Jet engine

A jet engine, comprising:

• at least one fan including adjustable blades for compressing an intake air mass flow;
• a common rotor shaft;
• a gear unit operatively connecting the common rotor shaft to the at least one fan;
• at least one compressor unit arranged downstream of the fan, the at least one compressor unit including at least one compressor;
• a bypass flow nozzle coaxially arranged with the compressor unit such that the compressed intake air mass flow is divided up into an inner flow entering the compressor unit and a bypass flow expanding in the bypass flow nozzle, wherein the ratio of bypass and inner flow is high in order to achieve a substantial contribution to the total thrust of the engine by the bypass flow;
• an annular combustion chamber arranged downstream of the compressor unit;
• a turbine arranged downstream of the combustion chamber;
• a second annular combustion chamber arranged downstream of the turbine;
• and
• a second turbine arranged downstream of this second combustion chamber;
• wherein the second combustion chamber is a self-igniting combustion chamber including vortex-generating elements, and wherein the at least one compressor, the first turbine, and the second turbine are arranged on the common rotor shaft and operatively connected with the fan by the gear unit, such that the fan is driven by the excess shaft output of the common rotor shaft.