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.
出处
《上海航天》
2004年第6期24-27,共4页
Aerospace Shanghai
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
Liquid apogee engine
Numerical simulation
Turbulent flow annulus shape
Turbulent flow annulus position
Combustion chamber performance
