The ignition experiments were conducted on atmospheric pressure and normal temperature. The experimental research object was a model combustor with multi-swirl air atomizing nozzle. The systematic parameters for study consist of atmospheric pressure

normal temperature

pressure drop of chamber of 1%-6%

ignition energy of 20J and 12J

mass flow ratios of oxygen and air in pilot zone of 0-0.04. The change rule of ignition fuel-air ratio of multi-swirl air atomizing nozzle. The results indicate that when ignition fuel-air ratio is small enough

maximum ignition air flow velocity at combustor inlet increases with the rising oxygen addition mass flow in pilot zone. On the condition of the same ignition energy and pressure drop of chamber

while the mass flow ratio of oxygen and air in pilot zone increases

the ignition fuel-air ratio reduces. When the mass flow ratio of oxygen and air in pilot zone increases to a threshold value (20J-0.01

12J-0.015)

the trend of ignition fuel-air ratio of curve changes. When it continues rising to another threshold value (20J-0.025

12J-0.03)

the ignition fuel-air ratio will not change.