This paper presents the numerical models for the analysis of combustor fuel spray, characteristics, invarious injection conditions in a can type of combustor with a double stage radial swirler. Spray consists of twofundamental and consecutive steps, means the primary breakup and the secondary breakup. The primary breakupis modeled by Linearized Instability Sheet Atomization (LISA) which are mostly used in a pressure swirlatomizers. Secondary breakup is modeled by Taylor analogy breakup model (TAB). The trajectory and velocityof generated fuel droplets is determined by Lagrangian Particle Tracking. Characteristics of jet breakup, dependson a variety of factors such as turbulence, injection pressure drop, velocity profiles, nozzle geometry, and thephysical state of the liquid fuel. In this paper Jet-A aviation fuel (kerosene), modeled as a two-componentsurrogate fuel (by mass 60 % C10H22 and 40 % C9H12). The standard k–e model with the enhanced walltreatment and the Euler-Lagrange method were employed for the simulation of the turbulence and spray. Allresults of the simulation in this paper are analyzing in 3 various injection conditions and one of these cases waschosen and implemented in a real annular combustion chamber of a gas turbine. A PDF Flamelet model wasemployed to simulate combustion process.