超声速横侧射流燃烧中可压缩性影响的数值研究  

Numerical investigation of compressibility effects on supersonic combustion with transverse injection

作　　者：韩省思[1] 叶桃红[1] 赵平辉[1] 朱旻明[1] 陈义良[1] 

机构地区：[1]中国科技大学热科学和能源工程系,安徽合肥230027

出　　处：《推进技术》2009年第5期538-543,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(50776085)

摘　　要：为了研究湍流的可压缩性效应对超声速燃烧的影响,对复杂的超声速横侧射流氢气/空气燃烧流场进行了数值模拟。采用修正的k-ε湍流模型(包括膨胀可压缩性和激波不稳定性两部分修正),考虑H2/Air详细化学反应机理(GRI-Mech2.11机理,10组分,28基元反应)。结果表明,可压缩性修正k-ε湍流模型能够预测复杂的超声速横侧射流流场结构。可压缩性使流体分离增强,湍流混合受到抑制,从而显著影响了超声速燃烧过程,数值模拟中需要考虑可压缩性效应的影响。Supersonic combustion flow fields with transverse injection were simulated to study the compressibility effect utilizing the modified k-ε turbulence model including dilatational compressibility and shock unsteadiness effects with comprehensive kinetic mechanism of H2/air reaction GRI-Mech 2.11,10 components,28 elementary reactions.The results show that the modified k-ε model can resolve the complex supersonic flow field with transverse injection,and the flow separation is strengthened and turbulent mixing p...

关 键 词：压缩性效应 超音速燃烧 湍流模型 数值仿真 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]