方波形单脉冲射流调节对进气道 再起动特性的影响

游进; 夏智勋; 方传波; 胡建新; 刘冰

方波形单脉冲射流调节对进气道再起动特性的影响

国防科学技术大学航天与材料工程学院,长沙 410073

基金项目: 武器装备预研基金项目(9140A28030309KG01)

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出版历程
- 收稿日期: 2011-02-18
- 修回日期: 2011-04-25
- 刊出日期: 2011-10-28

Influence of single square pulse injection on restart characteristics for mixed-compression inlet

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

摘要

摘要: 对方波形单脉冲射流作用下的混压式超声速进气道再起动过程进行了非定常数值仿真研究.结果表明,在外压缩楔面注入单个周期的方波形脉冲射流,在射流阻挡作用下,进入进气道的流量减小,脱体激波被吸入唇口,当射流流量大于某阈值后,进气道即能实现再起动.该阈值约为进气道流量的5%,再起动所需的射流作用时间小于15ms,所需的射流总质量小于0.0014kg.研究还发现,当射流流量略小于阈值时,射流作用下的进气道流场为135Hz的高频振荡流场.当射流流量大于阈值时,射流流量越大,流场响应越快,再起动所需的脉冲射流作用时间也越短,射流总质量越小.
- 混压式超声速进气道 /
- 再起动特性 /
- 方波型单脉冲射流 /
- 非定常数值仿真 /
- 振荡流场
Abstract: The unsteady numerical study of the mixed-compression inlet restarting flow with the single square pulse injection was performed.The results show that mass flow entering the inlet decreased and external normal shock is swallowed into lip with the joining of the injection on ramp,because of the blockage of the jet to incoming flow.As the mass flow of jet exceeds the threshold value of 5% of inlet mass flow,and the duration time of injection is less than 15ms,needing at least 0.0014kg gas for injection,the unstart flow of inlet will restart.And a high-frequency oscillation flow with 135Hz arises when the mass flow of jet is less lightly than the threshold value.The duration time for restart and total gas mass reduce with the increase of mass flow of jet because of the faster flow response when the mass flow of jet exceeds the threshold value.
- mixed-compression supersonic inlet /
- restart performance /
- single square pulse injection /
- unsteady numerical simulation /
- oscillation flow

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参考文献(14)

[1]	Satoru T,Brett J C,Akira F,et al.Inlet unstart influence on aerodynamics characteristics of next generation supersonic transport(SST) .AIAA-98-5546,1998.
[2]	Tahir R B,Sannu M,Timofeev E V.Unsteady starting of high mach number air inlets-a CFD study .AIAA 2003-5191,2003.
[3]	Wagner J L,Valdivia A,Yuceil K B,et al.An experimental investigation of supersonic inlet unstart .AIAA 2007-4352,2007.
[4]	Maru Y,Tanatsugu N,Sato T,et al.Multi-row disk arrangement concept for spike of axisymmetric air inlet .AIAA 2004-3407,2004.
[5]	Najafiyazdi A,Tahir R,Timofeev E V.Analytical and numerical study of flow starting in supersonic inlets by mass spillage .AIAA 2007-5072,2007.
[6]	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)
[7]	Schulte D,Henckels A,Wepler U.Reduction of shock induced boundary layer separation in hypersonic inlets using bleed [J].Aerospace Science and Technology,1998,2(4):231-139.
[8]	Haberle J,Gulhan A.Investigation of the performance of a scramjet inlet at Mach 6 with boundary layer bleed .AIAA 2006-8139,2006.
[9]	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 and Astronautics,2006,38(5):577-582.(in Chinese)
[10]	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)
[11]	Van W D,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets .AIAA 96-2914,1996.
[12]	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)
[13]	Simon T,Philippe D,Sebastien D.Experimental study of supersonic inlet buzz[J].AIAA Journal,2006,44(10): 2354-2365.
[14]	Ferri A,Nucci L M,Louis M.The origin of aerodynamic instability of supersonic inlets at subcritical conditions .Langley Field,VA,U.S.:NACA RM-L50K30,1951.