A numerical method is presented for predicting steady, three-dimensional, turbulent, liquid spray combusting flows in a gas turbine combustor. The Eulerian conservation equations for gas flow and the Lagrangian conservation equations for discrete fuel liquid droplets were solved. The trajectory computation of the fuel droplets provided the source terms for all the gas-phase equations. A standard k-ε submodel was used for turbulence. The combustion submodel used was a global local equilibrium model, where chemical species (CxHy, O2, CO2, H2O, CO, H2 and N2) approached local thermodynamic equilibrium with a rate determined by a combination of local turbulent mixing and global chemical kinetics times. The numerical methodology for gas-phase calculations involved a staggered finite-volume formulation with a multi-block curvilinear orthogonal coordinate computational grid, and the PISO algorithm. This numerical code was applied to a model gas turbine combustor similar to that of the Allison 570KF currently in use by the Canadian Navy. The combustor was equipped with an advanced airblast fuel nozzle. The calculations included the analysis of the internal passages of the fuel nozzle. Through the numerical study at full-power and low-cruise operating conditions, a better understanding of the physical processes of flow and temperature fields inside the primary zone was obtained. Predicted hot spots corresponded to locations where deterioration of the combustor liner has been observed in practice.

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