Abstract: An impeller (130) for a planet carrier of a planetary gear speed reducer of a turbomachine, said impeller having a generally annular shape and comprising means (158) for supporting axes of rotation of planets of said reducer, said impeller comprising means for lubricating teeth of said planets and bearings of said axes, said lubrication means comprising an annular groove (138) located on the internal periphery of said impeller and opening radially towards the inside, said groove being connected to lubricant supply and/or spray means, characterised in that the impeller comprises dynamic annular sealing means (142, 144) located at the inner periphery of said impeller, on either side of the groove, and configured to interact with a stator (132) of the reducer or of the turbomachine intended to extend inside of and coaxially with the impeller.

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 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: A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.

Abstract: A speed-reducing unit, particularly for transferring torque between a gas turbine and a fan in a turbine engine, includes an annular ring, at least one gear that is coupled to the ring, the ring including two annular half-rings that are offset relative to each other along the main axis of the speed-reducing unit and that are coupled with at least one gear, and a plate for supporting the two half-rings, in relation to which the two half-rings are rotationally fixed about the main axis of the speed-reducing unit. Each half-ring includes an internal helical tooth. Each half-ring is connected to the support plate so as to be able to be uncoupled from at least one gear when at least one gear exerts a disengaging action on each half-ring, with the amplitude of the action being greater than a determined amplitude value.

Abstract: A mechanical reduction gear is suitable for a turbomachine and, in particular, a turbomachine of an aircraft. The reduction gear includes a sun gear, a ring gear formed by two half-ring gears, planet gears arranged between the sun gear and the ring gear, and at least one shaft rotationally fixed to the ring gear. The reduction gear further includes an annular covering part that extends around the ring gear and is independently fixed by flanges and/or splines to each of the half-ring gears.

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 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: An impeller (130) for a planet carrier of a planetary gear speed reducer of a turbomachine, said impeller having a generally annular shape and comprising means (158) for supporting axes of rotation of planets of said reducer, said impeller comprising means for lubricating teeth of said planets and bearings of said axes, said lubrication means comprising an annular groove (138) located on the internal periphery of said impeller and opening radially towards the inside, said groove being connected to lubricant supply and/or spray means, characterised in that the impeller comprises dynamic annular sealing means (142, 144) located at the inner periphery of said impeller, on either side of the groove, and configured to interact with a stator (132) of the reducer or of the turbomachine intended to extend inside of and coaxially with the impeller.

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: A lubricant nozzle for a planetary gear set speed reducer of a turbomachine, the nozzle having a generally elongate shape and including a body with a longitudinal axis B, the body having a longitudinal inner cavity in fluid communication with a lubricant inlet located at a longitudinal end of the body and with lubricant outlet apertures that are provided in an annular wall of the body and that extend substantially radially relative to the axis B, wherein the apertures are formed in at least one boss of the body, which boss projects radially outwards on the wall and extends, about the axis, at an angular extent that does not exceed 180°.

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 propulsion unit for an aircraft, including an engine and a propeller and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.

Abstract: A mechanical reduction gear is suitable for a turbomachine and, in particular, a turbomachine of an aircraft. The reduction gear includes a sun gear, a ring gear formed by two half-ring gears, planet gears arranged between the sun gear and the ring gear, and at least one shaft rotationally fixed to the ring gear. The reduction gear further includes an annular covering part that extends around the ring gear and is independently fixed by flanges and/or splines to each of the half-ring gears.

Abstract: A speed-reducing unit, particularly for transferring torque between a gas turbine and a fan in a turbine engine, includes an annular ring, at least one gear that is coupled to the ring, the ring including two annular half-rings that are offset relative to each other along the main axis of the speed-reducing unit and that are coupled with at least one gear, and a plate for supporting the two half-rings, in relation to which the two half-rings are rotationally fixed about the main axis of the speed-reducing unit. Each half-ring includes an internal helical tooth. Each half-ring is connected to the support plate so as to be able to be uncoupled from at least one gear when at least one gear exerts a disengaging action on each half-ring, with the amplitude of the action being greater than a determined amplitude value.

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 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: Lubricating oil distributor for a mechanical reduction gear of a turbine engine, in particular of an aircraft, wherein it has a general annular shape around an axis X and is formed of a single part, the distributor including first and second independent oil circuits, the first oil circuit including a first oil inlet connected by a first annular chamber to several oil outlets, and the second oil circuit including a second oil inlet connected by a second annular chamber to several oil outlets, the first chamber including a section that is at least partially nested in a section of the second chamber.