Solid Rocket Ramjet Ignition Numerical Study Of Indoor Combustion Process

In solid ducted rocket, the fuel-rich gas from generator includes metallic particles, which have a very important effect on the flow and combustion in the secondary combustion chamber. This paper discusses the numerical model of two-phase flow and combustion in the secondary combustion chamber based on the combustion of aluminum and magnesium, and simulates the flow and combustion by CFD. It is shown that in the secondary combustion chamber, there are three eddies in the complicated flow field, and the temperature gradient is large. When the gas in the fuel-rich gas gets into the secondary firebox, it burns immediately, and much heat which makes aluminum combust is released. At the anterior part of secondary combustion chamber, much metallic oxide concentrates around axis. Then it diffuses to the area near wall, so the metallic oxide is homogeneous in radial direction at the mid and end of secondary combustion chamber. It is a fact that the combustion of aluminum will be easier when there is more magnesium, and the combustion efficiency of aluminum raises. If diameter of aluminum increases the whole surface area of aluminum drops decreases, so the evaporation slower. And because the drops concentrate around axis, the mixing between aluminum drops and air weaken. As a result, the combustion efficiency of aluminum descents. Increasing the air-fuel ratio, the mixing between air and fuel enhances. The combustion of aluminum accelerates, and the combustion efficiency rises.