Patent ID: 7568345

Claim:
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.