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 (SRM) with fin cylinder 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-ε turbulence 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 exhibits a space and time-dependent distribution in radial profiles of the chamber, and the mass addition from circumferential burning surface causes a non-equilibrium axial velocity distribution in the combustion gas field.