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 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 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: Device of the reduction gear or differential type for a turbine engine of an aircraft. A central sun gear and a row of planet gears, each of the planet gears are rotationally guided by at least one bearing extending around a tubular support. The tubular support includes an inner cavity for the reception of oil and through-orifices for the passage of oil of the tubular support to the at least one bearing. A member for circulating the oil is mounted in the cavity and includes at least one oil duct intended to be connected to an oil supply. The oil is intended to flow from the at least one duct into the inner cavity to form an oil film in contact with said tubular support, and to flow through the orifices.

Abstract: Accessory relay (100) suitable for driving accessory equipment for a gas turbine engine, such as an aircraft engine, comprising a housing (101) and a plurality of gear wheels (110) inside the housing, the wheels each comprising a tubular body (110a) and an outer annular web (110b) comprising outer peripheral teeth (110c), the wheels being supported in the housing by bearings (120), at least one (110) of said gear wheels being supported by a single bearing (120), characterized in that this bearing (120) comprises a fixed outer ring (122) that is radially further out with respect to an axis A of rotation of the wheel and is mounted in a bore (105) of the housing, and a mobile inner ring (123) that is radially further in with respect to the axis A and is mounted on the body of the wheel, said bearing being spaced apart passing through the inner periphery of the web of this wheel.

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: The invention concerns a process for the assembly of an epicyclic or planetary gear train of a planet gear carrier comprising one or more bores, each of the bores being intended to receive a pivot (18), the process comprising the following steps: a) manufacturing of at least one pivot (18) comprising a real axis (46) distinct from a theoretical axis; b) measuring the position of a real axis of each of said one or more bores of the carrier; c) for each bore of the carrier, mounting a pivot (18) in said bore and orienting it angularly so that the eccentricity of the pivot (18) at least partially makes up for the eccentricity of said bore.

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: Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch, in particular of an aircraft, the tube being intended to be mounted coaxially inside a tubular shaft of the propeller, the tube having an elongated shape and including a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft, wherein the first end part includes a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing, and in that said second end part comprises an outer axial annular bearing surface of an inner ring of the bearing, the annular bearing surface presenting in cross-section a convex curved shape.

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.