Safran Transmission Systems

Alexis Claude Michel Dombek

Jean-Charles Michel Pierre Di Giovanni

Julie Marie Renée Lemoine

Boris Pierre Marcel Morelli

Patrice Jocelyn Francis Gedin

Balint Pap

Florian Rappaport

Guillaume Julien Beck

Mathieu Jean Charrier

Bálint Pap

An oil restrictor for emergency lubrication of a component for an aircraft turbine engine includes a metal cylindrical body having a longitudinal axis and configured to be housed in and shrink-fitted into a cylindrical bore of a part of the turbine engine. The restrictor further includes an integrated oil circuit enabling oil to pass through the restrictor along the axial extent thereof. The body is a one-piece body, and the circuit has at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along the axis.

Oil restrictor for emergency lubrication of a component for an aircraft turbine engine

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

The invention relates to a pivot pin () for an epicyclic gear train sliding bearing, the pivot pin having a portion () forming a central shank, extending around an axial passage (), and axially opposed, axially open circumferential grooves () which radially separate two axially opposed lateral end portions () of the central shank from two cantilevered lateral portions (). With respect to a plane () perpendicular to said axis of the axial passage () and passing through the axial middle of the axial passage, the axial distance between said plane () and the bottom end of one of the circumferential grooves () is smaller than the axial distance between said plane and the bottom end of the axially opposed circumferential groove ().

Pivot and gear train

A pivot for a sliding bearing of an epicyclic train includes an annular wall delimiting an axial passage, the annular wall including a first and a second annular groove opening axially in opposite directions and each defined by two coaxial inner and outer annular branches formed at the axial ends of the annular wall. The pivot also includes a plurality of first holes opening at a first end into the first annular groove and at a second opposite end into the second annular groove, these holes being made over an angular sector of between 5&#xb0; and 330&#xb0;.

Pivot for a sliding bearing

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 a pivot () for a sliding bearing of an epicyclic train, comprising an annular wall () defining an axial passage () and comprising a first () and a second () annular groove opening axially in opposite directions (L, L) and each defined by two coaxial inner () and outer () annular branches formed at the axial ends of the annular wall (). According to the invention, the recesses () are made in at least one bottom wall () of one of the annular grooves ().

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

The invention relates to a pivot pin () for an epicyclic gear train sliding bearing, having axially opposed, laterally open circumferential grooves () providing flexibility to the pivot pin, each groove having a radial width and at least one depth (P). At least one of the circumferential grooves () has a said width and/or depth (P) which varies circumferentially.

Pivot for sliding bearing and gear train

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.

Cage planet carrier for a speed-reducing unit with an epicyclic gear train

A planet carrier for an epicyclic speed reduction gear, comprising a torque transmission member of longitudinal axis A and an annular cage extending around the axis A and connected to a longitudinal end of the member, said cage comprising two flanks extending essentially radially with respect to the axis A and connected by bridges, seats extending axially between the flanks and being intended for supporting planet gears mounted rotatably about the seats, characterized in that said bridges comprise bars which cross one another essentially in the shape of an X, and of which the ends located on the side of said member are connected to said member by a ring extending around said axis A and comprising a continuous internal annular channel.

Planet carrier for an epicyclic speed reduction gear

The invention relates to a planet-carrier () cage () for a turbomachine speed reducer () with a planetary gear set, said cage being designed such that it can contain a central sun wheel () with an axis of rotation X and an annular row of planets () arranged around the axis X and engaged with said sun wheel, the cage comprising axial receiving elements () on the periphery thereof, for receiving axial arms () secured to a barrel () of said reducer, a substantially radial finger () passing through each receiving element and being used to guide the rotation of a ball joint () carried by one of said arms, characterised in that each finger comprises means () for lubricating said ball joint.

Cage for a turbomachine speed reducer with planetary gear set

An oil pipe cover for a mechanical reduction gear of a turbomachine, for example of an aircraft, is configured to be fixed to a planet carrier of the reduction gear and to be mounted on an axial end of a hydrodynamic bearing tubular support of a planet gear of the reduction gear. The oil pipe cover has an annular body extending around an axis (Y) and having a mounting central orifice on the axial end. The body has two diametrically opposed circumferential deflectors: a first deflector having a circumferential oil guiding surface located radially outwards with respect to the axis (Y), and a second deflectors having a circumferential oil guiding surface located radially inwards with respect to the axis (Y).

Oil pipe cover and mechanical reduction gear for an aircraft turbomachine comprising such a cover

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.

Assembly comprising a lubricating wheel and lubricant nozzles for a planetary gear speed reducer of a turbomachine

The invention relates to a pivot pin () for an epicyclic gear train sliding bearing, the pivot pin having axially opposed, laterally open circumferential grooves (), providing flexibility to the pivot pin and which radially separate two axially opposite lateral end portions of a central shank from two lateral cantilevered portions () of the pivot pin. At least one of the cantilevered lateral portions is hollowed out by at least one recess ().

Growing community of inventors

Moissy-Cramayel, France

Alexis Claude Michel Dombek