Abstract: The mathematical models and numerical methods are presented for computer prediction of aeroengine combustor flows and characteristics. Among these models the droplet turbulent diffusion model, the modified k-∈ turbulence model and the hybrid Arrhenius/EBU model are described. The Eulerian scheme is used to construct conservation equations of both gas phase and droplet phase flows. The self-compiled computer code GEMCHIP programmed by author is provided, which incorporates; SIMPLER and DROPLET algorithms for gas flow and droplet flow predictions, respectively. The block correction technique is adopted to facilitate iteration convergence. The predicted results for three typical twophase flows are given to show the applicability of this method.