N-decane was chosen as the surrogate fuel of RP-3 aviation kerosene

and a reduced mechanism (36 species and 62 steps) was established. A Bunsen burner with premixed pre-evaporation combustion was designed to study the combustion flame of RP-3 aviation kerosene. And two verified kerosene simplified mechanisms (23 steps and 38 steps respectively) and the 62 steps mechanism were used by numerical simulation. The numerical results were compared with the experimental data. Results show that

the distributions of temperature and volume fraction of CO2 first increase and then decrease in the axial direction

and the temperature reaches the maximum at axial distance from nozzle of 0.020m.While the volume fraction of O2 first decreases and then increases

the volume fraction reaches the minimum at axial distance from nozzle of 0.025m. Compared with the 38 steps and 23 steps reduced mechanisms

the distributions of temperature and volume fraction of O2 are in good agreement with the experiment data when 62 steps reduced mechanism is applied. At the same time

the numerical results with 62 steps reduced mechanism can also well simulate the volume fraction of CO2

but the numerical results of 23 steps and 38 steps can only predict the change trend of the experimental results. Therefore

n-decane can be used as the surrogate fuel of RP-3 aviation kerosene and the 62 steps reduced mechanism can accurately predict the combustion characteristics of RP-3 aviation kerosene.