Safran Aircraft Engines

Jean-Claude Christian Taillant

Laurent Jablonski

Julien Fabien Patrick Becoulet

Caroline Marie Frantz

Régis Eugène Henri Servant

Paul Ghislain Albert Levisse

Tewfik Boudebiza

Clément Cottet

Didier Gabriel Bertrand Desombre

Patrick Jean Laurent Sultana

Pierre-Alain Jean Philippe Reigner

Wilfried Lionel Schweblen

Emmanuel Fabrice Marie Baret

Vianney Simon

Patrick Claude Pasquis

Patrice Jean-Marc Rosset

Stephane Pierre Guillaume Blanchard

A fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil transfer device for transferring oil between a stator and a rotor, the device including a stator ring having a cylindrical inner surface and internal oil ducts and a shaft engaged in the ring and having a cylindrical outer surface and internal oil ducts; the device includes a plain bearing located between said cylindrical inner surface and the cylindrical outer surface and defined by a single band; and rolling bearings mounted between the ring and the shaft, on either side of the plain bearing, each of these rolling bearings having one of the rings thereof integrated in one of the elements selected from the ring and the shaft.

Fan module equipped with an oil transfer device

The present invention relates to a rotating assembly of a turbomachine, comprising: —a shaft configured to drive a propeller of the turbo machine around an axis and comprising a first flange radially extending from the shaft, the first flange being monolithic with the shaft; —a sleeve fitted onto the shaft and comprising a second flange radially extending from the sleeve, the sleeve being attached to the first flange of the shaft by means of the second flange; and —at least one component connected to the shaft by means of the sleeve so as to be rigidly connected to the shaft to move therewith, the component comprising at least one sealing element.

Sleeve mounted onto a low-pressure shaft in a turbomachine

A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine, includes a blade having a vane connected to a root. A hub accommodates the root of the blade, and a ring is mounted around the root and in the hub. Stops are also mounted around the root and in the hub. A nut is threadedly engaged with a thread of the ring and is configured to bear axially against the hub to secure the assembly.

System for controlling the pitch setting of a propeller vane for an aircraft turbine engine

A turbomachine for an aircraft comprising a stator, a turbine shaft and an electric machine arranged to the rear of the turbine shaft, and comprising an electric machine stator and an electric machine rotor, a rotationally fixed coupling carriage capable of moving in axial translation relative to the electric machine rotor between coupled and uncoupled positions, coupling members which are designed to engage with one another after the coupling carriage has moved from the uncoupled position to the coupled position and to transmit a torque from the turbine shaft to the electric machine rotor when they are engaged, and an elastic return member designed to elastically return the coupling carriage in axial translation to the coupled position.

Aircraft turbomachine comprising an electric machine

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Moissy-Cramayel, France

Jean-Claude Christian Taillant