自由射流超燃冲压发动机燃烧室流场对比计算研究  

Analysis of Comparative Numerical Simulation of Free-jet Scramjet Combustor

作　　者：王元光[1] 徐旭[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2006年第5期825-829,859,共6页Journal of Astronautics

摘　　要：提出一种针对喷射的简化模型,拓展了二维/轴对称NS方程模型的适用范围。通过算例验证,显示出源项加质方法具有良好的质量守恒性。针对文献中的实验进行了对比计算,结果表明,数值模拟与实验点符合得较好,验证了方法的可靠性。采用上述简化模型,针对化学反应过程与流动过程采用了耦合与解耦这两种方法,对放置在自由射流实验台上两种构型的缩比发动机燃烧室段进行了考虑化学反应流场模拟,得到了主要气动参数的分布图。研究了总压耙等测量装置对于流动的影响。计算结果表明,数值模拟所得到的壁面静压值与实验壁面压力符合得较好,并且为合理布置测量仪器提供了一定的参考。Source term among the continuity equations is specially disposed in order to enlarge the scope of two-dimensional/ axisymmetric model especially about the normal injecting issue. To testify the above method, a calculation adopting the above source-addition method has been undertaken to make a comparison with three-dimensional method. Both have obtained a satisfactory result. The flow field in a sketch scramjet engine parts were simulated with the adoption of the above injecting simplified method and 5-species, single step reaction model, obtaining the major aerodynamic parameters and components distribution of the channel. Meanwhile, the influence of to the performance of the total pressure tab to the engine was investigated. The profoundness and robustness of the simplified method is highlighted with the presentation of the above work and it is ready to be applied to the engineering field in terms of calculation precision.

关 键 词：超燃冲压发动机 数值仿真 喷射 燃烧室 化学反应 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]