Double-flow turbojet engine assembly with epicycloidal or planetary gearbox

A double-flow turbojet engine comprising:

• a central shaft coaxially surrounded by a low-pressure rotor and by a high-pressure spool, coaxial with each other, the high-pressure spool being rotatably independent of the low-pressure rotor and of the central shaft, said turbojet engine including from upstream to downstream according to a direction of circulation of a flow that passes therethrough when the turbojet engine is operating:
• a fan driven by the central shaft;
• a low-pressure compressor carried by the low-pressure rotor;
• an inter-compressor casing;
• a high-pressure compressor and a high-pressure turbine belonging to the high-pressure spool;
• an inter-turbine casing;
• a low-pressure turbine carried by the low-pressure rotor;
• an exhaust casing;
• said turbojet engine further including:
• an upstream rotor bearing carried by the inter-compressor casing and which rotatably guides the low-pressure rotor;
• a downstream rotor bearing carried by the exhaust casing, and which rotatably guides the low-pressure rotor;
• a gearbox through which the low-pressure rotor drives the central shaft, said gearbox being located downstream of the downstream rotor bearing;
• and
• a downstream central shaft bearing which rotatably guides the central shaft while being located downstream of the downstream rotor bearing, the downstream central shaft bearing being an inter-shaft bearing which surrounds the central shaft and which is surrounded by the low-pressure rotor.