Snecma

Snecma Moteurs

Sébastien Baboeuf

Alain Pierre Page

Jacques Roche

Thierry Cortes

Sabine Charpenel

Eric Maingre

The after-burner device receives a 'hot' central primary flow from the turbine of the turbojet and a 'cold' peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of the primary flow is brought into the after-burner ignition zone in order to raise the temperature in said zone to a value that is higher than that of the secondary flow so as to encourage after-burner ignition.

Method of improving the ignition performance of an after-burner device for a bypass turbojet, and an after-burner device of improved ignition performance

The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the 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 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 Fdownstream from said upstream injectors. 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, said extracted flow 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.

Ventilation channels in an afterburner chamber confluence sheet

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Avon, France

Sébastien Baboeuf