Safran Aircraft Engines

Dan Ranjiv Joory

Benjamin Frantz Karl Villenave

Jacques Marcel Arthur Bunel

William Louis Rodolphe Dousse

Romain Nicolas Lunel

Christophe Pieussergues

Dominique Raulin

Patrice André Commaret

Damien Bonnefoi

Luc Namer

The invention concerns a turbo engine comprising a combustion chamber () arranged inside the outer housing () and comprising an internal revolution wall () and an external revolution wall (). First stop parts () and second stop parts () fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs ().

Combustion module for a gas turbo engine with chamber bottom stop

A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.

One-piece combustion chamber

A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.

Production of a combustion chamber made of composite material

Growing community of inventors

Moissy-Cramayel, France

Dan Ranjiv Joory