Turbofan jet engine with low pressure shaft passing outside of core engine

An aircraft turbofan engine comprising:

• only one core engine, including a high-pressure compressor, a combustion chamber and a high-pressure turbine which are coupled to one another via a high-pressure shaft,
• a primary flow duct for flowing air into the core engine,
• a secondary flow duct for flowing air outside the core engine,
• at least one fan for supplying air into both the primary flow duct and the secondary flow duct, wherein the secondary flow duct and the core engine have a same flow direction, the at least one fan driving a major proportion of an air mass ingested by the aircraft turbofan engine into the secondary flow duct past the core engine for propulsion of the aircraft turbofan engine,
• at least one low-pressure turbine arranged behind the core engine, and
• at least one low-pressure shaft coupling the at least one fan to the at least one low-pressure turbine,
• wherein none of the at least one low-pressure shaft of the turbofan engine passes through the core engine;
• wherein each one of the at least one low-pressure shaft runs substantially parallel to the high-pressure shaft, such that a deviation from parallel between each one of the at least one low-pressure shaft and the high-pressure shaft is no greater than 5°;
• wherein the at least one fan comprises at least two fans;
• wherein the at least one low-pressure turbine comprises at least two low-pressure turbines;
• and
• wherein the at least one low-pressure shaft comprises at least two low-pressure shafts, with each of the least two fans being respectively coupled to one of the at least two low-pressure turbines by one of the at least two low-pressure shafts.