Gas-solid two-phase flow characteristics of SRM propellant with front and rear wings

Based on the Navier-Stokes equation with strong conservation of compressible flow，the particle trajectory model （PTM） and shear stress transfer （SST） k-ω turbulence model were applied to calculate the gas-solid two-phase coupling by using the particle source method （PSIC） in the computational unit，and the three-dimensional two-phase flow field numerical calculation model of a type of solid rocket motor （SRM） with front and rear wings propellant at the ignition was established.The pressure field，velocity field，particle deposition mass concentrations and distributions under single-phase and two-phase conditions were compared and analyzed.The particle deposition mass concentrations in different parts of SRM combustion chamber and nozzle were studied，and the effects of different particle sizes，transvers and axial overloads were considered.The results showed that the solid particles produced by the front and rear wing SRM were mainly concentrated around the front wing，rear wing and the wall of the cylinder.With the increase of particle size，the particle deposition mass concentration on each monitoring surface increased.The transverse overload was positively correlated with the maximum particle deposition on the bearing surface，and the particle distribution on the bearing surface and the non-bearing surface was uneven.With the increase of axial overload，particles accumulated continuously along the overload direction，the escape rate increased，and the deposition decreased.The particle direction deflection caused by overload could affect the particle deposition mass concentration on the wall of combustion chamber and nozzle at the same time，which should be fully considered in the design of SRM insulation layer with front and rear wings charge propellant.