Of two-phase gas–particle flow in an inlet stage of a turbomachine

Time-dependent two-phase gas–particle flow through a set of two two-dimensional airfoil cascades is studied numerically. The first cascade moves (rotor) and the second one is immovable (stator). This set is a model in some sense of an inlet stage of a turbomachine, for example, an inlet compressor of an aircraft turbojet engine. Flow of the carrier gas is described by the Euler equations. They are solved by a finite-volume method with the use of the Roe scheme and the Harten entropy correction for calculations of the conservative variables fluxes through grid cell faces. On calculating the particles' motion, the particles' twisting in particle–blade collisions, the drag force, the transverse Magnus force, and the damping torque are taken into account. Flow fields of the gas phase and the instant flow patterns of the particle phase are obtained for various particle sizes.