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 integrated exhaust nozzle and thrust reverser for a turbojet engine is provided. The exhaust nozzle comprises an exhaust duct situated within a fairing (9), a set of hot flaps (14) at a downstream end of the duct, a set of cold flaps (16) at a downsteam end of the fairing (9), and a thrust reverser (30). The thrust reverser comprises two eyelids (31, 32) which are movable between a thrust reversal position wherein they project into the duct and a forward-thrust position. In a takeoff mode, the eyelids (32, 33) are moved away from each other by one or more actuators (50) acting on arms (33, 34) pivotably connected to the eyelids (31, 32). Movement of the eyelids (31, 32) from the reverse-thrust position to the forward-thrust position, or vice-versa, is implemented by control actuators (35, 36).