Patent ID: 6976361

Claim:
An aviation turbomachine including, upstream from a afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for conveying a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers, two bends so as to flare downstream in order to slow down the primary flow F 1 downstream from said upstream injectors, wherein an annular scoop is provided around the upstream portion of said confluence sheet in order to extract a flow of air from the cold flow, this extracted flow of air being injected tangentially into the primary flow via a plurality of channels formed in the wall of said confluence sheet between the scoop and said diffuser.