Effervescence injector for an aero-mechanical system for injecting air/fuel mixture into a turbomachine combustion chamber
View Patent ↗A fuel injector for an aero-mechanical injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the injector comprising a main tubular structure of axis XX′ opening out at a downstream end for delivering the air/fuel mixture, a tubular fuel duct that is disposed inside the main structure and that opens out into the main structure via a fuel atomizer plug so as to introduce fuel into the main structure at a pressure P C into the main structure, at least one air feed channel that opens out into the main structure so as to introduce air at a pressure P A therein, and means for injecting into the fuel duct a gas at a pressure P G that is greater than P A and greater than or equal to P C so as to create effervescence in the fuel on being introduced into the main structure.
1. A fuel injector for an aero-mechanical injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the injector comprising:
a main tubular structure, with an axis of revolution XX′, opening out at a downstream end for delivering the air/fuel mixture;
a tubular fuel duct disposed inside the main structure so as to co-operate therewith to form an annular passage, and opening out at a downstream end into the main structure via a fuel atomizer plug so as to introduce fuel at a pressure P C into the main structure; and
at least one air feed channel connected to a compressor stage of the turbomachine and opening out into the annular passage in such a manner as to introduce air at a pressure P A into said passage;
the injector further including a tubular gas duct disposed inside the fuel duct and having a plurality of orifices opening out into said fuel duct to inject therein a gas at a pressure P G that is greater than P A and greater than or equal to P C so as to create effervescence in the fuel on being introduced into the main structure, the orifices of the gas duct being disposed in at least one common plane transverse to the axis of revolution XX′, and the orifices of the gas duct opening out into the fuel duct through the fuel atomizer plug, wherein the tubular gas duct is the inner most duct.
2. The injector according to claim 1 , wherein the orifices of the gas duct open out substantially perpendicularly into the fuel duct.
3. The injector according to claim 1 , wherein the fuel atomizer plug comprises a cylindrical portion centered on the axis XX′, having an outside diameter that is smaller than the inside diameter of the fuel duct, and provided with a plurality of profiled fins extending radially outwards, said fins having outside surfaces coming into contact with an inside surface of the fuel duct.
4. The injector according to claim 3 , wherein the profiled fins of the fuel atomizer plug are distributed regularly over the entire circumference of the cylindrical portion.
5. The injector according to claim 3 , wherein the profiled fins of the fuel atomizer plug present angular twist in a common direction.
6. The injector according to claim 5 , wherein the angular twist of the profiled fins is at about 45° relative to the axis XX′.
7. The injector according to claim 3 , wherein the orifices of the gas duct open out into the fuel duct through the fuel atomizer plug between pairs of adjacent fins thereof.
8. The injector according to claim 7 , wherein the orifices of the gas duct open out tangentially into the gas duct.
9. The injector according to claim 1 , further comprising a device for controlling the flow rate of the gas injected into the fuel duct.
10. An aero-mechanical injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the system comprising a fuel injector according to claim 1 , and means for injecting air downstream from the fuel injector.
11. A system according to claim 10 , including an inner air swirler disposed downstream from the injector configured to enable air to be injected in a radial direction, an outer air swirler disposed downstream from the inner air swirler, and configured to inject air in a radial direction, a Venturi interposed between the inner and outer air swirlers, and a bowl mounted downstream from the outer air swirler.
12. A system according to claim 10 , comprising an inner air swirler disposed downstream from the injector and configured to enable air to be injected in a radial direction, an outer air swirler disposed downstream from the inner air swirler and configured to enable air to be injected into a radial direction, a first Venturi interposed between the inner and outer air swirlers, a second Venturi disposed downstream from the outer air swirler, and at least one of a pre-mixer or a pre-vaporization tube disposed downstream from the second Venturi.
13. A turbomachine combustion chamber including a fuel injector according to claim 1 .
14. A turbomachine including a combustion chamber fitted with a fuel injector according to claim 1 .
15. The injector according to claim 1 , wherein the gas duct and the fuel atomizer plug are a single piece.
16. The injector according to claim 1 , wherein an air swirler is disposed in the annular passage between an upstream end of the main structure and the downstream end of the main structure.
17. The injector according to claim 16 , wherein the air swirler is configured to impart a rotary effect to the air introduced into the annular passage.
18. The injector according to claim 5 , wherein an air swirler is disposed in the annular passage between an upstream end of the main structure and the downstream end of the main structure,
said air swirler is configured to impart a rotary effect in the common direction of angular twist of the profiled fins of the fuel atomizer plug to the air introduced into the annular passage.