Abstract: An aerodynamic injection system for injecting an air/fuel mixture into a turbomachine combustion chamber comprises 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 opens out into the structure so as to introduce air at a pressure PA therein, an annular fuel passage that is formed in the structure around its axis XX?, that is connected to at least one fuel feed channel in which there flows fuel at a pressure PC, and that opens out at a downstream end into the structure, and means for injecting gas into the at least one fuel feed channel, said gas being at a pressure PG that is greater than PA and greater than or equal to PC so as to create effervescence in the fuel on being introduced into the structure.

Abstract: An aerodynamic injection system for injecting an air/fuel mixture into a turbomachine combustion chamber comprises 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 opens out into the structure so as to introduce air at a pressure PA therein, an annular fuel passage that is formed in the structure around its axis XX?, that is connected to at least one fuel feed channel in which there flows fuel at a pressure PC, and that opens out at a downstream end into the structure, and means for injecting gas into the at least one fuel feed channel, said gas being at a pressure PG that is greater than PA and greater than or equal to PC so as to create effervescence in the fuel on being introduced into the structure.