Vaporization Behaviour of Fuel Droplets in a Gas Turbine Combustor

A model is developed for the description of the phase change process of evaporation, of droplet particles in a gas turbine engine combustor. The fuel spray is divided into three regimes, the sheet portion, the break up portion and the droplet portion. The sheet region is important in determining the spray cone angle and the initial conditions for the calculation of droplet trajectories. Both convective and radiation mode of heat transfer to the fuel spray due to flame and liner walls are considered. The description of the fuel spray involves, the effects of variable thermophysical properties and of transient heating. In the radiative heat transfer analysis combustion gases comprising both particulates and molecular gases such as CO2, H2O and soot particles which emit, absorb and scatter radiant energy and the full Mie scattering theory is used. The model is applied on a T53-L-13B turboshaft engine used for AB-205 (UH1H) helicopter.