Safran Aircraft Engines

Guillaume Aurelien Godel

Romain Nicolas Lunel

Haris Musaefendic

Christophe Pieussergues

Thomas Olivier Marie Noel

Alain Rene Cayre

Matthieu Francois Rullaud

Francois Pierre Georges Maurice Ribassin

A turbine engine combustion chamber including: an outer annular housing; a flame tube connected to the outer housing. The flame tube includes an inner annular wall and an outer annular wall and a second axial outlet portion of the flame tube. The flame tube also includes a chamber base located at the inlet of the flame tube; and a fuel injection system configured to inject fuel into the flame tube via the inlet of the flame tube. The injection system includes an injector axis, and an air manifold to move air towards twists in the injection system. The twists are arranged around an implantation axis. The air manifold includes a circular portion around the injector axis. The circular portion, forms an air inlet of the manifold. The opening places the entering air flow in rotation about the implantation axis.

Bent combustion chamber from a turbine engine

An air intake swirler for a turbomachine injection system includes an upstream wall and a downstream wall, both of revolution about an axis of the air intake swirler, and fins distributed about the axis and connecting the upstream wall to the downstream wall so as to delimit, between the upstream wall and the downstream wall, air inlet channels each having an inlet and an outlet. The swirler includes two aerodynamic deflectors that respectively extend the downstream walls radially outward and that have a concavity oriented upstream. The aerodynamic deflectors extend radially facing the respective inlets of the air inlet channels and thus make it possible to limit the loss of pressure of the air supplied to the air inlet channels.

Air intake swirler for a turbomachine injection system comprising an aerodynamic deflector at its inlet

A combustion chamber of a turbomachine includes an annular outer casing and a flame tube connected to the outer casing. The flame tube includes an annular inner wall and an annular outer wall defining a first, radial portion at the inlet of the flame tube and a second, axial portion at the outlet of the flame tube. The first portion extends towards the second portion forming an elbow between the inlet and the outlet of the flame tube.

Elbowed combustion chamber of a turbomachine

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Moissy-Cramayel, France

Guillaume Aurelien Godel