Safran Transmission Systems

Safran Aircraft Engines

Antoine Jacques Marie Pennacino

Jordane Emile André Peltier

Boris Pierre Marcel Morelli

Patrice Jocelyn Francis Gedin

Juan-Luis Marcos Izquierdo

Jean-Charles Michel Pierre Di Giovanni

Mathieu Jean Charrier

Balint Pap

Jérémy David Seban

Mohamed Bouyakoub

Adrien Louis Simon

Guillaume Julien Beck

Jean-Pierre Serey

Amélie Argie Antoinette Chassagne

Florian Rappaport

Bálint Pap

Loïc Francois

Patrice Julien Ptaszynski

Dhafer Ghribi

Anthony Cuffaro

Lilia Aoun

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 plain bearing for a planet gear of a turbomachine mechanical reduction gear, the plain bearing having an annular barrel with an axis which delimits at least one central bore centred on the axis, and the barrel having annular grooves which extend around the axis and which open out axially in opposite orientations at the axial ends of the barrel, each annular groove being delimited by two coaxial internal and external walls of the barrel connected by a transverse bottom wall which has at least one opening which opens into a cavity which is formed in the barrel between said the at least one central bore and a periphery of the barrel, characterised in that wherein each cavity is closed by a sealing seal.

Plain bearing for a planet gear of a mechanical reduction gear with silent operation

A gutter for recovering lubrication oil, particularly for a mechanical reducer, comprising un corps principal comprising an annular main body around a central axis, and a deflector attached to the main body and configured to allow the evacuation of the oil radially from an inner cavity of the main body toward the outside of the gutter, the deflector comprising a main sleeve disposed in the extension of the main body, and an evacuation channel configured to deflect oil from the main sleeve and having a curved shape such that a first end of the evacuation channel, communicating with the inner cavity, is tangent to the main body, and a second end of the evacuation channel is directed outward with respect to the annular main body.

Gutter for recovering lubrication oil for a mechanical reducer comprising an improved deflector

A gutter for recovering lubrication oil, particularly for a mechanical reducer of an aircraft turbomachine, annular around a central axis, and comprising a first radial wall extending radially with respect to the central axis, an inclined wall extending from a radially outer end of the first radial wall, a guide portion having an overall U shape extending from one end of the inclined wall, and a second radial wall extending radially outward with respect to the central axis from one end of the guide portion, a space delimited by the first radial wall, the second radial wall and the inclined wall forming an oil intake chamber, and a space delimited by the guide portion and the second radial wall forming an oil evacuation cavity.

Gutter for recovering lubrication oil for a mechanical reducer

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

Speed reduction gear for an aircraft turbomachine. The reduction gear has a main axis and planet carrier having a cage and a cage carrier, a sun gear located in the cage and centred on the main axis, an annular row of planet gears arranged around the main axis and the sun gear and meshed with the sun gear, and a ring gear arranged around the axis and the cage and meshed with the planet gears. The cage and the cage carrier are connected to each other by connections whose bending flexibility is optimised.

Speed reduction gear 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

A pivot () with a longitudinal axis (Y) for a bearing of a mechanical reduction gear, comprising a first annular part () including an axial passage () and a second annular part () mounted around the first annular part (), the first annular part () delimiting with the second annular part (b) a lubrication circuit at least one oil inlet () of which opens out inwards of the first annular part () into the axial passage () and at least one oil outlet () of which opens radially outwards of the second annular part ().

Pivot for a turbomachine mechanical reduction gear

An oil supply device intended to supply oil to an epicyclic reduction gear, the oil coming from at least one oil injector fixed with respect to the reduction gear, the oil supply device including at least one cup which is integral with a planet carrier of the reduction gear and substantially annular open radially with respect to an axis of the reduction gear and the walls of which delimit a cavity supplied by the at least one oil injector and which supplies at least one of the oil distribution circuits of the reduction gear. The oil supply device is staged and includes at least two independent stages provided with cups coaxial, of different diameters, each supplying an associated oil circuit and configured to receive the oil axially, centripetally, or tangentially, or according to an inclined direction combining two of the directions.

Staged impeller for the oil supply of an epicyclic or planetary reduction gear

An impeller for a planet carrier of a epicyclic speed reduction gear of a turbine engine is fixed in rotation to the planet carrier and is rotatable about an axis of the reduction gear. The impeller has an annular shape about the axis and includes means for lubricating in particular planet gear bearings of the reduction gear. The lubricating means include an annular cavity located at the inner periphery of the impeller, wherein the impeller has an inner peripheral wall that closes the cavity in the radial direction. The impeller further includes an annular aperture that extends around the axis and opens in the axial direction into the cavity to supply lubricating oil thereto.

Impeller for a planet carrier of an epicyclic speed reduction gear of a turbine engine

A toothed wheel extending along an axis and comprising at least two annular toothed areas and an annular groove located axially between said toothed areas, intended for collecting lubricating oil from said toothed areas, characterized in that said groove is delimited by an axially extending bottom surface and radially extending lateral surfaces, characterized in that the groove has at least one projecting portion extending radially outwards from the bottom surface of the groove.

Growing community of inventors

Moissy-Cramayel, France

Antoine Jacques Marie Pennacino