Safran Transmission Systems

Safran Aircraft Engines

Safran Electrical & Power

Aldric Renaud Gabriel Marie Moreau De Lizoreux

Boris Pierre Marcel Morelli

Guillaume Julien Beck

Mathieu Jean Jacques Santin

Jean-Michel Bernard Paul Chastagnier

Thomas Turchi

Xavier Paul Lucien Hert

Benjamin Feraud

Boris Morelli

Antoine Mathieu

Maxime Amiet

A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.

Aircraft propulsion assembly provided with a rotary transformer for supplying the blades with electrical energy

Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch, in particular of an aircraft, the tube being intended to be mounted coaxially inside a tubular shaft of the propeller, the tube having an elongated shape and including a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft, wherein the first end part includes a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing, and in that said second end part comprises an outer axial annular bearing surface of an inner ring of the bearing, the annular bearing surface presenting in cross-section a convex curved shape.

Oil transfer for a control system regulating the propeller pitch of a turbine engine

A reduction gear including an input shaft including an input gear, an output shaft including an output gear, and two intermediate transmission lines, each intermediate transmission line including an intermediate shaft including a first stage of teeth and a second stage of teeth, the stages rotating as one, and an additional gear for meshing respectively with the first stage of teeth and the input gear, or with the second stage of teeth and the output gear, and the reduction gear wherein the input gear or the output gear meshing with the additional gears is axially offset with respect to the stage of teeth of the intermediate shafts meshing with the additional gears.

Reduction gear with input/output rotation reversal

The invention relates to a self-aligning roller bearing, comprising a rotary outer ring exhibiting a spherical raceway, the bearing comprising first and second annular rows of rollers respectively associated with first and second rotary cages that hold the rollers in place. According to the invention, the first cage has an exterior surface equipped with at least one deflector for discharging lubricant towards a first side of the bearing, in a first axial direction extending from the second cage towards the first cage, this deflector extending, in a second axial direction that is the opposite of the first direction, beyond the rollers associated with the first cage and also beyond the first cage so as to cover part of the second cage.

Self-aligning roller bearing having improved lubricant discharge, preferably for an aircraft turbojet engine speed reducer

In an aeroengine comprising a gas turbine engine driving a propeller via a reduction gearbox, the propeller comprising a plurality of blades, each provided with one or more electrical deicer elements and being set into rotation by a propeller-carrying shaft passing through the gearbox, the propeller-carrying shaft having a fastener flange for fastening to the propeller, provision is made, in order to deliver the electrical power needed for powering said electrical deicer elements, for the aeroengine to include a rotary three-phase transformer set into rotation by the propeller-carrying shaft and comprising firstly a rotor mounted inside the propeller-carrying shaft and angularly secured thereto, and secondly a stator secured to a stationary portion of the aeroengine, the rotary three-phase transformer being arranged behind the propeller fastener flange.

Growing community of inventors

Moissy-Cramayel, France

Aldric Renaud Gabriel Marie Moreau De Lizoreux