Two-phase combustion flow fields in a model combustor were numerically simulated using realizable k-ε turbulent model

particles stochastic trajectory model

flamelet models and the detailed chemical reaction mechanism of aviation kerosene.The detailed reaction mechanism was assembled using the combustion mechanism of surrogate fuel (80% decane and 20% 1

2

4-trimethylbenzene by mass fraction) and NOx formation mechanism.The accuracy of flamelet modeling of RP-3 kerosene combustion flow fields (especially for NO emissions) employing the detailed reaction mechanism was investigated by comparison with the experimental data.The result shows that the temperature and CO2 concentrations predicted using the steady flamelet model are in good agreement with the experimental data

but the NO emissions have a bigger deviation.The use of unsteady flamelet model significantly improves the prediction accuracy of NO concentrations and shows good agreement with the experimental data in condition 1 (inlet Mach number 0.16

inlet temperature 537K

fuel-air ratio 0.0048

atmospheric pressure)

but NO emissions are overpredicted in condition 2(inlet Mach number 0.155

inlet temperature 523K

fuel-air ratio 0.010

atmospheric pressure).