Turbogenerator for hybrid electric aeronautical propulsion

A turbogenerator for hybrid electric aeronautical propulsion comprising:

• a heat engine
• an electrical generator mechanically coupled to the heat engine and including a rotor and a stator,
• the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings,
• the stator including a magnetic stator yoke, the rotor being sectorized in the axial direction and comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors,
• wherein at least two stationary sectors, including one covering axially at least two movable annular rings, are further arranged angularly so as not to coincide with one another and thus deliver at least two distinct and independent voltage levels.