Safran Aircraft Engines

Jérémy Dievart

Michel Gilbert Roland Brault

Julien Fabien Patrick Becoulet

Arnaud Nicolas Negri

Nathalie Nowakowski

Romain Guillaume Cuvillier

Guillaume Patrice Kubiak

Serge René Morreale

Nils Edouard Romain Bordoni

Yanis Benslama

Alexandre Jean-Marie Tan-Kim

Dominik Igel

A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.

Dual-flow turbojet engine arrangement with epicyclic or planetary reduction gear

A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.

Fan module with variable-pitch blades for a turbine engine

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Moissy-Cramayel, France

Jérémy Dievart