Safran Transmission Systems

Safran Aircraft Engines

Safran

Patrice Jocelyn Francis Gedin

Adrien Louis Simon

Guillaume Julien Beck

Antoine Jacques Marie Pennacino

Boris Pierre Marcel Morelli

Jordane Emile André Peltier

Serge René Morreale

Alexis Claude Michel Dombek

Juan-Luis Marcos Izquierdo

Bálint Pap

Fabien Roger Gaston Caty

Olivier Belmonte

Julien Fabien Patrick Becoulet

Jean-Charles Michel Pierre Di Giovanni

Paul Ghislain Albert Levisse

Guillaume Pierre Mouly

Jean-Pierre Serey

Amélie Argie Antoinette Chassagne

Mathieu Jean Charrier

Simon Loic Clement Lefebvre

Balint Pap

Simon Loïc Clément Lefebvre

Quentin Pierre Henri Pigott

Loïc Francois

Melody Elisabeth Laurent Cailler

Mélody Elisabeth Laurent Cailler

A sun gear for a mechanical gearbox of an aircraft turbomachine, the sun gear having an annular shape around an axis and including an internal annular part having at its internal periphery coupling grooves, an external annular part having at its external periphery at least one meshing tooth, the external part extending around the internal part, and an annular veil connecting the internal and external parts. At least one of the internal and external parts can include two independent rings, each having grooves or teeth, and the veil can have two annular branches connected respectively to the two rings.

Sun gear for a mechanical reduction gear of an aircraft turbomachine

A power transmission system for an aircraft turbine engine including a speed reducer including a ring gear that is able to rotate about an axis X, formed from half-rings having annular flanges clamped together by first fastener. The reducer includes an annular channel for recovering centrifuged oil, having a U-shaped cross section, extending around the flanges, this channel being formed by an axial assembly of at least two parts and forming a fairing for the flanges and the first fastener intended to limit aerodynamic disturbances.

Power transmission system comprising an improved oil recovery channel

An oil recovery device for a reducer of an aircraft turbomachine, the device having a gutter extending around an axis and being intended to be arranged facing oil ejection means formed in a ring gear of the reducer of the turbomachine. The gutter can include at least one oil reception chamber which extends around the axis and which is open towards the axis so as to receive the oil coming from the oil ejection means. The reception chamber can be delimited by a first wall and a second wall arranged facing each other. The first wall can have an axial oil evacuation orifice and the second wall can have a radial dimension relative to the axis which increases increasingly along the axis towards the axial orifice, so as to allow oil ejected by the reducer to be conveyed to the axial orifice.

Oil recovery device for a turbomachine

An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.

Aircraft turbine engine with an off-axis propeller

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

Lubrication device for a turbomachine reduction gear, the device comprising an annular lubricating oil collecting cup delimited by a first wall and a second wall, said cup being divided by internal walls extending between the first wall and the second wall so as to define a plurality of angular sectors forming oil collection basins, the basins being circumferentially adjacent around the axis and comprising lubricating oil outlets, characterized in that one or more of said internal walls have openings allowing oil to pass between the circumferentially adjacent basins, characterized in that said openings (58) are formed in one or more of said internal walls so as to define one or more rows of openings in said one or more internal walls.

Lubrication device for turbomachine reduction gear

The present invention relates to an oil transfer device () for lubricating a planet carrier, movable in rotation, of an epicyclic gear train for a turbomachine, the device () extending around an axis (A) and having:

Oil transfer device

A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.

Mechanical reduction gear for an aircraft turbomachine

The invention concerns an assembly comprising an epicycloidal gear train () having a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the central pinion () surrounding and being rotationally fixed to a shaft () and the gear train comprising means for lubricating the teeth and axes () of the satellite pinions (), these means including an annular cup () fixed to the satellite carrier () opened radially inward. According to the invention, the assembly includes fixed oil spraying means () configured to spray oil towards oil deflecting means () towards the inside of the annular cup ().

Assembly comprising a planetary gearset

The invention concerns an epicycloidal gear train () comprising a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the gear train () comprising an annular cup () being integral with the satellite carrier () and open radially inward. According to the invention, the cup () is divided into a circumferential succession of first basins () of the first oil circuit and second basins () of the second oil circuit, the first basins () being fluidly separated from the second cells () and characterised in that the cup () comprises two annular walls () axially facing, the annular wall () of which is furthest from a median transverse plane () of the gear train () has openings () opening into the second basins ().

Planetary gearset

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.

Growing community of inventors

Moissy-Cramayel, France

Patrice Jocelyn Francis Gedin