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

An injection system for injecting an air and fuel mixture in a turbomachine combustion chamber, comprising:

• a sleeve for centering an injector;
• a bowl;
• a first air intake swirler axially arranged between the sleeve and the bowl;
• and
• a second air intake swirler axially arranged between the first air intake swirler and the bowl, each of the first and second air intake swirlers comprising an upstream wall and a downstream wall along a flow direction of gas primary flow, both the upstream wall and the downstream wall being 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 downstream and upstream walls air inlet channels each having an inlet arranged on a radially outer side and an outlet arranged on a radially inner side,
• wherein the downstream wall of the first air intake swirler is the upstream wall of the second air intake swirler,
• wherein each of the first and second air intake swirlers further includes a respective aerodynamic deflector which is an outwardly radial extension of the downstream wall of the corresponding air intake swirler and is terminated with a free end, each respective aerodynamic deflector having a concavity pointing upstream along the flow direction of the gas primary flow such that the aerodynamic deflector extends radially facing the respective inlets of the air inlet channels of the corresponding air intake swirler, and
• wherein at least one of the respective aerodynamic deflectors of the first and second air intake swirlers is shaped such that a radial extent of an air inlet section of the corresponding air intake swirler varies about the axis.