Abstract: Helicopter with tip-jet rotor drive comprising at least two rotor blades attached to a central shaft, where each rotor blade comprises means for guiding a fluid from a location close to said central shaft towards a tip of the rotor blade. At the area of said tip there is an outlet arranged so that by each of the rotor blades a jet stream is generated. The helicopter comprises a compressor for releasing compressed air. This compressor is co-axially arranged with respect to said central shaft above the rotor blades. The compressor is connected to the rotor blades to feed compressed air into the rotor blades. A piping system is provided for feeding fuel into the rotor blades. Each rotor blade comprises a combustion zone and means for bringing the fuel and compressed air together so that a combustion process is maintained which produces the jet streams.

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).