加扰流环双组元LAE的流场数值仿真  

Studies on Flowfield Numerical Simulation of Bipropellant ApogeeLiquid Rocket Engine with Turbulent Flow Annulus

作　　者：银仁亮[1] 周进[1] 张中光 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073 [2]上海航天动力机械研究所,上海200233

出　　处：《上海航天》2004年第6期24-27,共4页Aerospace Shanghai

摘　　要：采用交错网格系统SIMPLE算法和二维两相流场燃烧模型,对有不同形状(矩形、圆弧三角形及其混合结构)和位置扰流环的某双组元液体远地点发动机(LAE)流场进行了数值仿真计算。结果表明,扰流环对提高燃烧效率作用明显。环的位置应适中(不能过于靠近头部和喷管出口处),其高度越大,燃烧效率越高。另外,矩形环的压力损失大于三角形环。The flowfield numerical simulation of some bipropellant apogee liquid rocket engine with different configuration (rectangular, triangular and mixture) and position of turbulent flow annulus was calculated by using SIMPLE algorithm of alternate grid system and two-dimension flowfield combustion model in this paper. The results showed that the effect of turbulent flow annulus to improve combustion efficiency was obvious. The position of annulus should be proper not too near the head or nozzle exit. The higher of the annulus, the greater of combustion efficiency. Moreover, the pressure lost of rectangular annulus is bigger than that of triangular one.

关 键 词：液体远地点发动机 数值仿真 扰流环形状 扰流环位置 燃烧室性能 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]