Fuel injection device for a gas turbine.

摘要

1. Fuel injection assembly for a combustion chamber of a turbo-jet engine in which a single array of swirl blading (2) for rotationally impelling a flow of air, is constituted by a centripetal blading array discharging into a cylindrical space disposed downstream of an injection device so as to break up the droplets of fuel by the swirling air flow, characterized in this that the said cylindrical space is extended by a tubular duct (3) connected downstream to a conical bowl (4) and in this the said injection device is formed by a hollow cylindrical body of which the base (6) comprises a fuel inlet (7) and the hood (8) of the infection orifices (5) projects for the passage of the fuel so that the transverse outlet plane of the orifices (5) is very close to the plane of the upstream end of the blading array (2).