Abstract: The invention relates to a method and a device for protecting fuel injectors in a turboshaft engine. The protection is carried out by injecting compressed air directly into the injectors. The air thus directly purges the injectors and evacuates the fuel present in them into the combustion chamber.

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: The invention relates to a method and a device for protecting fuel injectors in a turboshaft engine. The protection is carried out by injecting compressed air directly into the injectors. The air thus directly purges the injectors and evacuates the fuel present in them into the combustion chamber.

Abstract: 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 PC 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 PA therein, and means for injecting into the fuel duct a gas 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 main 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.