Abstract: An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.

Abstract: A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.

Abstract: A power transmission system for an aircraft turbine engine including a speed reducer including a ring gear that is able to rotate about an axis X, formed from half-rings having annular flanges clamped together by first fastener. The reducer includes an annular channel for recovering centrifuged oil, having a U-shaped cross section, extending around the flanges, this channel being formed by an axial assembly of at least two parts and forming a fairing for the flanges and the first fastener intended to limit aerodynamic disturbances.

Abstract: A planet carrier (213) for a speed reducer (210) of a turbomachine (1), this planet carrier (213) having a main axis X and comprising: a cage carrier (222) comprising an annular row of axial fingers (282) about the axis X, which comprises first connection elements, and a cage (220) comprising at its periphery housings (280) and second connection elements which are mounted in said housings and which cooperate with the first connection elements to form connections between the cage carrier (222) and the cage (220), which allow at least one degree of freedom, characterised in that the cage (220) comprises two shells (220a, 220b) which are axially assembled to each other, said first or second connection elements comprising broaches (288) oriented radially with respect to said axis X and passing through radial orifices (220a, 220a2, 220b1, 220b2) of said shells (220a, 220b).

Abstract: An oil collector for a mechanical reduction gear of a turbomachine, in particular for an aircraft, the reduction gear including a body having two opposite lateral faces configured to extend in part around planet gears of the reduction gear, the collector further including an internal oil circulation cavity connected firstly to oil inlets located on the faces, and on the other hand to at least one oil outlet, characterised in that at least one of the faces comprises includes columns and rows of several inlets each having a recess with a progressively increasing cross-section, each recess being delimited by walls, at least some of the walls having a hydrodynamic profile.

Abstract: A planet carrier (213) for a speed reducer (210) of a turbomachine (1), this planet carrier (213) having a main axis X and comprising: a cage carrier (222) comprising an annular row of axial fingers (282) about the axis X, which comprises first connection elements, and a cage (220) comprising at its periphery housings (280) and second connection elements which are mounted in said housings and which cooperate with the first connection elements to form connections between the cage carrier (222) and the cage (220), which allow at least one degree of freedom, characterised in that the cage (220) comprises two shells (220a, 220b) which are axially assembled to each other, said first or second connection elements comprising broaches (288) oriented radially with respect to said axis X and passing through radial orifices (220a, 220a2, 220b1, 220b2) of said shells (220a, 220b).

Abstract: An oil collector for a mechanical reduction gear of a turbomachine, in particular for an aircraft, the reduction gear including a body having two opposite lateral faces configured to extend in part around planet gears of the reduction gear, the collector further including an internal oil circulation cavity connected firstly to oil inlets located on the faces, and on the other hand to at least one oil outlet, characterised in that at least one of the faces includes columns and rows of several inlets each having a recess with a progressively increasing cross-section, each recess being delimited by walls, at least some of the walls having a hydrodynamic profile.

Abstract: A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear.

Abstract: An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation.

Abstract: An epicyclic reduction gear, including a planetary gear movable in rotation about an axis of rotation, planet pinions driven by the planetary gear and movable in rotation about axes of planet gears carried by a planet carrier, the planet pinions rolling on a fixed ring gear and the planet carrier being axially positioned laterally relative to the ring gear, the gear formed by the planet pinions and the ring gear being formed to axially eject lubricating oil thereof after use. The planet carrier includes a radial extension positioned facing the gear and forming a mechanism for guiding the oil to a radial end thereof to be ejected from there by centrifugation.

Abstract: A reduction gear includes a sun pinion and planet pinions driven by the sun pinion and rolling on a fixed ring gear. The device includes an oil tank, an oil supply duct and oil routing ducts. The device also includes an oil ejection device at the end of the fixed supply duct, the orientation of which includes a radial component directed away from a common axis of rotation, and a cylindrical device for recovering the oil that can move in rotation about the common axis of rotation. The oil ejection device is linked by at least one duct to a lubrication device for the gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion. This device feeds the ducts which supply the oil to the parts to be lubricated, by virtue of the action of the centrifugal field.

Abstract: A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear.

Abstract: The invention relates to a method of fabricating a structural part comprising a tubular portion from which there projects a structural element made of composite material, the method comprising the steps of: shaping a plane preform comprising a stack of a plurality of superposed fiber plies such that over at least a fraction of the preform that is to form a structural portion, the plies are secured to one another, and over at least another fraction of the preform that is to form a portion for connecting to the tube, the plies are separable so as to form two facing sheets; inserting a tube between the sheets of the connection portion so that the sheets surround the tube at least in part; and bonding the tube to the preform such that the tube forms the tubular portion and the preform forms the structural element of the structural part.

Abstract: The invention relates to a method of fabricating a structural part comprising a tubular portion from which there projects a structural element made of composite material, the method comprising the steps of: shaping a plane preform comprising a stack of a plurality of superposed fiber plies such that over at least a fraction of the preform that is to form a structural portion, the plies are secured to one another, and over at least another fraction of the preform that is to form a portion for connecting to the tube, the plies are separable so as to form two facing sheets; inserting a tube between the sheets of the connection portion so that the sheets surround the tube at least in part; and bonding the tube to the preform such that the tube forms the tubular portion and the preform forms the structural element of the structural part.