Numerical simulation of gas-particle two-phase turbulent flows in the combustion chamber of spinning solid rocket motor

Abstract

Basing on incompressible N-S equations, spinning relative coordinate, body-fitted grid system and SIMPLE method, internal gas-particle turbulent flows in the combustion chamber of Solid Rocket Motor in ground spinning firing test are simulated numerically. The calculated results show that the distribution of tangential vortex possesses the features of Rankme, whose nucleus radius in the forward opening is very small, nucleus spinning rate is very high. The strong gas-particle vortex which seriously affects the thermal protection is the main reason that the forward boss of solid rocket motor was burned through in ground spinning firing test . I . Introduction A spinning acceleration often produce significant internal ballistics change and insulation erosion enhancement of large solid propellant rocket motors[ 11, the circular motion of combustion gas in the chamber caused by spin can make gas flows and heat transfer changed, and these variation and difference can increase rapidly along with the augmentation of spin rate and burning surface-tocenterline distance. For a long time, a series of domestic and foreign solid rocket motors failed in ground spinning firing tests. in china, the perigee solid rocket motor matching with launch vehicle continuously failed twice in ground spinning firing tests because the forward boss was burned through[2], and during apogee solid rocket motors’ research and development, spinning enhancement of the forward opening insulation erosion is a phenomenon seen consistently in ground spinning firing. But up to now, the research on spinning effects of solid rocket * Associate Professor, The 41” Institute of China Aerospace Corporation. * Professor and President, The Fourth Academy of China Aerospace Corporation. x Professor, The 41” Institute of China Aerospace Corporation. Copyright