Safran Aircraft Engines

Thomas Gerard Daniel Riviere

Caroline Marie Frantz

Nicolas Xavier Trappier

Antoine Elie Hellegouarch

Romain Jean-Claude Ferrier

Nora El Ghannam

Matthieu Etienne Attali

The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.

Turbine engine having horizontally offset axes

The invention relates to a system for suspending two modules of a propulsion unit, such as two fan modules, said system comprising a pylon () and a rudder bar (). One part (') of the rudder bar is hinged to the pylon, while the opposing ends thereof are hinged to connecting rods (). The system also comprises a torque bar () which has an elongate shape and is mounted on the pylon such that it can pivot about an axis substantially parallel to an axis (B) of elongation of the torque bar, the opposing ends () of said bar being secured on each side of the above-mentioned part of the rudder bar.

System for suspending two modules of a propulsion unit

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Noise-le-Grand, France

Thomas Gerard Daniel Riviere