Study of Liquid Breakup Process in Solid Fuel Booster Rocket Chamber

This paper presents a solid fuel booster rocket, both experimental and simulation studies of Al2O3 molten flow. The propulsion of aluminum composite fuel in booster rocket chambers causes severe conditions, such as high temperature and pressure, thus resulting in accumulation into molten droplets. These particles impinge on the walls in the propulsion chamber; thus, particle size and droplet distribution are the major parameters affecting erosive behavior. In this study, we investigated the phenomenon of the breakups in the relationship between gas velocity and molten particle size. The high-temperature, high-speed gas discharged from the solid fuel booster rocket has a large erosion damage on the nozzle, especially the alumina (Al2O3) particles in the gas, playing a major role in the erosion of the nozzle material. The erosion phenomenon is a serious problem since it negatively affects ballistic performance. It was discovered that the number of droplets increases by increasing gas speed in the inlet section. In the throat section of the combustion chamber, regardless of the gas speed, the average droplet size increases due to more breakup phenomena because gas velocity speeds up as the gas passes through the nozzle. However, the average droplet size decreases in the throat section by increasing gas velocity due to flow convection. The number of droplets increases by increasing gas velocity in the throat section. In the exit section of the channel, the average droplet size decreases and increases due to the flow convection.