Flame Flow Analysis for HVOF/HVAF System byTwo-Dimension Computational Fluid Dynamics Method

摘要

Based on the principle of the liquid-fueled rocket engine, acombustion model is proposed for the HVOF/HVAF system.The combustion gas components and temperature for differentmixture fractions were analyzed. At lower oxygen contentcondition (under-stoichiometry), the combustion temperatureis lower and the solid carbon content is higher. The wholefluent flow mode was proposed for the supersonic spray,which consists of the gas combustion, the accelerating process,the cooling process and the decelerating process in theatmosphere. The velocity and temperature distributions werecalculated according to this model; the results fitted well withexperiments. The combustion gas parameter distributions arealmost identical in the barrel, but differ significantly in theatmosphere. For HVOF system, the under-expanded gas willexpand in the atmosphere, while HVAF system exhibits anopposite behavior. At the gun exit, the combustion gas reachessupersonic velocities both for the HVOF and HVAF condition.