Turbo aircraft engine with internal mixer

The present invention relates to a turbo aircraft engine with at least one compressor unit, a combustion unit, a turbine unit and a mixing unit, escaping hot exhaust gases are mixed with secondary air in from the turbine unit via a mixer nozzle. The present turbo aircraft engine is characterized in that the mixer nozzle is formed as a chevron nozzle from which the hot gases emerge at subsonic speed. The present turbo aircraft engine comprises a mixing unit with high mixing efficiency and low weight.