冲压发动机进气道/燃烧室/尾喷管耦合流场计算  

Inlet/combustor/nozzle coupled flow field calculation for ramjet

作　　者：石喜勤[1] 陈兵[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：《推进技术》2008年第5期557-561,共5页Journal of Propulsion Technology

摘　　要：采用耦合求解的方法进行了冲压发动机进气道/燃烧室/尾喷管流场一体化计算,进气道采用单一气体、变比热比模型,燃烧室和尾喷管采用多组分化学动力学模型,湍流模型为k-g湍流模型。进气道与燃烧室界面通过流量、静压等参数实现耦合。结果表明,通过合理设计参数的传递方式,可以快速实现进气道/燃烧室/尾喷管流场的耦合求解,流场分布合理。An efficient multi-code CFD solver was designed to simulate the integrated flowfields in a ramjet engine in a loosely coupled manner. The muhiblock, multigrid, single-species, turbulence flow solver was used to simulate the flows in the inlet, while a multi-species one to simulate the flows in the combustor and nozzle. The k-g turbulence model was used in the calculations. By means of carefully designed message feedback of mass flow rate, static pressure, etc. , on the inlet-combustor interface, the flowfield of inlet and combustor can be solved efficiently. The turbulent flowfields obtained are reasonable.

关 键 词：进气道 燃烧室 冲压喷气发动机 一体化流场+ 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]