Safran Aircraft Engines

Safran Transmission Systems

Maeva Daphné Gros-Borot

Adrien Louis Simon

Gilles Alain Marie Charier

Caroline Marie Frantz

Matthieu Bruno François Foglia

Julien Fabien Patrick Becoulet

Clémentine Charlotte Marie Mouton

Paco Maurer

Nicolas Stoliaroff-Pepin

A turbomachine includes a low-pressure shaft having an internal passage for a first air stream and a first segment. A second segment includes a first frustoconical portion, and an intermediate lubrication chamber wherein at least one bearing is arranged. The intermediate lubrication chamber is arranged in an intermediate casing. An annular air chamber is configured to be supplied with air from a low-pressure compressor and is at least partly axially delimited by the first frustoconical portion. A radial separating wall is mounted around the first segment, and the first frustoconical portion further includes an opening to enable the first air stream to pass from the air chamber to the internal passage.

Turbomachine for an aircraft

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 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.

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.

Growing community of inventors

Moissy-Cramayel, France

Maeva Daphné Gros-Borot