Safran Transmission Systems

Safran Aircraft Engines

Guillaume Pierre Mouly

Adrien Louis Simon

Guillaume Julien Beck

Jean-Pierre Serey

Simon Loic Clement Lefebvre

Jordane Emile André Peltier

Bálint Pap

Clément Jarroux

Olivier Belmonte

Julien Fabien Patrick Becoulet

Boris Pierre Marcel Morelli

Paul Ghislain Albert Levisse

Antoine Jacques Marie Pennacino

Patrice Jocelyn Francis Gedin

Balint Pap

Simon Loïc Clément Lefebvre

Quentin Pierre Henri Pigott

Patrice Julien Ptaszynski

Dhafer Ghribi

Frederic Nicolas François Laisnez

Frédéric Nicolas François Laisnez

Pierre-Damien Tune

Pierre Gilbert Claude Medecin

Michel Chevallier

Laurent Pascal Diogène Pichard

The invention relates to a turbomachine assembly () extending around a longitudinal axis and comprising a speed reduction gear () having an external ring gear () and a gutter () for recovering a lubricant ejected by centrifugal effect, the gutter () being arranged around the external ring gear and comprising an area () for collecting the lubricant received by ejection. According to the invention, the gutter () is secured in terms of rotation to the external ring gear and in that the assembly comprises a device () for evacuating the lubricant to the outside of the collection area (), the evacuation device being intended to be connected to a stator of the turbomachine and extending at least partly into the collection area, the evacuation device being configured so as to evacuate the lubricant located in the collection area to an oil evacuation area located outside the gutter.

Assembly for a turbomachine comprising lubricant evacuation means, and turbomachine equipped with such an assembly

An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.

Aircraft turbomachine with mechanical reduction gear

A planet carrier for a mechanical gearbox of a turbomachine, in particular for an aircraft, the planet carrier being formed in a single piece and comprising two annular flasks connected by material bridges and together defining housings configured to receive planet gears, the flasks comprising orifices for mounting the planet gears which are oriented axially and which open into the housings. One of the flasks can include at least one thinning around its orifices, the at least one thinning defining a minimum thickness of material in the axial direction which is less than a minimum thickness of the other flask around each of its orifices.

Planet carrier for a mechanical gearbox on an aircraft turbomachine

A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.

Planet carrier for a speed reducer on an aircraft turbomachine

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

A mechanical reducer for a turbomachine, in particular for an aircraft, this reducer 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 hydrodynamic bearings being carried by a planet carrier and including cylindrical bodies which include an internal oil circulation cavity and first pipelines for conveying oil from this cavity to at least one external cylindrical surface of the body, wherein each of the cylindrical bodies further includes second oil evacuation pipelines, which are different from the first pipelines, and which extend from said at least one external cylindrical surface to at least one of the longitudinal ends of that body.

Mechanical reducer for an aircraft turbomachine

A planet carrier for a speed reduction gear of a turbomachine has a main axis X and includes a cage carrier with an annular row of axial fingers around the axis X, which carry first connecting elements. The carrier further includes a cage having at its periphery housings and second connecting elements that are mounted in the housings and that cooperate with the first connecting elements to form connections between the cage carrier and the cage, which allow at least one degree of freedom. The cage comprises two shells that are axially fastened to each other and separated from each other by a plane. The housings are formed respectively in the shells.

Planet carrier for a speed reduction gear of an aircraft 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

A mechanical gearbox for turbomachine, in particular for aircraft. The gearbox includes a sun gear including an external toothing, a ring gear including an internal toothing, and planet gears which are meshed with the sun gear and the stationary ring gear. The planet gears are carried by a movable planet carrier and each having external toothings of different diameters. The movable planet carrier includes a movable ring gear which carries an internal toothing and which is independent of the stationary ring gear, each of the planet gears being meshed with the sun gear and the stationary and movable ring gears.

Mechanical gearbox for an aircraft turbomachine

A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element.

Power transmission module for an aircraft turbomachine

The present invention relates to a mechanical reducer () for a turbomachine, in particular an aircraft, this reducer () including:

Mechanical reducer

A planet carrier for a mechanical gearbox for a turbomachine includes a one-piece cage that extends about an axis of rotation defining an internal housing configured to receive a sun gear and planet gears of the gearbox. The planet carrier further includes a lubrication system with at least one bore formed in the cage and extending parallel to the axis over more than 30% of a maximum axial dimension (Lmax) of the cage. The lubrication system also includes for the at least one bore, at least two sprinklers which are fitted to the cage and which are each mounted in a recess of the cage.

Planet carrier for a mechanical gearbox of an aircraft turbomachine

A planet carrier () for a speed reducer () of a turbomachine (), this planet carrier () having a main axis X and comprising: characterised in that the cage () comprises two shells () which are axially assembled to each other, said first or second connection elements comprising broaches () oriented radially with respect to said axis X and passing through radial orifices () of said shells ().

Planet carrier for a speed reducer of an aircraft turbomachine

A triple-flow turbomachine for an aircraft, including a power transmission module including a torque input connected to a turbine shaft, a first torque output of a gearbox connected to a main shaft for rotatably driving a main fan propeller, and a second torque output of a planet gear connected to a secondary shaft for rotatably driving a secondary fan propeller. The planet gear is independent of the gearbox and arranged downstream of the gearbox.

Growing community of inventors

Moissy-Cramayel, France

Guillaume Pierre Mouly