Flamelet modeling of two-phase kerosene combustion flow fields using a detailed chemical reaction mechanism

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 NO_x 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 537 K, fuel-air ratio 0.0048, atmospheric pressure), but NO emissions are overpredicted in condition 2 (inlet Mach number 0.155, inlet temperature 523 K, fuel-air ratio 0.010, atmospheric pressure).