某型固体火箭冲压发动机补燃室内流场仿真  

Simulation of the second combustor internal flowfield for a solid-propellant ducted rocket

作　　者：徐颖军[1] 高峰[1] 王鹏[1] 

机构地区：[1]空军工程大学导弹学院,陕西西安713800

出　　处：《火箭推进》2007年第4期23-27,46,共6页Journal of Rocket Propulsion

摘　　要：基于简单反应的漩涡分裂模型,建立了固体火箭冲压发动机补燃室内的湍流燃烧模型,并在该模型下对某实验发动机进行了三维数值模拟,获得了补燃室内的流场结构。分析了补燃室燃烧效率的变化和发动机的性能,并研究了补燃室设计参数包括进气道出口设计参数对燃烧效率的影响。通过计算与分析,为固体火箭冲压发动机补燃室设计提供了一些建议。A simple reacting flow model in solid-propellant ducted rocket combustor based on Eddy Break-Up model is established. The model is used to simulate the three-dimensional combustion flowfields in an experimental motor. Flowfield of structure was obtained, variation and perfor- mance of the combustion efficiency were analyzed. Some factors that affect the combustion efficiency were discussed in the paper, including air intake. Some significative results are offered by computation and analysis.

关 键 词：固体火箭冲压发动机 燃烧模型 数值模拟 燃烧效率 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]