Effect of Mach number and Shock Dynamics for FourDifferent Particle Types at Four Different Pressure Ratiosin Two-Phase Flow in Convergent-Divergent Nozzles

This study Effect of Mach number and Shock Dynamics for Different ParticleTypes at Four Different Pressure Ratios in Convergent-Divergent Nozzles inTwo-Phase Flow the flow behavior inside the nozzle is considered as a twowaycoupled flow. The governing equations used in this research are thecompressible Navier-Stokes equations and the axisymmetric geometry withviscous and steady flow. Since the volume fraction of the secondary phase inthe continuous phase is less than ۱۰%, the Eulerian-Lagrangian method isemployed. The numerical simulation is conducted for single-phase and twophaseflow conditions. The pressure ratio in the nozzle is defined as thedivision of the nozzle inlet pressure by the atmospheric pressure. The effectsof pressure difference on the shock created in the nozzle for four types ofnanoparticles (Cu, Al۲O۳, SiO۲, CuO) at four pressure ratios (۵.۳, ۶.۷, ۸.۴,۱۳.۴) and for a particle mass flow rate of ۲.۰ kg/s are investigated. An increasein the pressure ratio in the nozzle leads to flow separation. The flow separationpushes the shock wave towards the throat.