NUMERICAL SIMULATION ON THE EFFECT OF FLOW PATTERN IN SOLID ROCKET MOTOR

In the present work, cold flow simulation has been conducted to evaluate the frequencies and amplitudes of pressure oscillations in solid rocket motor cavity. Axisymmetric model of solid rocket combustor has been modelled and simulated using Fluent. The numerical simulations performed for laminar and turbulent calculation to observe the oscillation frequency and amplitude in combustor. The results for oscillation amplitude have been compared for laminar and turbulent flow and it was observed that a vortex produced from the shear layer has large amplitude with varying the flow rate of working cold fluid. It has been found that the vortex shedding frequency is more oscillating at initial stage and then the oscillation gradually dies out.