Safran Transmission Systems

Safran Aircraft Engines

Safran Electrical & Power

Safran

Boris Pierre Marcel Morelli

Jordane Emile André Peltier

Adrien Louis Simon

Guillaume Julien Beck

Mathieu Jean Charrier

Clément Paul René Niepceron

Loïc Francois

Maxime Fernandez

Jean-Charles Michel Pierre Di Giovanni

Antoine Jacques Marie Pennacino

Aldric Renaud Gabriel Marie Moreau De Lizoreux

Jean-Pierre Serey

Yohan Douy

Alexis Claude Michel Dombek

Patrice Jocelyn Francis Gedin

Florian Rappaport

Mathieu Jean Jacques Santin

Jean-Michel Bernard Paul Chastagnier

Patrice Julien Ptaszynski

Xavier Paul Lucien Hert

Thomas Turchi

Guillaume Pierre Mouly

Benjamin Feraud

Matthieu Bruno François Foglia

Simon Loïc Clément Lefebvre

Luc Henri Chatenet

Antoine Mathieu

Marc Dominique Seyfrid

Gilles Gaston Jacques Gouin

Xavier Roger Betbeder-laüque

Florent Lejeune

Bernard Guy Antoine Charpentier

Jonathan Jean-Pierre Rouffet

Clément Raucoules

Antoine Pennacino

An aircraft turbomachine includes a speed reduction gear having an input pinion connected to a power shaft and an output pinion connected to a propeller shaft. An electric machine is integrated into the speed reduction gear and is configured to provide electrical power to the propeller shaft or to take mechanical power from the propeller shaft. The electric machine has a rotor driven in rotation about an axis coaxial with a longitudinal axis of the turbomachine and a stator connected to a casing. The input pinion includes an input shaft offset from an axis of the output pinion, and the speed reduction gear has two parallel intermediate transmission lines configured to transmit the torque from the input pinion to the output pinion to drive the rotor in rotation.

Turbomachine comprising a speed reduction gear integrating an electric machine

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

A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.

Mechanical reducer for an aircraft turbomachine

A device for driving at least one wheel of an aircraft landing gear including at least one landing gear wheel, this wheel including a rim, an electric motor including a shaft, a mechanical transmission system between the shaft of the motor and the rim, this mechanical transmission system including a mechanical reducer including a sun gear secured in rotation to the shaft of the motor, a ring gear, and planet gears which are carried by a planet carrier and which each includes three external toothings, including a median external toothing which is meshed with a toothing of the sun gear, and two lateral external toothings which are respectively meshed with toothings of the ring gear.

Device for driving at least one wheel of an aircraft landing gear

A device for driving at least one wheel of an aircraft landing gear is provided. The device includes at least one wheel having a rim, an electric motor having a shaft, and a mechanical transmission system for mechanical transmission between the shaft of the motor and the rim. The mechanical transmission system includes a mechanical reduction gear. The mechanical reduction gear includes a sun gear secured in rotation to the shaft and having an external toothing, a stationary ring gear with internal toothing, a movable ring gear secured in rotation to the rim and having an internal toothing, and planet gears that are meshed with the sun gear and each have two external toothing meshed respectively with the toothing of the stationary and movable ring gears.

A mechanical speed reducer, in particular for a device for driving at least one wheel of an aircraft landing gear, this reducer including a first sun gear including external toothing, first planet gears meshed with the external toothing of the first sun gear, these first planet gears being carried by a first planet carrier, a stationary ring gear meshed with the planet gears, and second planet gears meshed with a ring gear and with an external toothing of said first planet carrier, these second planet gears being carried by a second planet carrier.

Speed reducer for a device for driving a wheel of an aircraft landing gear

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

Turbomachine including: a fan arranged along a longitudinal axis of the turbomachine, a primary duct able to channel a primary air flow from the fan through a compressor, a combustion chamber and a turbine of the turbomachine, an annular nacelle surrounding the fan so as to delimit a secondary duct able to channel a secondary air flow from the fan the temperature of which is less than that of the primary air flow of the fan, the secondary air flow extending around the primary air flow of the fan and, engine support arms arranged around the longitudinal axis between the annular nacelle and a hub which delimits the primary and secondary ducts characterized in that it also includes an electrical energy generation device mounted facing or so as to be able to be arranged facing one of the support arms.

Integration of generators in an air flow of an aircraft engine

The disclosure relates to an assembly for an aircraft turbomachine, having a speed reduction gear comprising an input pinion connected to a power shaft of the turbomachine and an output pinion connected to a propeller shaft of the turbomachine. According to the disclosure, the assembly includes two electric machines which are each configured to provide electrical power to the propeller shaft or to draw mechanical power from the propeller shaft, each electric machine comprising a rotor and a stator, the stator configured to be connected to a casing of the turbomachine. The speed reduction gear can include two substantially parallel intermediate transmission lines configured to transmit the torque from the input pinion to the output pinion, each rotor being driven in rotation respectively by a pinion of an intermediate line.

Turbomachine comprising a speed reduction gear and at least one electric machine

A ring gear for an aircraft mechanical gearbox, the ring gear having an annular shape about an axis and having an internal toothing at its internal periphery, an external annular flange or splines at its external periphery, and an annular web extending between the internal toothing and the external flange or splines. The web can include an annular row of arms which are distributed about the axis, these arms connecting the internal toothing to the external flange or splines and being formed in a single piece with the internal toothing and the external flange or splines.

Ring gear for an aircraft mechanical gearbox

A turbomachine includes a fan, a first casing with longitudinal axis X in which a motor shaft is rotated around the longitudinal axis X, a second casing surrounding and coaxial with the first casing, and a drive shaft connected to the motor shaft. The driveshaft is also connected to at least two electric machines via a power transmission angle gear device housed in a housing. The electric machines being intended are configured to take or inject power on the motor shaft. The housing has a coupling surface to which the two electric machines are coupled.

Turbomachine equipped with electric machines coupled to a coupling surface

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

An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.

Epicyclic reduction gear for a turbomachine

The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.

Lubricating oil distributor for a mechanical reduction gear of a turbine engine, in particular of an aircraft, wherein it has a general annular shape around an axis X and is formed of a single part, the distributor including first and second independent oil circuits, the first oil circuit including a first oil inlet connected by a first annular chamber to several oil outlets, and the second oil circuit including a second oil inlet connected by a second annular chamber to several oil outlets, the first chamber including a section that is at least partially nested in a section of the second chamber.

Growing community of inventors

Moissy-Cramayel, France

Boris Pierre Marcel Morelli