Snecma

Aircelle Limited

Safran Aircraft Engines

Safran Nacelles

Centre De Recherche En Aeronautique Asbl - Cenaero

Sébastien Pascal

Denis Guillois

Jonathan Langridge

Irwin Kernemp

Gérard Clere

Loïc Chapelain

An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors facing each other between two lateral beams. The doors pivot around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of the doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which the middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases. The edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody.

Afterbody for a turbojet engine comprising a nozzle provided with a thrust reverser system that incorporates a crown of noise-reducing chevrons

Growing community of inventors

Moissy-Cramayel, France

Sébastien Pascal