Aimed at the low pollution emission requirements of gas turbines

the increase of the main combustion hole diameter and the improvement of the mixing hole advance are carried out for one type of conventional aero-engine combustion chamber. The test is conducted using 0# diesel fuel as the fuel

and the research on ignition

flameout characteristics and exit temperature fields is performed. The results show that the main combustion hole diameter increases from 9 mm to 11 mm

the intake air flow increases from 26.2% to 39.1% and the excess air coefficient of main combustion zone increases from 0.95 to 1.10. The oil-gas ratio of lean ignition at normal temperature and pressure changes from 0.025 50~0.032 44 to 0.024 46~0.036 25

but better than the low pollution combustion chamber design standards value of 0.05. The distribution coefficient of outlet temperature is reduced from 0.226 4 to 0.207 1

which improves the quality of the temperature field. The emission indexes of CO and UHC increase

but the emission index of NO_x decreases from 2.26 g/kg to 1.34 g/kg

by 40.7%. The combustion efficiency slightly decreases from 0.984 2 to 0.982 3. After advancing the mixing hole

all indexes are not improved. This results provide a reference for the design of low pollution gas turbines and the modification of conventional combustion chambers.