Abstract: Combustor (50) for use in a turbine (100). The combustor (50) comprising a multiple fuel atomizers (10) which has a gas inlet for feeding gaseous fuel as first combustible into an inlet zone of the atomizer, an air inlet for feeding compressed air into the inlet zone, and an orifice for injecting a liquid fuel as second combustible into the inlet zone. The atomizer comprises a diffuser for emitting a gas stream at an exit side. The atomizer (10) is arranged with respect to a combustion chamber of the combustor (50) so that the exit side of the diffuser points in a tangential direction relative to the combustion chamber. The combustor (50) comprises an outlet duct (51) for discharging an exhaust gas produced by a combustion process of the gas stream inside the combustion chamber. The exhaust gas drives a turbine (63).