Safran Aircraft Engines

Damien Bonnefoi

Romain Nicolas Lunel

Christophe Pieussergues

Dominique Raulin

Damien Bonneau

Benjamin Frantz Karl Villenave

François Xavier Chapelle

Dan Ranjiv Joory

Julien Michel Tamizier

Christophe Bernard Texier

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 turbomachine includes a combustion chamber with a radially extending downstream flange at its downstream end. A distributor is disposed downstream of the combustion chamber and includes a platform from which at least one vane extends radially. The platform has an upstream edge extending radially and delimiting, with the downstream flange disposed opposite, a gap opening into the combustion chamber at its radially inner end and closed at its radially outer end by sealing means fixed to the distributor. The downstream flange of the combustion chamber has at least one rectilinear cooling orifice passing through the flange and opening into the gap opposite the platform of the distributor.

Assembly for a turbomachine

Growing community of inventors

Moissy-Cramayel, France

Damien Bonnefoi