Injection system for a turbine engine combustion chamber configured for direct injection of two coaxial fuel flows

1. An injection system for a turbine engine combustion chamber comprising:

a double flow injector with an injection head opening up into an internal space in the injection system, the injection head injecting a primary fuel flow and a secondary fuel flow surrounding said primary fuel flow into the internal space, the primary and secondary fuel flows being conical and centered on a same injection axis;

a swirler comprising channels configured to generate an air flow swirling about said injection axis on a downstream side of said injection head to be mixed with the primary and secondary fuel flows from the injection head, said swirler comprising a downstream transverse surface delimiting said channels at a downstream end and forming an upstream face of a downstream transverse wall of the swirler;

a bowl extending from the downstream transverse wall of the swirler towards a downstream direction;

first orifices formed through the bowl for the formation of an air film along an inside surface of the bowl; and

a first annular deflector surrounded by the bowl and extending in the downstream direction from the downstream transverse surface of the swirler and having a free downstream end offset in the upstream direction from a downstream end of the bowl, to guide said air film,

wherein an internal radius of a cross section of the first annular deflector continuously increases from the downstream transverse surface of the swirler as far as the downstream end of the first annular deflector, and wherein the first annular deflector delimits the outside of the internal space from the downstream transverse surface of the swirler as far as the downstream end of the first annular deflector.

2. The injection system according to claim 1 , wherein an internal radius of a cross section of the bowl increases from the downstream transverse wall of the swirler as far as the downstream end of the bowl.

3. The injection system according to claim 1 , wherein the first orifices are oriented in a first circumferential direction such that said air film swirls around said injection axis in the same direction as the air flow originating from the swirler.

4. The injection system according to claim 3 , further comprising second orifices formed through the bowl downstream from said first orifices, and oriented along a second circumferential direction contrary to said first circumferential direction.

5. The injection system according to claim 1 , wherein the channels in the swirler are distributed in a single annular row.

6. The injection system according to claim 1 , wherein the first orifices open up facing the first annular deflector.

7. The injection system according to claim 1 , further comprising a second annular deflector having a downstream end connected to the bowl and a free upstream end, the second annular deflector extending facing the first orifices and being closer to the bowl than the first annular deflector.

8. The injection system according to claim 7 , wherein the upstream end of the second annular deflector extends between the downstream end of the first annular deflector and the bowl.

9. A combustion chamber for a turbine engine, including at least one injection system according to claim 1 .

10. A turbine engine for an aircraft, including at least one combustion chamber according to claim 9 .

11. The injection system according to claim 1 , wherein each channel extends along an average direction inclined from a radial direction defined relative to the injection axis at positive angle in a clockwise direction.

12. The injection system according to claim 1 , wherein the swirler, the bowl, and the first annular deflector are formed as a single monolithic piece.