Abstract
A ducted rocket is a ramjet propulsion system, and a typical ducted rocket uses two combustion chambers. Metal particles are occasionally added to the fuel in order to increase thrust. For the complete combustion of metal particles in the second combustion chamber, it is important to understand the mixing characteristics in the chamber’s recirculation zone. In this study, the effects of the mixing chamber geometry and velocity ratio on the flow in the chamber were investigated using particle image velocimetry. A total of four mixing chamber geometries and three velocity ratios were considered, and the effects of the size of the metal fuel-simulating particles were also investigated. The experimental results showed that the size of the recirculation zone and the fuel penetration depth were strongly affected by the location of the axial inlet and the size of the particles. As particle size increased, the size of the recirculation zone increased due to the increased momentum of the axial flow. The effects of chamber geometry and velocity ratio on the flow were significant near the mixing region. However, the effects diminished downstream.
Published Version
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