摘要
采用基于Favre平均的三维N-S方程和k-ε湍流模型对固体火箭发动机二次喷射推力矢量喷管复杂干扰内流场进行数值模拟。空间上采用三阶精度差分格式进行求解,时间上采用隐式Jacobi点迭代方法进行迭代推进,直至流场收敛。数值模拟得到矢量喷管二次射流的激波系结构,以及复杂的主/次流干扰流动图像。二次喷射流场包含复杂的涡系结构和波系结构,还存在着边界层与激波的相互干扰、自由剪切层、激波、膨胀波和大尺寸分离。数值模拟还表明,高温燃气射流导致喷射孔附近喷管壁面处的温度相当高,需采取相应的热防护措施。
The complex inner flow-field of secondary gas injection for Solid Rocket Motor was numerically investigated by using three-dimensional average Favre equations and the turbulent models. Three-order spatial scheme and Implicit point Jacobi algorithm were used to solve these equations. It gained the structures of shockwave series of secondary gas injection vector nozzle and complex main/ secondary flow image by numerical simulation. The secondary flow field includes complex vortices and shockwave series. It also has interaction by the boundary layer and shockwave, free sheafing layer, shockwave, rarefaction wave and heavy gauge separation. The numerical simulation also indicates that secondary hot gas injection results in high temperature on the surface wall round the injector hole. Corresponding thermal protections should he adopted.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2006年第2期22-25,共4页
Journal of National University of Defense Technology
关键词
二次喷射
矢量控制喷管
数值模拟
secondary injection
vector control nozzle
numerical simulation
