| In order to explore the influences of inlet air temperature, pressure and fuel-air ratio on the ignition and flameout boundar?
ies, temperature rise, combustion efficiency and main emissions mole fraction, tests were conducted on the ignition and flameout character?
istics, outlet temperature distribution and main emissions mole fraction of an aeroengine combustor under different operating conditions.
The structure of flow field, the distributions of temperature field, intermediate species and main emissions mole fraction fields in the flame
tube were simulated by using the reduced reaction mechanism of n-decane and the single step reaction mechanism of C 12 H 23 respectively,
and the computational results were compared with the corresponding experimental data. The results show that with the increase of inlet air
temperature, pressure and fuel-air ratio of the combustor, combustion efficiency, temperature rise, outlet average temperature and NOX
mole fraction gradually increase, while UHC and CO mole fraction gradually decrease. Compared with the single step reaction mechanism
of C 12 H 23 , when adopting the reduced reaction mechanism of n-decane, the distributions of flow field and temperature field in the flame
tube are more reasonable, the distributions of temperature field and main emissions mole fraction at the flame tube outlet are closer to the
experimental data, and the calculation accuracy is greatly improved. |