics were re- searched. A few unsteady numerical simulations were performed to verify the steady re- sults. The steady calculation results show that new restarting flow impress such as movable pneumatic throat appears, and the supersonic mass spillage increases with the injection. In- let restarts with the injection mass flux of 4.5 ~/60 ~11~ inlet mass flux as 5% inlet mass flux spills out with the injection mass flux of 1% inlet mass flux. When the distance between lip and slot is 35~65mm, inlet would restart and has same restarting characteristics. With the increase of injection angle, spillage efficiency of injection enhances, and the range of injec- tion mass flux for restart reduces. However the effects of slot width on spillage efficiency of injection and restarting characteristics of inlet is slight.

关 键 词：二元混压式进气道 窄缝形射流调节 再起动特性 数值模拟 结构参数设计 溢流效率 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]