Safran Aircraft Engines

Snecma

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Hispano Suiza

Jean-Pierre Galivel

Jacky S Naudet

Jean-Louis Charbonnel

Frédéric Dautreppe

Jean-Claude L Delonge

Guy Dusserre-Telmon

Guy Franck Dusserre-Telmon

Zoltan Zsiga

Gerard R Vermont

Jean-Christophe M Cordier

Laurent Gille

Thierry Henri Tassin

Samuel Becquerelle

Corrine G Delahaye

Régis Servant

Didier M Nouveau

An aircraft turbomachine module, including an accessory gearbox, a transfer shaft, and a drive shaft rotatably connected with one another by a power transmission device. The power transmission device can be housed in a gearbox and the module can further include an electric machine rotatably connected to the transfer shaft. The electric machine can be interposed between the transmission housing and at least one part the transfer shaft.

Turbomachine module equipped with an electric machine, and turbomachine equipped with such a module

A method of determining the angular position of a first rotor of a turbojet. A vibration pulse is generated during a rotation of the first rotor, each vibration pulse being generated when the first rotor passes through a given reference angular position. The vibration generated is detected. The angular position is obtained at a given instant of a second rotor of the turbojet relative to the angular position that it occupied at a reference instant representative of detecting a vibration pulse. The second rotor is coupled in rotation with the first rotor and has a speed of rotation different from the speed of rotation thereof. The angular position of the first rotor at the given instant is determined from the angular position of the second rotor.

Method and system for determining the angular position of a turbojet engine rotor

A device for ensuring the sealing in a rotary machine between a rotor and fixed blade stages. Blade edges are joined by rings carrying circular seals in slots. Springs force the seals in the longitudinal direction towards transverse faces of reinforcements of the rotor. A turbulence-free gas flow is obtained as a result of the total seal obtained by the seals (19). Moreover, the rotor can be constructed with a substantially rectilinear ferrule which only induces limited stress concentrations.

Sealing device between blade stages and a rotary drum, particularly for

Growing community of inventors

Savigny-Le-Temple, France

Jean-Pierre Galivel