Dual-flow turbojet engine arrangement with epicyclic or planetary reduction gear

A dual-flow turbojet engine comprising a central shaft surrounded by a high-pressure spool, coaxial and rotatably independent, said turbojet engine including from upstream to downstream according to the direction of circulation of flow that passes therethrough when said turbojet engine is operating:

• a fan driven by the central shaft;
• a high-pressure compressor and a high-pressure turbine belonging to the high-pressure spool;
• an inter-turbine casing;
• a low-pressure turbine;
• an exhaust casing;
• said turbojet engine further including:
• a low-pressure rotor which surrounds the central shaft and which comprises the low-pressure turbine;
• a rotor upstream journal carried by the inter-turbine casing and which rotatably guides the low-pressure rotor while being located downstream of the high-pressure compressor;
• a rotor downstream journal carried by the exhaust casing, and which rotatably guides the low-pressure rotor;
• a reduction gear through which the low-pressure rotor drives the central shaft, said reduction gear being located downstream of the rotor downstream journal;
• a shaft downstream journal which rotatably guides the central shaft while being located downstream of the rotor downstream journal.