Safran Transmission Systems

Safran Aircraft Engines

Simon Loïc Clément Lefebvre

Adrien Louis Simon

Guillaume Jean Pierre Robinet

Julien Fabien Patrick Becoulet

Boris Pierre Marcel Morelli

Jean-Charles Michel Pierre Di Giovanni

Guillaume Julien Beck

Romain Guillaume Cuvillier

Guillaume Pierre Mouly

Emmanuel Pierre Dimitri Patsouris

Guillaume Patrice Kubiak

Didier Jean-Louis Yvon

Patrice Jocelyn Francis Gedin

Mathieu Jean Charrier

Clément Paul René Niepceron

Bálint Pap

Quentin Pierre Henri Pigott

Dhafer Ghribi

Marc Dominique Seyfrid

An impeller () for a planet carrier of a planetary gear speed reducer of a turbomachine, is configured intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer. The impeller has an annular shape about the axis and includes lubrication means (), in particular for lubricating bearings of planet gears of the speed reducer. The lubrication means include an annular cavity () situated at the inner periphery of the impeller. The impeller includes an inner peripheral wall () closing the cavity () in the radial direction, and the impeller includes an annular port () that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.

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

A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.

Mechanical gearbox for aircraft turbomachine

A mechanical reduction gear of a turbine engine, in particular for an aircraft, includes a sun gear having external toothing, a ring gear which extends around the sun gear and has internal toothing, planet gears which are in mesh with the sun gear and the ring gear and which have toothings of different diameters, a planet carrier which supports bearings for guiding the planet gears in rotation, and a lubrication circuit of the reduction gear. The planet carrier has a hydrodynamic abutment on which the sun gear is configured to bear axially.

Mechanical reduction gear for an aircraft turbine engine

The present disclosure relates to the lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, for example of an aircraft. The planet-carrier includes a cage defining an internal housing configured to receive a central sun gear with an axis of rotation X, and an annular row of planet gears arranged around the sun gear. The cage includes two annular walls that are radial with respect to the axis X, and connected to one another at their outer periphery by a cylindrical wall. At least one of the radial walls has orifices for mounting the planet gears, and the cylindrical wall has 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 configured 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 planetary gearset having a first planet gear, a second planet gear, and pinion gears. The pinion gears mesh with the first planet gear and with the second planet gear, and each pinion gear is pivotally mounted around a shaft. A pinion gear carrier supports each shaft. Each shaft has a radially inner cylindrical portion mounted on the pinion gear carrier, a radially outer cylindrical portion about which the pinion gear is pivotally mounted and a flange extending radially from the radially outer cylindrical portion. The radially outer periphery of the flange is mounted on the pinion gear carrier. The radially outer cylindrical portion and the radially inner cylindrical portion are connected to each other by a radially extending connecting zone.

Planetary gear train

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.

Mechanical reduction gear for an aircraft turbomachine

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Moissy-Cramayel, France

Simon Loïc Clément Lefebvre