| 摘要 |
The invention relates to a two-spool bypass turbojet comprising a low-pressure spool having a rear portion carrying 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 in which said rotor is mounted, the bearing being situated in an enclosure including liquid lubricant feed means, said enclosure being put to atmospheric pressure via an air feed pipe connected to said enclosure via link means. In characteristic manner, said turbojet further comprises an electricity generator connected to the rear end of said low-pressure that extends downstream from said link means, which link means are secured to said rotor and include means for guiding the liquid lubricant from said feed means to said bearing.
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