超声速空间发展燃烧反应剪切层放热效应分析  

Analysis of the energy release effects in supersonic reacting flows

作　　者：苗文博[1] 程晓丽[1] 王强[1] 

机构地区：[1]航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2008年第3期339-343,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金重大研究计划项目(90305014)

摘　　要：为探索化学反应对混合燃烧的影响机理,本文从流体力学基本方程出发,采用直接数值模拟方法研究了二维7组元/8反应化学非平衡剪切层的流动,讨论了数值上考虑化学反应放热对流动混合的影响,并分析其机理。研究发现:在相同的基频扰动促发下,考虑化学反应时混合层厚度变薄,且混合层的厚度会随着燃料组分的增大先变小后增大,涡量厚度发展至饱和的位置逐渐靠后;反应放热和组分含量影响湍流切应力和湍动能的变化,涡量厚度随着湍动能以及湍流切应力规律性变化,随着燃料组分的增加,湍动能、湍流切应力及混合层厚度非单调变化,存在极值点。For the purpose of studying the mechanism of reacting flow, two-dimensioned non-equilibrium reacting flow with high temperature was studied on the basis of general N-S equations. On the assumptions that there are seven species and eight reactions, the difference between considering the energy release numerically and not is the purpose of the research. The results show that the energy release decrease the growth of the mixing layer; the growth of the mixing layer decreases first and increases later and the position where the peak of the vorticity thickness locates stands back when the ratio of H2 increases from 0.1 to 0.4 ;it is the energy release and species diffusion which work on the Reynold stress and turbulent energy; vorticity thickness varies with Reynold stress diseiplinarily; all of them vary non-monotonously with extrema.

关 键 词：化学非平衡流 混合层 涡量厚度 直接数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]