Abstract: Equipment for disassembling a planet carrier is provided. The planet carrier includes a cage, a cage carrier, and a connection shaft. The cage includes an inner bridge and an outer bridge. The cage carrier include a finger bar to be inserted between the inner bridge and the outer bridge. The connection shaft is housed in through-holes formed in the bridges and in the finger bar, such as to retain the cage on the cage carrier. The equipment includes a jack and a support. The jack includes a body and a piston, the piston being designed to apply a force to the connection shaft. The support is designed to bear on the finger bar when the piston applies a force to the connection shaft.

Abstract: The invention relates to a method for assembling (S) a planet carrier (16), comprising the following steps: separately producing (S1) the cage (20) and the cage carrier (30), providing a machining allowance at one element from among the through-holes (23, 25) in at least one upright (21) of the cage (20) or the through-hole (32) in a finger bar (31) of the cage carrier (30), and/or at one element from among a bearing seat (26) or a rolling bearing seat (41, 42); assembling (S2) the cage (20) and the cage carrier (30) and securing (S3) same to produce a one-piece assembly; determining (S4) the position of a reference axis (Y1, Y2) linked to the cage (20), to the cage carrier (30) and/or to the shaft (40); and, taking account of the position of the reference axis (Y1, Y2), machining (S5) all or part of the machining allowances.

Abstract: The invention relates to a self-aligning roller bearing, comprising a rotary outer ring exhibiting a spherical raceway, the bearing comprising first and second annular rows of rollers respectively associated with first and second rotary cages that hold the rollers in place. According to the invention, the first cage has an exterior surface equipped with at least one deflector for discharging lubricant towards a first side of the bearing, in a first axial direction extending from the second cage towards the first cage, this deflector extending, in a second axial direction that is the opposite of the first direction, beyond the rollers associated with the first cage and also beyond the first cage so as to cover part of the second cage.

Abstract: A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.

Abstract: The present disclosure relates to the lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, for example of an aircraft. The planet-carrier includes a cage defining an internal housing configured to receive a central sun gear with an axis of rotation X, and an annular row of planet gears arranged around the sun gear. The cage includes two annular walls that are radial with respect to the axis X, and connected to one another at their outer periphery by a cylindrical wall. At least one of the radial walls has orifices for mounting the planet gears, and the cylindrical wall has through-holes for the passage of the gearings of the planet gears so that they may engage with a gearing of the ring gear, which is configured to extend around the planet gears and the cage.

Abstract: A sun gear for a mechanical reduction gear of a turbine engine, in particular for aircraft, the sun gear having a general annular shape about an axis and comprising at the outer periphery thereof, a meshing gearing with planet gears of the reduction gear, and at the inner periphery thereof, splines for coupling with an input shaft of the reduction gear, characterised in that the sun gear has a staged profile in axial cross-section, and preferably comprises an annular recess opening radially inwards and configured to receive at least one oil jet.

Abstract: A speed reducer includes two intermediate lines for a turboprop engine, the reducer including: an input line including an input shaft bearing an input gear wheel, a first intermediate line including a first intermediate shaft bearing a first intermediate gear wheel, a second intermediate line including a second intermediate shaft bearing a second intermediate gear wheel, a spring held by a frame, the spring surrounding a longitudinal portion of the input shaft in order to allow a movement of the input gear wheel towards an equilibrium position corresponding to an equal distribution of the transmission of the power coming from the input shaft to the first intermediate shaft of the first intermediate line and the second intermediate shaft of the second intermediate line.

Abstract: In an aeroengine comprising a gas turbine engine driving a propeller via a reduction gearbox, the propeller comprising a plurality of blades, each provided with one or more electrical deicer elements and being set into rotation by a propeller-carrying shaft passing through the gearbox, the propeller-carrying shaft having a fastener flange for fastening to the propeller, provision is made, in order to deliver the electrical power needed for powering said electrical deicer elements, for the aeroengine to include a rotary three-phase transformer set into rotation by the propeller-carrying shaft and comprising firstly a rotor mounted inside the propeller-carrying shaft and angularly secured thereto, and secondly a stator secured to a stationary portion of the aeroengine, the rotary three-phase transformer being arranged behind the propeller fastener flange.

Abstract: A planetary reduction gear ring gear for a turbine engine, in particular of an aircraft, the ring gear extending about an axis (X) and including first and second coaxial annular elements and respectively two inner annular teeth oriented differently. The first and second annular elements include respectively first and second radially external annular flanges to secure the first and second elements to one another, the teeth of the first and second annular elements being axially spaced from one another and from a joint plane (P) of the first and second flanges, and defining between them an annular space externally delimited by two annular rims supporting respectively the flanges. At least one of the flanges includes joint plane notches that are substantially radial for the oil to pass through by centrifugation. The ring gear further includes an annular row of oil-retention walls protruding from the rims in the space.

Abstract: A ring gear (114) for an epicyclic or planetary reduction gear (110) of a turbomachine, in particular of an aircraft, said ring gear extending about an axis and comprising first and second coaxial annular elements (114a, 114b) and comprising, respectively, two inner annular toothing sets (150) of different orientation, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges (114ab, 114bb) for attaching said first and second elements to each other, characterised in that one of said first and second flanges comprises, at its outer periphery, a cylindrical centring rim (164) configured to cooperate with the outer periphery of the other of said first and second flanges.

