二元混压式进气道窄缝形射流调节结构参数设计

游进; 夏智勋; 刘冰; 吕仲

二元混压式进气道窄缝形射流调节结构参数设计

国防科学技术大学航天与材料工程学院,长沙 410073

基金项目: 武器装备预研基金(9140A28030309KG01)

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出版历程
- 收稿日期: 2011-08-28
- 刊出日期: 2012-07-28

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

College of Aerospace and Material Engineering, National University of Defense Technology,Changsha 410073,China

摘要

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.
- 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
Abstract: 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 researched.A few unsteady numerical simulations were performed to verify the steady results.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.Inlet restarts with the injection mass flux of 4.5%~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 injection mass flux for restart reduces.However the effects of slot width on spillage efficiency of injection and restarting characteristics of inlet is slight.
- rectangle mix-compression inlet /
- slot injection control /
- restarting characteristics /
- numerical simulation /
- structural parameter design /
- spillage efficiency

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参考文献(18)

[1]	Kantrowitz A,Donaldson C.Preliminary investigation of supersonic diffuser .NACA WRL-713,1945.
[2]	Van Wie D M,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets .AIAA 96-2914,1996.
[3]	Tahir R B,Molder S,Timofeev E V.Unsteady starting of high Mach number air inlets-a CFD study .AIAA 2003-5191,2003.
[4]	Wagner J L,Valdivia A,Yuceil K B,et al.An experimental investigation of supersonic inlet unstart .AIAA 2007-4352,2007.
[5]	Yusuke M.Multi-row disk arrangement concept for spike of axisymmetric air inlet .AIAA 2004-3407,2004.
[6]	Najafiyazdi A,Tahir R,Timofeev E V.Analytical and numerical study of flow starting in supersonic inlets by mass spillage .AIAA 2007-5072,2007.
[7]	潘瑾,张堃元.移动唇口变收缩比侧压式进气道反压特性和自起动性能[J].航空动力学报,2009,24(1):104-109. PAN Jin,ZHANG Kunyuan.Study on back pressure abd self-starting characteristics for sidewall-compression inlet with variable internal contraction ratio by moving cowl[J].Journal of Aerospace Power,2009,24(1):104-109.(in Chinese)
[8]	张华军,梁德旺.某组合发动机进气道抽吸作用分析[J].南京航空航天大学学报,2006,38(5):577-582. ZHANG Huajun,LIANG Dewang.Analysis of suction roles for supersonic inlet on combined engine[J].Journal of Nanjing University of Aeronautics & Astronautics,2006,38(5):577-582.(in Chinese)
[9]	李宇飞,何国强,刘佩进.一种辅助高超音速进气道起动方法研究[J].固体火箭技术,2007,30(5):392-395. LI Yufei,HE Guoqiang,LIU Peijin.Investigation on one aid hypersonic inlet starting method[J].Journal of Solid Rocket Technology,2007,30(5):392-395.(in Chinese)
[10]	Harrison N A,Anderson J,Fleming J L,et al.Computational analysis of active flow control of a boundary layer ingesting serpentine inlet diffuser .AIAA 2006-874, 2006.
[11]	方传波,夏智勋,胡建新,等.基于主动射流控制的二元混压式进气道起动特性研究[J].固体火箭技术,2010,33(3):280-284. FANG Chuanbo,XIA Zhixun,HU Jianxin,et al.Study on starting characteristics of a two-dimensional supersonic inlet based on active injection control[J].Journal of Solid Rocket Technology,2010,33(3):280-284.(in Chinese)
[12]	游进,夏智勋,方传波,等.方波形单脉冲射流调节对进气道再起动特性的影响[J].航空动力学报,2011,26(10):2181-2187. YOU Jin,XIA Zhixun,FANG Chuanbo,et al.Influence of single square pulse injection on restart characteristics for mixed-compression inlet[J].Journal of Aerospace Power,2011,26(10):2181-2187.(in Chinese)
[13]	Porzio A J,Franke M C.Experimental study of a confined jet thrust vector control nozzle .AIAA 86-0448,1986.
[14]	Srivastava B.Lateral jet control of supersonic missile:computational and experimental comparisons[J].Spacecraft and Rockets,1998,35(2):140-146.
[15]	McGilvaray M,Morgan R G.Effects of upstream injection on scramjet performance using an entropy-based method[J].Journal of Propulsion and Power,2009,25(2):295-302.
[16]	Meter F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
[17]	Aso S,Okuyama S,Kawai M,et al.Experimental study on mixing phenomena in supersonic flows with slot injection .AIAA 91-0016,1991.
[18]	Spaid F W,Cassel L A.Aerodynamic interference induced by reaction controls .AGARD-AG-173,1973.