Safran Aircraft Engines

Faouzi Aliouat

Jacques Marcel Arthur Bunel

Bruno Alexandre Didier Jacon

Baghdad Achbari

Hervé Simonotti

Etienne Gérard Joseph Canelle

An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.

Air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element, and a nacelle element

A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.

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Moissy-Cramayel, France

Faouzi Aliouat