高超进气道自适应泄压槽的设计参数分析

刘媛; 金志光; 张堃元; 南向军

高超进气道自适应泄压槽的设计参数分析

南京航空航天大学能源与动力学院, 南京 210016

基金项目: 国家自然科学基金(11102086)

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出版历程
- 收稿日期: 2012-06-15
- 刊出日期: 2013-06-28

Parameters analysis of adaptive pressure relief slot in hypersonic inlet

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 采用自适应泄压控制技术解决宽范围定几何高超进气道低马赫数下自起动问题,利用数值仿真对一种采用自适应泄压控制的高性能二元高超进气道单个自适应泄压槽的位置、角度、有效流通面积等主要设计参数对泄漏量以及进气道总体性能的影响规律开展了研究.结果表明:泄压槽参数变化对基准进气道总体性能影响较小,总压恢复系数在2%范围内变化.位于唇口激波反射点下游的槽的泄漏量较大且随开槽角度的增加而减小,随有效流通面积的增加成线性增加;相同条件下,自适应泄压槽的泄漏量只有常规顺向放气槽的50%;随来流马赫数升高,自适应泄压槽的漏气量明显减小,高马赫数下接近气动自封闭状态.
- 高超声速进气道 /
- 定几何进气道 /
- 自适应泄压槽 /
- 参数分析 /
- 数值仿真
Abstract: In order to improve self-starting performance of the fixed-geometry inlet at low Mach number,a technology of self-adaptive pressure relief slot was proposed.The law about the location,direction and effective area of single adapted pressure relief slot was studied with a high performance two-dimensional hypersonic inlet utilizing the technology of numerical simulation.The result shows that:the slot has little influence on the model inlet,and the total pressure recovery ranges around 2%;the slot located downstream the cowl shock wave has large outgassing rate,which will increase as the angle descends and the effective area ascends.The outgassing rate of the adapted pressure relief slot is just 50% compared with normal slot under the same condition.It will drop as the Mach number increases,approaching self-close state at high Mach number condition.
- hypersonic inlet /
- fixed-geometry inlet /
- adaptive pressure relief slot /
- parameters analysis /
- numerical simulation

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参考文献(19)

[1]	Van Wie D M,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets[R].AIAA 96-2914,1996.
[2]	王翼.高超声速进气道启动问题研究[D].长沙:国防科学技术大学,2008. WANG Yi.Investigation on the starting characteristics of hypersonic inlet[D].Changsha:National University of Defense Technology,2008.(in Chinese)
[3]	金志光,张堃元.典型二元高超声速进气道与侧压式进气道的性能比较[J].航空动力学报,2008,23(9):1553-1560. JIN Zhiguang,ZHANG Kunyuan.Performance comparison between 2-D scramjet inlet and 3-D sidewall compression scramjet inlet[J].Journal of Aerospace Power,2008,23(9):1553-1560.(in Chinese)
[4]	Hamed A,Shih S H,Yeuan J J.A parametric study of bleed in shock boundary layer interactions[R].AIAA 93-0294,1993.
[5]	Haberle J,Gulhan A.Investigation of the flow field of a 2D SCRAM-jet inlet at Mach 7 with optional boundary layer bleed[R].AIAA 2007-5068,2007.
[6]	Schulte D,Henckels A,Neubacher R.Manipulation of shock/boundary-layer interactions in hypersonic inlets[J].Journal of Propulsion and Power,2001,17(3):585-590.
[7]	赵亮,袁化成,李博.溢流槽道对二元高超声速进气道性能影响[J].航空动力学报,2010,25(7):1573-1580. ZHAO Liang,YUAN Huacheng,LI Bo.Effect of spillage slot on the performance of two dimensional hypersonic inlet[J].Journal of Aerospace Power,2010,25(7):1573-1580.(in Chinese)
[8]	袁化成,梁德旺.抽吸对高超声速进气道起动能力的影响[J].推进技术,2006,27(6):525-528. YUAN Huacheng,LIANG Dewang.Effect of suction on starting of hypersonic inlet[J].Journal of Propulsion Technology,2006,27(6):525-528.(in Chinese)
[9]	梁德旺,钱华俊.抽吸孔板的气动实验及附面层抽吸数值模拟[J].航空学报,2002,23(6):512-516. LIANG Dewang,QIAN Huajun.Experimental investigation of aerodynamic characteristics of porousplates and numerical simulation of boundary layer suction[J].Acta Aeronautica et Astronautica Sinica,2002,23(6):512-516.(in Chinese)
[10]	Davis D O,Willis B P,Hingst W R.Flow field masurements in a slot-bled oblique shock wave and turbulent boundary-layer interaction[R].AIAA 95-2168,1995.
[11]	刘志伟,马高建,崔金平.附面层吸除对二元混压式进气道起动影响分析[J].弹箭与制导学报,2009,29(3):149-152. LIU Zhiwei,MA Gaojian,CUI Jinping.Influence of boundary layer bleed sew to start[J].Journal of Projectiles,Rockets,Missiles and Guidance,2009,29(3):149-152.(in Chinese)
[12]	莫展,王新月,未军光.槽对超声速混压式进气道性能及边界层的影响[J].航空动力学报,2009,24(2):302-306. MO Zhan,WANG Xinyue,WEI Junguang.Performance and boundary layer of flow in axisymmetric mixed-compression supersonic inlet with cavity[J].Journal of Aerospace and Power,2009,24(2):302-306.(in Chinese)
[13]	李璞,郭荣伟.一种高超声速进气道起动/再起动的数值研究[J].航空动力学报,2010,25(5):1049-1055. LI Pu,GUO Rongwei.Numerical simulation of the start and restart performance of a hypersonic inlet[J].Journal of Aerospace and Power,2010,25(5):1049-1055.(in Chinese)
[14]	金志光,张堃元.宽马赫数范围高超声速进气道转动唇口变几何方案研究[J].航空动力学报,2010,25(7):1553-1560. JIN Zhiguang,ZHANG Kunyuan.Investigation of a variable geometry scramjet inlet with a rotating cowl operating in a large mach number range[J].Journal of Aerospace and Power,2010,25(7):1553-1560.(in Chinee)
[15]	张华军,梁德旺,郭荣伟.一种组合发动机变几何进气道流场特性研究[J].航空动力学报,2009,24(10):2201-2207. ZHANG Huajun,LIANG Dewang,GUO Rongwei.Study of flow characteristics for a variable geometry inlet on combined engine[J].Journal of Aerospace and Power,2009,24(10):2201-2207.(in Chinese)
[16]	Marc B.Airbreathing space launcher interest of a fully variable geometry propulsion system status 1999[R].AIAA 99-2376,1999.
[17]	Huebner L D,Rock K E,Ruf E G,et al.Hyper-X flight engine ground testing for X-43 flight risk reduction[R].AIAA 2001-1809,2001.
[18]	金志光,张堃元.带前体压缩的前掠侧压式进气道实验及数值研究[J].推进技术,2005,26(6):508-512. JIN Zhiguang,ZHANG Kunyuan.Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression[J].Journal of Propulsion Technology,2005,26(6):508-512.(in Chinese)
[19]	金志光,张堃元.高超侧压式进气道M6高焓脉冲风洞实验[J].推进技术,2005,26(4):319-323. JIN Zhiguang,ZHANG Kunyuan.Test of a generic sidewall compression scramjet inlet in the high-enthalpy impulse wind tunnel[J].Journal of Propulsion Technology,2005,26(4):319-323.(in Chinese)