Numerical Simulation of the Two-Phase Turbulent Combustion Flow in the Multicomponent Propellant Rocket Engine

Abstract:

The numerical simulation, based on computational fluid dynamics methodology, has been performed to study the two-phase turbulent combustion flow in rocket engine using non-metallized multicomponent propellant. A reduced reaction mechanism is developed for modelling combustion of fuel droplets in the absence of metal. Gas governing equations are two dimensional axisymmetric N-S equations in Eulerian coordinates. The trajectory model is adopted to analyse the droplet-phase including the droplet collision, breakup and evaporation. The gas flow is influenced by the droplets by adding source term to N-S equations. The reliability of the simulation programme is validated by comparing numerical simulation result with engine test data.

• Periodical: Advanced Materials Research (Volumes 452-453)
• Pages: 1334-1338
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.452-453.1334
• Online since: January 2012
• Authors: De Song Liu, Hong Fu Qiang, Xue Li Xia, Guang Wang
• Keywords: Computational Fluid Dynamics (CFD), Non-Metallized Multicomponent Propellant, Reduced Reaction Mechanism, Two-Phase Turbulent Combustion Flow

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