Abstract
Aluminized propellants are frequently used in solid rocket motors (SRMs) to increase specific impulse. However, as the propellant combusts, the aluminum is oxidized into aluminum oxide (Al2O3), it agglomerates into molten droplets that attach to the outside wall of the rocket nozzle. This phenomenon negatively impacts ballistics performance because the droplets remain attached to the inner wall of propulsion chambers. This buildup of particles tends to erode the wall, decreasing the performance and sustainability of the rocket. This study presents both experimental and computational fluid dynamics (CFD) to investigate the relationship between gas velocity and molten particle size for the vertically arrayed combustion chamber. Also, the Weber number and the Froude number are monitored to explain the breakup phenomenon and the condition of alumina flow in the whole testing channel. This study focused mainly on the vertical arrangement of the propulsion chamber with the cold experimental and simulation investigating the role of the liquid water in addition to a comparison with the horizontal chamber case. Unlike the horizontal setup, a greater number of droplets with smaller average droplet diameter present in the vertical setup; however, Froude number follows the same trend as for the horizontal C-D nozzle setup.
