激波诱燃冲压发动机燃料喷注混合增强机理与预着火抑制研究

项目名称： 激波诱燃冲压发动机燃料喷注混合增强机理与预着火抑制研究

项目编号： No.11272349

项目类型： 面上项目

立项/批准年度： 2013

项目学科： 数理科学和化学

项目作者： 罗世彬

作者单位： 中南大学

项目金额： 82万元

中文摘要： 本项目采用理论分析、数值模拟和实验研究等手段对激波诱燃冲压发动机前体/进气道的燃料/空气混合过程和预着火抑制开展机理研究。综合运用高速摄影/激光纹影、PLIF、PIV、NPLS、TDLAS、质谱仪等设备，结合高精度混合RANS/LES数值模拟方法，研究前体/进气道内混合/燃烧流场的精细时空结构，探索高超声速气流中激波、旋涡增强燃料/空气混合的机理。深入研究不同来流条件、进气道构型、喷注方式在不同喷射条件下的燃料/空气混合效率和总压损失的影响规律；通过冷却进气道壁面、壁面喷注冷却氮气和优化喷注方案等措施，主动控制边界层的温度和燃料分布，探索边界层内预混气体预着火边界，揭示预着火抑制的本质；综合混合增强和预着火抑制规律，给出优化的前体/进气道/喷注器一体化设计方案。该项目研究将加深对激波诱燃冲压发动机流动混合与燃烧过程的认识，为激波诱燃冲压发动机关键技术研究提供基础支撑。

中文关键词： 悬臂斜坡喷注器；燃料/空气预混；混合增强；混合性能参数；高超声速

英文摘要： The fuel/air mixing process and the premature ignition suppression in the forebody/inlet of the shock-induced combustion ramjet (shcramjet) engine are investigated by combination of experiments, theoretical analysis and numerical simulations. High-speed flame luminosity imaging/laser schlieren, PLIF, PIV, NPLS, TDLAS and mass spectrograph, combined with High-resolution hybrid RANS/LES numerical simulation, are adopted to study detailed temporal-spatial structure of the mixing and combustion flow in the forebody/inlet, in which the mechanism of shock and votex enhancing the fuel/air mixing in hypersonic flow are explored. The rules of mixing efficiency and total pressure lose of different injection modes under different injection conditions are investigated. The injection modes includes inflow condition, inlet configuration and injector type. The limit to control premature ignition in boundary layer is investigated by using cooling inlet wall, N2 injected from inlet wall, and other optimized injection scheme. Thus the essence of the premature ignition suppression is given. Finally, the optimal integral design concept of forebody/inlet/injector is promoted. The project will be helpful for understanding the mixing and combustion process of shcramjet and provides technology basis of key research on shcramjet.

英文关键词： Cantilevered ramp injector；fuel/aix premixed；mixing enhancement；mixing performance parameter；hypersonic