Double-flow turbojet engine assembly with epicycloidal or planetary gearbox

A double-flow turbojet engine comprising a central shaft coaxially surrounded, on the one hand, by a low-pressure rotor and, on the other hand, 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 the direction of circulation of the flow that passes therethrough when it 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;
• a downstream shaft bearing which rotatably guides the central shaft while being located downstream of the downstream rotor bearing.