Safran Transmission Systems

Bálint Pap

Adrien Louis Simon

Jean-Charles Michel Pierre Di Giovanni

Guillaume Julien Beck

Guillaume Pierre Mouly

Patrice Jocelyn Francis Gedin

Alexis Claude Michel Dombek

Antoine Jacques Marie Pennacino

Simon Loïc Clément Lefebvre

Quentin Pierre Henri Pigott

Clément Jarroux

Cyrille Casteloot

Pierre-Damien Tune

Pierre Gilbert Claude Medecin

Lilia Aoun

A plain bearing for a mechanical reducer for a turbomachine is integrally formed and includes a cylindrical body. The cylindrical body has an external cylindrical guide surface, a first axial mounting extension, a first circumferential edge extending around the first extension, a second axial mounting extension, and a second circumferential edge extending around the second extension. The plain bearing further includes an attachment cover connected to the first axial extension and extending axially opposite said first edge.

Plain bearing for an aircraft turbomachine mechanical reducer

A drive assembly for a mechanical reducer for a turbomachine, in particular for an aircraft, includes planet gears, a planet carrier having at least one transverse wall, plain bearings for guiding the planet gears in rotation, and an oil supply circuit for the plain bearings. The planet carrier has collars for attaching the planet gears to the at least one transverse wall, and each of the planet gears includes at least one external cylindrical surface for forming an oil film with an internal cylindrical surface portion of each of the collars for forming said oil film.

Drive assembly for a mechanical reducer for an aircraft turbomachine

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

Mechanical gearbox for an aircraft turbomachine

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

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Moissy-Cramayel, France

Bálint Pap