Safran Aircraft Engines

Snecma

Arianegroup Sas

Nicolas Ravier

Gérard Roz

Noël David

Dominique Le Louedec

Bruno Bucher

Frederick Millon

Olivier Dobek

Michel Fiolek

Romain Stephant

Jacques Lelong

Arnaud Sternchuss

Stéphanie Dreyer

Lauren Nguyen Duc

David Hayoun

A holding system () for holding at least one pipe, comprising a comb including a bar and parallel teeth perpendicular to the bar. A blocking device () consisting essentially of a pin, serves to prevent a pipe passing between two of the teeth from moving away from the bar. The holding system further comprises two supports (A,B), positioned at the ends of the comb, and which hold the comb so as to allow rotation thereof around the axis of the bar. A method for mounting a heat exchanger () comprising such a holding system.

Pipe supporting system

The device comprises two heat exchangers () suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (). The heat exchangers co-operate respectively with first and second gas generators () suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator () being suitable for being fed at least in part by the exhaust from the first gas generator ().

Device for pressurizing propellant tanks of a rocket engine

A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.

Convex thermal shield for rocket engine with extendable divergent nozzle

Growing community of inventors

Vernon, France

Nicolas Ravier