Simulation of particulate flows in combustion chambers of solid rocket motors with multiscale model

The study addresses how numerical simulation has been developed and applied to the investigation of intra-chamber processes in solid rocket motors (SRMs). The existence of non-spherical condensed phase particles is a feature of internal flows in the SRM channels and nozzles. The simultaneous occurrence of events on several temporal and spatial scales that characterize the production of agglomeration particles, their burning, and their transport in the flow of combustion products in internal channels and nozzles are mathematical difficulties in this field. A multi-scale strategy that integrates models expressing the system’s status at the micro-, meso- and macro-sizes is one way to solve these issues. A summary of models with different levels of depth and complexity is provided. In order to simulate two-phase flows with metal-oxide agglomerates generated in the propellant channel and simulating drops of molten metal with oxide particles attached to their surface, the design of multi-scale models is taken into consideration. The developed approach capabilities are exhibited through the computation of combustion product flows in propulsion system nozzles and channels that contain agglomeration particles.