The feasibility for an ultrasonic/pressure-swirl hybrid injector to be applied in aero-engine combustors was investigated experimentally.Mass flow characteristics

atomization performance including Sauter mean diameter (SMD) and spray angle were obtained by cool spraying experiments.A single-dome rectangular combustor rig has been constructed with the cross section dimensions 117mm×60mm and series of experiments have been conducted.Results indicate that the mass flow characteristics are in accord with that of a conventional pressure-swirl injector

the SMD falls between 8~12μm without air supply

the SMD falls between 8~12μm under the existence of ultrasonic wave (kerosene is employed as the fuel)

and the spray angle is strongly dependent on the air supply.Good flame stability has been obtained for all the combustion experiments conducted.Under certain situations

combustion efficiency of the combustor rig can achieve 99%.