双燃烧室冲压发动机直连式实验与数值仿真

谭建国; 吴继平; 王振国

双燃烧室冲压发动机直连式实验与数值仿真

国防科学技术大学航天科学与工程学院, 长沙 410073

基金项目: 国家自然科学基金(51076164,11272351)

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出版历程
- 收稿日期: 2012-06-21
- 刊出日期: 2013-07-28

Direct-connect experiment and numerical simulation on dual-combustor ramjet

1. School of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

摘要

摘要: 通过直连式实验和数值仿真,对双燃烧室冲压发动机的流场结构和性能进行了研究.数值仿真采用了半全局多步化学反应机理,计算的压力分布和实验结果基本一致,计算结果表明:中心高温富油燃气与边区空气在混合层内快速反应,热力喉道出现在约0.9m处,出口处的燃烧效率达到了较高水平.提出了结合直连式实验和数值计算的性能估算方法,结果表明:双燃烧室发动机在马赫数为4,高度为17km状态时具有较高的性能,当燃油当量比为0.9时,发动机内推力为8.3kN,内推力比冲为12.29kN·s/kg,更高的燃油当量比将导致超燃进气道不起动.
- 双燃烧室冲压发动机 /
- 直连式实验 /
- 数值仿真 /
- 推力 /
- 比冲
Abstract: The flow field structure and performance of dual-combustor ramjet (DCR) were investigated through direct-connected experiment and numerical simulations.Semi-global kinetic mechanism was adopted in the simulations.The simulated pressure distributions agreed with the experimental data.Results show that:rapid reaction occurs in the mixing-layer between central high-temperature fuel-rich gas and peripheral air,the thermal choked throat appears at the position of 0.9m,and the combustion efficiency reaches a relatively high level.A method of assessing performance according to experiment and numerical simulation was brought forward.Results show that:the performance of the DCR presented is good under the condition of Mach number is 4.0,altitude is 17km.When the equivalence ratio is 0.9,the internal thrust is 8.3kN and specific impulse is 12.29kN ·s/kg.However,increasing equivalence ratio leads to unstart of inlet.
- dual-combustor ramjet(DCR) /
- direct-connected experiment /
- numerical simulation /
- thrust /
- specific impulse

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参考文献(15)

[1]	Fry R S.A century of ramjet propulsion technology evolution[J].Journal of Propulsion and Power,2004,20(1):27-58.
[2]	温杰.美国海军的HyFly计划[J].飞航导弹,2008(12):10-13. WEN Jie.HyFly project in U.S.navy[J].Cruise Missile,2008(12):10-13.(in Chinese)
[3]	Stockbridge R D,Schetz J A,Waltrup P J,et al.Combustion inlet interaction and modeling of hypersonic dual combustion ramjet engine [R].DTIC,ADA162111,1984.
[4]	Waltrup P J.The dual combustor ramjet:a versatile propulsion system for hypersonic tacticle missile application [R].N93-1760705-20,1992.
[5]	王春,陆惠萍,司徒明.双燃式冲压发动机中超燃燃烧室冷态流场数值模拟[J].推进技术,1999,20(5):35-39. WANG Chun,LU Huiping,SITU Ming.Numerical predictions of cold flowfield of supersonic combustor in dual combustor ramjet[J].Journal of Propulsion Technology,1999,20(5):35-39.(in Chinese)
[6]	李璞,郭荣伟.亚/超燃混合发动机模块间界面参数设计及数值仿真[J].航空动力学报,2009,24(8):1837-1842. LI Pu,GUO Rongwei.Design of the interface between ramjet and scramjet modules of dual combustor ramjet and flow field simulation[J].Journal of Aerospace Power,2009,24(8):1837-1842.(in Chinese)
[7]	孙英英,司徒明,王春,等.双燃烧室中煤油超燃实验研究[J].流体力学实验与测量,2000(1):51-56. SUN Yingying,SITU Ming,WANG Chun,et al.Experimental investigation of kerosene supsonic combustion in DCR[J].Experiments and Measurements of Fluid Mechanics,2000(1):51-56.(in Chinese)
[8]	朱淼,向红军.基于FLUENT的双燃烧室火箭发动机数值仿真研究 [C]//中国宇航学会固体火箭推进专业委员会第26届年会论文集(发动机分册).张家界中国:中国宇航学会,2009:175-179.
[9]	于江飞,晏至辉,刘卫东.双燃烧室冲压发动机富油燃气超声速燃烧数值模拟[J].弹箭与制导学报,2009,29(2):169-173. YU Jiangfei,YAN Zhihui,LIU Weidong.Numerical simulation on supersonic combustion of fuel-rich gas for a dual combustor ramjet[J].Journal of Projectiles,Rockets,Missiles and Guidance,2009,29(2):169-173.(in Chinese)
[10]	晏至辉,陈逖,于江飞,等.双燃烧室冲压发动机超声速混合层混合增强数值研究[J].航空动力学报,2010,25(4):821-828. YAN Zhihui,CHEN Ti,YU Jiangfei,et al.Numerical study on mixing enhancement for supersonic mixing layer in dual combustor ramjet[J].Journal of Aerospace Power,2010,25(4):821-828.(in Chinese)
[11]	潘余,李大鹏,刘卫东,等.超燃冲压发动机燃烧模态转换实验研究[J].爆炸与冲击,2008,28(4):293-297. PAN Yu,LI Dapeng,LIU Weidong,et al.Combustion mode transition in a scram jet engine[J].Explosion and Shock Waves,2008,28(4):293-297.(in Chinese)
[12]	王成鹏,杨永阳,刘晨,等.超燃燃烧室流场计算方法比较分析[J].航空动力学报,2009,24(5):963-969. WANG Chenpeng,YANG Yongyang,LIU Chen,et al.Comparative analysis of computational methods of supersonic combustor flowfield[J].Journal of Aerospace Power,2009,24(5):963-969.(in Chinese)
[13]	Franzelli B,Riber E,Sanjosé M,et al.A two-step chemical scheme for kerosene-air premixed flames[J].Combustion and Flame,2010,157(7):1364-1371.
[14]	Watanabe H,Suwa Y,Matsushita Y,et al.Spray combustion simulation including soot and NO formation[J].Energy Conversion and Management,2007,48(7):2077-2089.
[15]	Ueda S,Kouchi T,Takegoshi M,et al.Performance of a scramjet engine model in Mach 6 flight condition[J].Shock Waves,2009,2:1129-1134.