Abstract: A device for varying the section of the throat of a turbine nozzle, the nozzle being formed by a plurality of stationary vanes extending radially between outer and inner annular platforms and spaced apart from one another in order to define a throat presenting a minimum flow section. The device comprises an annular element having a coefficient of expansion that is less than that of the platforms of the nozzle, the annular element being secured to the outer platform and being capable of taking up two positions: one position corresponding to no expansion of the platforms, in which the element provides continuity for the profile of the flow passage; and another position corresponding to the platforms having expanded, in which position the element projects into the flow passage so as to reduce its section.

Abstract: Several embodiments of devices for intaking gases from the boundary layer through ducts (3, 4) hollowed out in blades (7) are disclosed. These embodiments are characteristic in that they are suitable for variable setting blades, installed on the stator (1) using pivots (8). The seal is maintained despite the variation in the relative position between the moving pivots (8) through which ducts pass, and the fixed intake header pipe (10).

Abstract: A turbomachine having a longitudinal axis, the turbomachine comprising an annular rotor centered on the longitudinal axis of the turbomachine, an annular stator disposed coaxially around the rotor, at least one ball bearing disposed on the rotor and rotatably supporting said stator, the inside of the rotor defining part of an oil enclosure for cooling and lubricating the balls of the bearing, an electricity generator having a secondary magnetic circuit secured to the stator and a primary magnetic circuit constrained to rotate with the rotor, and a detector device for automatically detecting ferromagnetic particles in the oil enclosure, said detector device being powered electrically by electromagnetic induction.

Abstract: 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.

Abstract: The invention relates to a turbomachine comprising a high-pressure spool, an axial compressor of axis X mounted on a rotor and comprising a casing and at least one rear bearing disposed between the casing and the rotor of said compressor, said turbomachine further comprising an electricity generator coaxial with said spool and including a primary magnetic circuit that is constrained to rotate with said rotor of the compressor and a secondary magnetic circuit that is secured to said casing. In characteristic manner, said electricity generator is disposed upstream from said rear bearing and includes at least a first cooling circuit surrounding said secondary magnetic circuit and extended by a nozzle for lubricating said rear bearing.