Abstract: An assembly for an epicyclic reduction gearset, including a satellite carrier, satellites, and at least one satellite bearing including a central axis linked to the satellite carrier. An inner ring mounted on the central axis, an outer ring mounted to rotate around the central axis. A lubrication circuit brings a flow of oil between the rings. The lubrication circuit includes a first portion supplied with oil with openings to the outside of the inner ring in a radially inner area of the bearing. A second portion has openings to the outside of the inner ring. An intermediate portion has at least one channeling connecting the first portion to the second portion, having at least one singular pressure reduction formed by an elbow and at least one flattening of a transverse cross-section. The central axis has a radially outer first surface. The inner ring has a radially inner second surface.

Abstract: A method for aligning toothing in an assembly of two half-ring gears is provided: an angular positioning pin is provided which is to be received in respective holes of the half-ring gears; the holes are drilled on the first half-ring gear such that the first hole has a first cross-section that is smaller than the final cross-section thereof; the angles between the teeth are compared between the two half-ring gears, and an angular difference between said angles of the half-ring gears is deduced therefrom; the first hole is redrilled to the final cross-section, while the centre of the hole is angularly shifted by the value of the angular difference; the pin is engaged in the holes, and the half-ring gears are then assembled using an interference fit.

Abstract: A lubricating and cooling core for a mechanical reduction gear of a turbine engine, for example of an aircraft, is configured to be mounted in an axis of a planet gear of the reduction gear. The core includes first and second coaxial and substantially frusto-conical shields, each having a first end with a greater diameter and a second opposite end with a smaller diameter, the shields being secured to one another by their second ends and being configured to extend inside the axis and to cover at least a radially internal surface of the axis to define with the latter at least one annular cavity for the circulation of oil for lubricating and cooling the axis, the second ends of the first and second shields having fluid connection means configured to connect the at least one cavity to a source of lubricating and cooling oil.

Abstract: A ring gear for an epicyclic or planetary reduction gear of a turbomachine, in particular of an aircraft, said ring gear extending about an axis X and comprising first and second coaxial annular elements and comprising, respectively, two inner annular toothing sets of different orientation, each of said toothing sets having a pitch diameter and a median plane substantially perpendicular to said axis and with an intersection point designated Y in an axial cross-section of the ring gear, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges for attaching said first and second elements to each other, wherein each of said first and second flanges comprises a peripheral portion extending in a plane that is angled with respect to said axis X and that passes substantially through said intersection point Y.

Abstract: A planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft, this planet-carrier having a rotation axis and comprising axes for guiding the planet gears that are arranged around and parallel with the rotation axis, each guiding axis having a general tubular shape of which the outer periphery comprises only two coaxial and adjacent cylindrical tracks of the respective rollers of two annular rows of rollers, wherein each axis has an inner periphery that is substantially bi-conical and comprising two coaxial and adjacent frustoconical surfaces, these inner frustoconical surfaces converging towards one another and extending respectively radially inside the tracks.

Abstract: A deflector for a mechanical reduction gear of a turbine engine, for example of an aircraft, is configured to be inserted between two adjacent planets of the reduction gear. The deflector includes a block having a first lateral surface that is cylindrical and concave and has a radius of curvature R1 measured from an axis G1. The block also has a second lateral surface, opposite the first lateral surface, that is cylindrical and concave and that has a radius of curvature R1 measured from an axis G2 that is parallel to G1. Each of the first and second surfaces has at least one protruding tab having a generally elongate shape about the respective axis G1, G2 of the surface considered and having an internal periphery that is concavely curved and a has radius of curvature R2 measured from the respective axis G1, G2, R2 being less than R1.

Abstract: A lubricating oil distributor for a turbine engine mechanical reduction gear, for example of an aircraft, has an annular shape about an axis X and is formed of one single part. The distributor includes first and second independent oil circuits, the first oil circuit having a first oil inlet connected by a first annular chamber to several oil outlets distributed over a first circumference C1 about the axis X, and the second oil circuit having a second oil inlet connected by a second annular chamber to several oil outlets distributed over a second circumference C2 about the axis X, the first and second circumferences having different diameters.

Abstract: A toothed wheel extending along an axis and comprising at least two annular toothed areas and an annular groove located axially between said toothed areas, intended for collecting lubricating oil from said toothed areas, characterized in that said groove is delimited by an axially extending bottom surface and radially extending lateral surfaces, characterized in that the groove has at least one projecting portion extending radially outwards from the bottom surface of the groove.

Abstract: An assembly comprising a lubricating wheel and lubricant nozzles for a planetary gear speed reducer of a turbomachine, the wheel having a lubricator configured to supply lubricant to the nozzles and the bearings of the planetary carriers of the reducer, the wheel being intended to be mounted coaxially on an annular wall of an axis of rotation X of a planetary carrier of the reducer, the wheel having a bearing and attachment surface on the annular wall of the planetary carrier, the lubricant nozzles being distributed around the axis and each having a generally elongated shape, the nozzles having first longitudinal ends for fluidly connecting to the lubricator of the wheel, wherein the first ends of the nozzles being configured to be attached to the wheel before mounting the wheel on the annular wall of the planetary carrier.

Abstract: A clevis, particularly for a turbomachine includes a body that is attachable to a casing and at least one aperture for fitting a hinge pin. The body is formed in one piece and includes, about the at least one aperture, a honeycomb-type annular portion. The annular portion acts as a vibration filter and has a compressive and/or flexural strain capacity greater than that of the rest of the body.