Abstract: Based on the Unsteady Reynolds Averaged Navier Stokes URANS) method, a three-dimensional two-phase turbulent combustion numerical software for aeroengine combustor has been developed. The physical and chemical processes taking place in the liquid fuel are simulated completely, including liquid film formation, breakup, evaporation and combustion. LISA and KH-RT are used as the primary and second atomization model respectively, and also the standard evaporation model is used to simulate the evaporation process. Besides, detailed chemical mechanism of kerosene is used for reaction kinetics, and the Unsteady Flamelet/Progress Variable (UFPV) approach in which the unstable combustion characteristics of the flame could be simulated is used as the combustion model. The temperature and species of the flow field and the diameter of fuel droplets in the aeroengine combustor are obtained. At the same time, the Coherent Anti-stokes Raman Scattering (CARS) technology is used to measure the temperature in the primary zone of the aeroengine combustor. Then the temperature of the simulation is compared with that measured by CARS technology, and the calculation error of numerical results is less than 7.3%. The studies have shown that the numerical method in this paper and UFPV approach can simulate the two-phase turbulent combustion process appropriately in the aeroengine combustor.