Patent ID: 7372175

Claim:
A two-spool bypass turbojet comprising a low-pressure spool having, at its rear end, a low-pressure turbine provided with a low-pressure rotor, said turbojet including a support structure connected to a casing and to a rear bearing on which said rotor is mounted, said rear bearing being situated in an enclosure having means for feeding said bearing with liquid lubricant, said enclosure being put to atmospheric pressure by an air feed pipe coaxial with said rotor and connected to said enclosure via link means enabling gas communication between said enclosure and said air feed pipe while guaranteeing sealing against liquid lubricant from said enclosure, the turbojet further comprising an electricity generator coaxial with said spool and situated outside said enclosure, said generator being disposed and being connected to the rear end of said low-pressure rotor which extends downstream from said link means, said link means being secured to said rotor and including guide means for guiding the liquid lubricant between said feed means and said bearing, wherein said guide means comprise a guide wall extending axially, at least the face of said guide wall that faces towards the axis of the turbojet being inclined radially outwards on going from said feed means towards said bearing.