Abstract: The 3-D unsteady turbulent flow was simulated in the chamber of solid propellant rocket motor with finocyl type grain It was based on numerical solution of the 3-D time-dependent ensemble-averaged Navier-Stokes equations of incompressible fluid and a“high Reynolds number” k-ε turbulence model The SIMPLE calculation procedure and TDMA was used to solve the discrete equations The k-ε turbulence model was modified with wall function in the vicinity of the shell and burning surface Some special treatments were applied to initial flow field The computed results show:in radial profiles of the chamber, vortex motion act a space and time-dependent distribution,the mass addition from circumferential burning surface cause a non-equilibrium axial velocity distribution in the combustion gas field

Key words: Solid propellent rocket engine;Combustion chamber;Three dimensional flow;Navier-Stokes equation;Multi-grid;Numerical simulation

摘要： 采用k ε双方程湍流模型 ,以SIMPLE计算程式结合TDMA法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。

关键词: 固体推进剂火箭发动机;燃烧室;三维流;纳维尔斯托克斯方程;多重网格法;数值仿真