Three-Dimensional Model of Spray Combustion in Gas Turbine Combustors

A mathematical model of the three-dimensional two-phase reacting flows in gas turbine combustors has been developed which takes into account the mass, momentum and energy coupling between the phases. The fundamental equations of motion of the droplets are solved numerically in a Lagrangian frame of reference using a finite difference solution of the governing equations of the gas. Well known relations are used to model the heat and mass transfer processes and the initial droplet heat-up is allowed for. The entire fuel spray is constructed using a finite number of size ranges obeying a two parameter droplet size distribution. The technique permits the rational selection or specification of fuel nozzle design. 26 refs.