当量比对带凹腔超声速燃烧室流动及燃烧特性的影响

贾真; 吴迪; 朴英

当量比对带凹腔超声速燃烧室流动及燃烧特性的影响

清华大学航天航空学院,北京 100084

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出版历程
- 收稿日期: 2011-09-05
- 刊出日期: 2012-08-28

Effect of equivalence ratio on flow and combustion characteristics of super-sonic combustor with cavity

School of Aerospace,Tsinghua University,Beijing 100084,China

摘要

摘要: 通过调节燃料氢喷射压力参数从而改变油气当量比,分别在冷态喷流与燃烧情况下计算了当量比对流场波系及燃料与空气的掺混、燃烧特性的影响.研究表明:增大当量比会增大燃烧反压,扩大上游边界层分离区,逐渐将激波串推向燃烧室进口;同时发现燃料与空气的混合性能在近场处受当量比影响较大,随当量比增大混合效果明显增强,而在远场处基本不再受当量比变化的影响;增大当量比一定程度增大射流穿透深度,但并不能明显改善燃料分布区不合理问题,导致燃烧效率随当量比单调下降;流场总压损失及凹腔阻力系数均同当量比成正比例关系,而流场摩擦阻力随当量比单调下降,且燃烧使摩擦阻力更小.
- 凹腔 /
- 当量比 /
- 燃烧反压 /
- 激波串 /
- 总压损失
Abstract: Numerical simulation on effect of equivalence ratio on flow field and combustion characteristics of supersonic combustor with cavity under the condition with/without chemical reactions was conducted by adjusting the fuel injection pressure to reach a certain equivalence ratio value.It is found that increasing equivalence ratio enhances combustion backpressure,expands the upstream boundary layer separation zone,and pushes shock train to the entrance of the combustor gradually.Also,enlarging equivalence ratio increases jet penetration depth gradually.In the field near fuel injector ,mixing performance was obviously enhanced by increasing equivalence ratio,while in the field far away from fuel injector,little effect was induced by equivalence ratio.In the aspects of total pressure loss and cavity drag coefficient,they had proportional relationships with equivalence ratio.
- cavity /
- equivalence ratio /
- combustion backpressure /
- shock train /
- total pressure loss

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参考文献(16)

[1]	Vinagradov V,Grachev V,Petrov M.Experimental investigation of 2-D dual mode scramjet with hydrogen fuel at Mach 4-6 .AIAA 90-5269,1990.
[2]	司徒明.煤油超燃冲压发动机性能分析[J].推进技术,1998,19(2):18-22. SITU Ming.Performance analysis of hydrocarbon-fueled scramjet[J].Journal of Propulsion Technology,1998,19(2):18-22.(in Chinese)
[3]	Young G,Balar R,Ashwani K G.Characterization of scramjet combustor with transverse fuel injection .AIAA 2006-1377,2006.
[4]	Lee S H,Kim H B,Mitani T.Mixing and combustion augmentations of transverse injection in scramjet combustor .AIAA Paper 2001-0384,2001.
[5]	Gouskov O V,Kopchenov V I.Investigation of ignition and flame stabilization behind the strut in supersonic flow .AIAA 2002-5227,2002.
[6]	Bussing T R A,Murman E M.Numerical investigation of 2-dimensional H₂-air flame holding over ramps and rearward facing steps .AIAA Paper 85-1250,1985.
[7]	Fox J S,Gastont M J,Houwingf A F P,et al.Instantaneous mole-fraction PLIF imaging of mixing layers behind hypermixing injectors .AIAA Paper 99-0774,1999.
[8]	Roudakov A S,Schikhmann Y,Semenov V,et al.Flight testing of an axisymmetric scramjet-russian recent advances .IAF Paper 93-S4,1993.
[9]	Rodriguez C G.CFD analysis of the CIAM/NASA scramjet .AIAA 2002-4128,2002.
[10]	Ben-Yakar A,Hanson R K.Cavity flameholders for ignition and flame stabilization in scramjets:review and experimental study .AIAA 98-3122,1998.
[11]	Sang-Hyeon L,Yong-Jin K.Mixing augmentation of transverse injection in scramjet combustor .AIAA 2000-0090,2000.
[12]	刘敬华,凌文辉,刘陵,等.设置空腔的超声速燃烧室流场数值模拟[J].推进技术,2000,21(2):56-59. LIU Jinghua,LING Wenhui,LIU Ling,et al.Numerical simulation on flowfield in supersonic combustor with cavity[J].Journal of Propulsion Technology,2000,21(2):56-59.(in Chinese)
[13]	丁猛,王振国.基于凹腔的超声速燃烧火焰稳定技术研究 .长沙:国防科技大学,2005. DING Meng,WANG Zhenguo.Investigation on flame-houlding in supersonic combustor based on cavity .Changsha:National University of Defense Technol,2005.(in Chinese)
[14]	Bhagwandin V A,Engblom W A,Georgiadis N J.Numerical simulation of a hydrogen fueled dual-mode scramjet engine using Wind-Us .AIAA 2009-5382,2009.
[15]	陈思员,徐旭.当量比对单凹腔超燃燃烧室流场影响的三维数值模拟[J].航空学报,2009,30(5):794-799. CHEN Siyuan,XU Xu.3-D numerical simulation of the influence of fuel equivalence ratio on single cavity supersonic combustor flow[J].Acta Aeronautica et Astronautica Sinica,2009,30(5):794-799.(in Chinese)
[16]	王春,司徒明,马继华,等.高温富油燃气超声速燃烧数值模拟[J].推进技术,2000,21(2):60-63. WANG Chun,SITU Ming,MA Jihua,et al.Numerical simulation on supersonic combustion of fuel-rich hot gas[J].Journal of Propulsion Technology,2000,21(2):60-63.(in Chinese)