超燃冲压发动机缩比燃烧室流场数值模拟  

Numerical Simulation of the Flowfield in a Scaled down 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：《航空动力学报》2006年第1期56-60,共5页Journal of Aerospace Power

基　　金：国家"863"基金资助

摘　　要：为了采用二维N-S方程来研究带有垂直喷射的三维问题,即拓展二维模型的适用范围,提出了一种针对喷射的简化模型,即采用源项加质来近似模拟喷射的质量添加。为了验证这种简化的可行性,针对文献中的实验条件进行了对比计算。结果表明,数值模拟与实验点符合得较好。运用以上简化模型,对放置在自由射流实验台上的缩比超燃冲压发动机燃烧室流场,采用五组元单步反应模型进行了数值模拟,得到了各主要气动参数及组分质量分数的分布,表明,根据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。A new concept was raised and adopted to enlarge the scope of two-dimensional model particularly in dealing with three dimensional normal injection cases. Meanwhile, the method has a very good performance in terms of time consuming. The new idea was realized through special disposal with the continuity equations,i, e. , mass flow are added in the source term of the continuity equation. To prove the robustness of this simplified method, in accordance with the test condition published in the literature, calculation was carried out. Calculating results compared with three dimensional programs prove to be satisfactory. A model scramjet combustor tested on the free-jet scram jet test facility was demonstrated and undergone numerical calculation with the two-dimensional program adopted theabove injecting simplification. To simulate the chemical reaction process in thescramjet tunnel,a 5-specise,single step reaction model was introduced. The major aerodynamic parameters and components mass fraction distribution within the model combustor channel were presented. This makes it easy to observe and analyze the flow field. Comparisons of wall pressure between the numerical and experimental results prove the adequate accuracy of the calculation model.

关 键 词：航空、航天推进系统 超燃冲压发动机 源项 化学反应 燃烧室 数值仿真 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]