Safran Aircraft Engines

Safran Transmission Systems

Matthieu Bruno François Foglia

Adrien Louis Simon

Gilles Alain Marie Charier

Caroline Marie Frantz

Maeva Daphné Gros-Borot

Boris Pierre Marcel Morelli

Serge René Morreale

Jean-Pierre Serey

Zoltan Zsiga

Clément Raucoules

Valentin Sébastien Simon Avoyne

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

A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a low-pressure compressor driven in rotation by the drive shaft, the low-pressure compressor having a mean radius, a fan shaft, a fan driven in rotation by the fan shaft, a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet having a mean radius. A first ratio between a ratio of a mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.

Aeronautic propulsion system with improved propulsion efficiency

An assembly for an aircraft turbomachine, comprising an intermediate casing hub, an equipment support having an upstream face located downstream of the intermediate casing hub, and a transfer gear box driving a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the turbomachine, to at least one upstream equipment item mounted on the upstream face of the equipment support, the upstream equipment item comprising a structural element attaching the equipment support to the intermediate casing hub.

Aircraft turbine engine assembly comprising a support for equipment

An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.

An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.

Arrangement for an aircraft turbine engine having improved lubrication, the arrangement comprising a shaft rotatably coupled to a following member by means of splines

A propulsion system includes a drive shaft that rotates about an axis, a fan, a fan shaft that drives the fan about the axis, a reduction mechanism coupling the drive and fan shafts, a compression section driven by the drive shaft, and an inlet channel that extends between the fan and the compression section. The inlet channel includes inner and outer ferrules delimiting an air inlet flow path, the inner ferrule having a minimum radius. The reduction mechanism includes two reduction stages including two or more planet gears circumferentially distributed around the axis, each planet gear including a first portion meshed with the drive shaft and a second portion meshed with the fan shaft and being mounted fixed with respect to the inner ferrule and having a maximum radius greater than the minimum radius such that the air inlet flow path extends partly between the two or more planet gears.

Aeronautical propulsion system with improved propulsive efficiency

A propulsion system includes a drive shaft, a fan, a fan shaft, and a reduction device coupling the drive and fan shafts. The reduction device includes a first reduction stage and a second reduction state, and include a sun gear, centered on an axis of rotation of the drive and fan shafts and driven in rotation by the drive shaft, a ring gear, coaxial with the sun gear and that drives the fan shaft in rotation about the axis, and planet gears distributed circumferentially about the axis between the sun and ring gears, each planet gear including a first portion which is meshed with the sun gear and a second portion which is meshed with the ring gear, a diameter of the first portion being different from a diameter of the second portion, and an oil transfer bearing positioned between the fan and the reduction device.

Aeronautic propulsion system with low leakage rate and improved propulsion efficiency

A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.

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Moissy-Cramayel, France

Matthieu Bruno François Foglia