Eulerian approach for unsteady two-phase solid rocket flows with aluminum particles

To increase the specific impulse in a solid rocket motor, aluminum particle s are embedded in the propellant formulation; combustion of these particles causes two-phase and reactive flow features. A model of unsteady compressi ble flow is presented, which includes particle-phase effects. The compositi on of gaseous combustion products of such a solid propellant involves many species and, to reduce the computational time, a reduced description is use d for the gas phase. The particles are assumed to form a continuum; then, t he dispersed phase Is treated by an Eulerian approach. A basic description of aluminum combustion and the current general knowledge are presented. Alu minum combustion is computed hy using Law's model, which assumes a steady v apor-phase diffusion flame; a D-n law giving the vaporized aluminum mass ho w rate is also used. The computations are performed on a simple cylindrical port motor. After some computational verifications, a parametric study of several important quantities of the two-phase how is carried out. The influ ence of particle injection velocity, initial diameter of aluminum particles , and effects of oxidizing species are analyzed.