Parametric Numerical Study of Erosion in Solid Rocket Motor Nozzles

摘要

A validated theoreticalumerical approach for the study of the erosion of graphite material has been used to parametri-cally analyze solid rocket motor thermal protections. The parametric numerical study of nozzle erosion has been carried out considering the role of propellant composition at first. Then the erosion rate dependence on chamber conditions has been analyzed, showing that erosion rate increases with a nearly linear dependence with chamber pressure, whereas it is only marginally affected by equilibrium chamber composition and flame temperature variation with pressure. Finally, the effect of nozzle scale and entrance length has been also investigated permitting to quantify the erosion rate reduction caused by boundary layer thickening.