摘要
采用二维轴对称雷诺平均方程和Spalart-Allmaras湍流模型,对一大面积比火箭发动机高空模拟试车台在不同引射方案下发动机启动至稳定运行过程中不同室压下的流场结构进行了数值模拟。空间上采用二阶迎风格式进行耦合求解,时间上采用显式Runge-Kutta方法进行迭代推进。结果表明,采用启动段主动引射、主级段被动引射的方案可满足火箭发动机从启动工况到运行工况的引射要求,但需仔细考察引射器第二喉道收缩比的选择;采用启动段引射器高工况运行、主级段引射器转为低工况运行的全程主动引射,则是综合考虑了系统性能和经济性的较为理想的方案。
The flow-field during ignition in a high altitude test facility for rocket engine of large area-ratio nozzle were investigated by using two-dimensional axial symmetry average Reynolds equations and the Spalart-Allmaras turbulent model.The study used various ejecting schemes and chamber pressures.Two-order upstream scheme and explicit Runge-Kutta algorithm were used to solve these equations.The results show that using positive ejection on starting phase while using passive ejection on operational phase could satisfy the altitude simulation requirement,howevers,the second throat contraction ratio of the ejector should consider carefully.As a tradeoff between performance and cost,it seemed that using positive ejection all through which applies high primary pressure on starting phase and low primary pressure on operational phase was a sound scheme.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第1期126-130,共5页
Journal of Solid Rocket Technology
关键词
火箭发动机
高空模拟试车台
主动引射
被动引射
数值模拟
rocket motor
altitude simulation test facility
positive ejection
passive ejection
numerical simulation
