Safran Transmission Systems

Jean-Charles Michel Pierre Di Giovanni

Adrien Louis Simon

Alexis Claude Michel Dombek

Florian Rappaport

Boris Pierre Marcel Morelli

Mathieu Jean Charrier

Antoine Jacques Marie Pennacino

Guillaume Jean Pierre Robinet

Guillaume Julien Beck

Jordane Emile André Peltier

Patrice Jocelyn Francis Gedin

Balint Pap

Simon Loic Clement Lefebvre

Simon Loïc Clément Lefebvre

Bálint Pap

Patrice Julien Ptaszynski

Marc Dominique Seyfrid

Maxime Lefebvre

A planet-carrier cage is provided for a turbomachine speed reducer having a planetary gear set. The cage contains a central sun gear and an annular row of planet gears arranged around the sun gear axis and engaging both the sun gear and an internal gear that surrounds the cage. A periphery of the cage has axial receiving elements configured to receive axial fingers secured to a cage carrier of the speed reducer. Each receiving element is penetrated by a radial spindle that guides the rotation of a connection means, such as a swivel joint or a bearing, which is supported by the fingers. The spindles include means for projecting lubricating oil into regions in which the planet gears mesh with the internal gear.

Cage for a turbomachine speed reducer with planetary gear set

An installation for mounting an outer sun gear in a reduction gear. The reduction gear includes an outer sun gear and planet gears meshing with an inner sun gear and with the outer sun gear and each mounted for free rotation around a pivot of a planet carrier. The outer sun gear includes a first crown having a first toothing and a second crown having a second toothing each meshing with first and second toothings of the planet gears. The installation includes a frame for supporting the reduction gear along its longitudinal axis, and first and second torque applicators, such as cylinders, that apply a torque around an axis of first and second rings, respectively. The first ring is configured to engage with the first crown of the outer sun gear and the second ring is configured to engage with a second crown of the outer sun gear.

Installation for mounting an outer sun gear

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 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&#xb0;.

Lubricant nozzle for a planetary gear set speed reducer of a turbomachine

An oil supply device intended to supply oil to an epicyclic reduction gear, the oil coming from at least one oil injector fixed with respect to the reduction gear, the oil supply device including at least one cup which is integral with a planet carrier of the reduction gear and substantially annular open radially with respect to an axis of the reduction gear and the walls of which delimit a cavity supplied by the at least one oil injector and which supplies at least one of the oil distribution circuits of the reduction gear. The oil supply device is staged and includes at least two independent stages provided with cups coaxial, of different diameters, each supplying an associated oil circuit and configured to receive the oil axially, centripetally, or tangentially, or according to an inclined direction combining two of the directions.

Staged impeller for the oil supply of an epicyclic or planetary reduction gear

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 Rmeasured from an axis G. 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 Rmeasured from an axis Gthat is parallel to G. Each of the first and second surfaces has at least one protruding tab having a generally elongate shape about the respective axis G, Gof the surface considered and having an internal periphery that is concavely curved and a has radius of curvature Rmeasured from the respective axis G, G, Rbeing less than R

Deflector for a mechanical reduction gear of an aircraft turbine engine

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.

Lubricating and cooling core for a mechanical reduction gear of an aircraft turbine engine

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 and comprising first and second coaxial annular elements () and comprising, respectively, two inner annular toothing sets () of different orientation, 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, characterised in that one of said first and second flanges comprises, at its outer periphery, a cylindrical centring rim () configured to cooperate with the outer periphery of the other of said first and second flanges.

Ring gear for an epicyclic or planetary reduction gear of a turbomachine

The invention relates to the lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft, said planet-carrier comprising a cage defining an internal housing intended to receive a central sun gear with an axis of rotation X, and an annular row of planet gears arranged around the sun gear, said cage comprising two annular walls that are radial with respect to said axis X, and connected to one another at their outer periphery by a cylindrical wall of axis X, at least one of these radial walls comprising orifices for mounting the axes of said planet gears, and the cylindrical wall comprising 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 intended to extend around the planet gears and the cage.

Lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft

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 Cabout 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 Cabout the axis X, the first and second circumferences having different diameters.

Lubricating oil distributor for a mechanical reduction gear of aircraft turbine engine

An impeller for a planet carrier of a epicyclic speed reduction gear of a turbine engine is fixed in rotation to the planet carrier and is rotatable about an axis of the reduction gear. The impeller has an annular shape about the axis and includes means for lubricating in particular planet gear bearings of the reduction gear. The lubricating means include an annular cavity located at the inner periphery of the impeller, wherein the impeller has an inner peripheral wall that closes the cavity in the radial direction. The impeller further includes an annular aperture that extends around the axis and opens in the axial direction into the cavity to supply lubricating oil thereto.

Impeller for a planet carrier of an epicyclic speed reduction gear of a turbine engine

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.

Sun gear for a mechanical reduction gear of an aircraft turbine engine

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.

An impeller () for a planet carrier of a planetary gear speed reducer of a turbomachine, said impeller having a generally annular shape and comprising means () 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 () 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 () located at the inner periphery of said impeller, on either side of the groove, and configured to interact with a stator () of the reducer or of the turbomachine intended to extend inside of and coaxially with the impeller.

Impeller for a planet carrier of a planetary gear speed reducer of a turbomachine

Planet-carrier () for a reduction gear (), in particular for a turbine engine of an aircraft, said planet-carrier comprising an annular cage extending about an axis X and comprising two radial annular walls () extending about the axis X and connected at their outer periphery by means of first fins (), said radial walls being intended to be arranged opposite the planet gears () of the reduction gear, and said first fins defining between them the first assembly spaces () for these planet gears, characterised in that the planet-carrier is made of a single block and further comprises an attachment ring () that extends about the axis X and is connected to one of said walls by means of second fins (), said second fins defining between them second spaces (), separate from the first spaces (), and of which at least some are intended to be intersected by lubrication pipes () of the reduction gear.

Planet-carrier for a reduction gear of the planetary type

A planet carrier for a speed-reducing unit with an epicyclic gear train for a turbine engine, said planet carrier comprising a cage defining an internal space for assembling a central sun gear having an axis of rotation and an annular row of planet gears disposed around the axis and meshed with said sun gear, said cage comprising two substantially parallel annular walls centered on said axis and a cylindrical wall connecting said annular walls to their outer periphery, a first one of said annular walls being connected to a substantially cylindrical body, wherein a second one of said annular walls is formed as a single part with a lubrication grove, channel or duct.

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Moissy-Cramayel, France

Jean-Charles Michel Pierre Di Giovanni