Safran Aircraft Engines

Benjamin Frantz Karl Villenave

Jacques Marcel Arthur Bunel

William Louis Rodolphe Dousse

Dan Ranjiv Joory

Dan-Ranjiv Joory

Romain Nicolas Lunel

Christophe Pieussergues

Dominique Raulin

Damien Bonnefoi

Luc Namer

A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.

Fastening for a turbomachine combustion chamber

A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.

Combustion chamber for a turbomachine

The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall () and a wall made of a refractory material (). A device () guides a spark plug () in said two orifices, the guiding device comprising a metal flange () and a floating ring (), the flange being shrunk onto or welded to the metal wall ().

Spark plug for a single-piece combustion chamber

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.

Growing community of inventors

Moissy-Cramayel, France

Benjamin Frantz Karl Villenave