固体火箭发动机燃烧室三维流动数值计算

采用k-ε双方程湍流模型,以SIMPLE计算程式求解翼柱型装药固体火箭发动机燃烧室内三维非定常不可压流N-S方程.在建立翼柱型装药简化模型的基础上采用边界标志法来表达燃面推移,采用从二维到三维的初场给定方法结合多重网格法求出了多个时间步的非稳态流场结构.计算结果表明燃烧室内旋涡运动呈现一定的空间与时间分布,周向加质导致燃气通道横断面上轴向速度分布的极不均衡. 

Numerical Calculation of 3-D Flow in SRM Chamber

The 3-D unsteady turbulent flow is simulated in the chamber of solid propellant rocket motor with finocyl type grains. It is based on numerical solution of the 3-D time-dependent ensemble-averaged Navier-Stokes equations, incompressible fluid and a high Reynolds number k-εturbulence model. The SIMPLE calculation procedure is used to solve the discrete equations. Some special treatment has been applied to initial flow field. The computation results indicate that vortex motion act a space and time-dependent distribution in radial profiles of the chamber, and the mass addition from circumferential burning surface caused a non-equilibrium axial velocity distribution in the combustion gas field.