超声速燃烧室内氢气燃烧的三维数值研究

3-D numerical investigation on supersonic hydrogen combustion in scramjet combustor

摘要: 通过隐式耦合求解可压缩N-S方程及组分方程,对氢气的超声速燃烧进行三维数值模拟,对燃烧室内的冷热态流场,以及氢气喷射压力对燃烧的影响进行了系统分析和研究.研究表明,燃烧放热以及氢气喷射压力提高都会导致燃烧室内波系结构变化,沿周向的流向涡增强,压缩波和膨胀波与氢气核心区的相互作用增强,促进氢气和空气的掺混,更利于氢气的燃烧.
- 航空、航天推进系统 /
- 超声速燃烧 /
- 氢气 /
- 流向涡 /
- 超燃冲压发动机
Abstract: 3-Dnumerical simulation for supersonic hydrogen combustion was performed by solving the compressible Navier-Stokes equation and composition equations using implicit finite volume methods.Meanwhile,the effect of hydrogen injection pressure on combustion was analyzed and studied.The results show that,owing to the heat release from combustion and the influences of hydrogen's injection pressure,the flow field changes greatly,leading to enhanced streamwise vortex and stronger interaction between waves in the combustor and hydrogen flow,and also facilitating the mixing of hydrogen and air for improved hydrogen combustion performance.
- aerospace propulsion system /
- supersonic combustion /
- hydrogen /
- streamwise vortex /
- scramjet

[1]	刘陵,刘敬华,张榛,等.超声速燃烧和超声速燃烧发动机[M].西安:西北工业大学出版社,1993.
[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.
[3]	Vinagradov V,Grachev V,Petrov M.Experimental investigation of 2-D dual mode scramjet with hydrogen fuel at Mach 4-6[R].AIAA 90-5269.
[4]	Owens M G,Tehranian S,Segal C.Flame-holding configuration for combustion in Mach 1.8 airflow[J].Journal of Propulsion and Power,1998,14(4):456-461.
[5]	Voland R T,Auslender A H,Smart M K,et al.CIAM/NASA Mach 6.5 scramjet flight and ground test[R].AIAA 99-4848.
[6]	Rodriguez C G.CFD analysis of the CIAM/NASA scramjet[R].AIAA 2002-4128.
[7]	Roudakov A S,Semenov V L,Hicks J W.Recent flight test results of the joint CIAM-NASA Mach 6.5 scramjet flight program[R].NASA/TP 1998-206548.
[8]	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.