Patent ID: 7506496

Claim:
An aerodynamic injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the system comprising: a tubular structure of axis XX′ that opens out at a downstream end for delivering the air/fuel mixture; at least one air feed channel that is connected to a compressor stage of the turbomachine and that opens out into the tubular structure in such a manner as to introduce air at a pressure PA into the tubular structure; an annular fuel passage that is formed in the tubular structure around its axis XX′, that is connected to at least one fuel feed channel in which fuel flows at a pressure PC, and that opens out at a downstream end into the tubular structure, forming an enlargement therein; means for injecting gas into the at least one fuel feed channel, the gas being at a pressure PG that is greater than the pressure PA and greater than or equal to PC so as to create effervescence in the fuel on being introduced into the tubular structure; at least one gas injection channel that opens out into the fuel feed channel(s) and that is connected to a gas feed duct; and an annular gas distribution cavity that is formed in the tubular structure around the fuel passage, that is connected to the gas feed duct, and that opens out into the gas injection channel.