Safran Helicopter Engines

Nicolas Roland Guy Savary

Stéphane Lavignotte

Jean-Paul Didier Autret

Olivier Lamaison

Thomas Sebastien Alexandre Gresy

Hubert Pascal Verdier

Yvan Ludovic Lameignere

Guillaume Thierry Cottin

Chritophe Nicolas Henri Viguier

Christophe Lailhacar

Claude Marie Michel Berat

Mehdi Deliba

Thomas Sébastien Alexandre Gresy

A method for manufacturing a flame tube for a turbomachine, the flame tube extending about an axis and comprising an annular radially internal wall and an annular radially external wall, connected to each other by an end wall or head wall, the internal wall, the external wall and the end wall defining an internal volume, at least one part of the said end wall forming a double wall comprising a first part and a second part connected to each other and spaced apart from each other so as to delimit a flow channel for a flow of cooling air opening into the said internal volume, the said flow channel comprising at least one air-inlet opening, the first and second parts of the double wall being connected by connecting zones or bridges extending into the flow channel for the cooling-air flow, the flame tube being manufactured by additive manufacturing.

Method for manufacturing a flame tube for a turbomachine

A double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams, outside the external wall, which cool the internal wall. The internal wall being free of perforations to prevent any circulation of a cooling air stream towards the centre of the combustion chamber. The the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.

Double wall for aircraft gas turbine combustion chamber and method of producing same

A combustion assembly for a gas turbine includes a flame tube and a fuel supply including a flow rate limiter supplying an injector. The flow rate limiter and the fuel injector are formed in one piece.

Integral flow rate limiter and fuel injector for a gas turbine combustor

A gas turbomachine combustion chamber includes bridges extending side by side to connect in one piece a radially inner wall and a radially outer wall towards a free end of the radially inner wall. The bridges, inner wall, and outer wall have an additive layer structure.

Production by additive manufacturing of complex parts

The invention relates to a pre-vaporizing pipe () for a combustion chamber of a turbomachine, comprising a generally elongate main body (), comprising a first end portion () delimiting an inlet duct () in which a fuel injector is to be mounted, the body () having an external surface () having a first length (L) that extends from the portion () to at least one first fuel outlet end piece (), and a second length (L) that extends the first length (L) from the end piece () and that extends from the end piece () to a second fuel outlet end piece (). According to the invention, inside the body () there is a first channel () connecting the duct () to the end piece () and a second channel () which is distinct from the first channel () and which connects the duct () to the end piece ().

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Moissy-Cramayel, France

Nicolas Roland Guy Savary