Patent ID: 6098401
Filing Date: 2000-08-08
Classification: F02K,F23R

Abstract:
An afterburn device for a bypass turbojet engine defining a longitudinal axis of revolution and including an outer first wall disposed coaxially about said axis, an inner second wall which is also disposed coaxially about said axis and which together with said first wall defines an annular outer enclosure forming a secondary air flow duct, and an inner exhaust enclosure disposed inwardly of said second wall and separated thereby from said outer enclosure, said inner exhaust enclosure forming an exhaust duct for the escape of gases from the turbine stages of said engine, said afterburn device comprising a third wall disposed axially downstream of said first wall and said second wall to define an afterburn chamber which forms a downstream axial extension of said outer enclosure and said inner exhaust enclosure, and flame arrester means disposed between said afterburn chamber and said inner and outer enclosures, said flame arrester means comprising a plurality of substantially radial arms distributed evenly around said axis, each arm having a fixed rear part and a front part which is separable from said rear part along a median joint plane substantially perpendicular to said axis, a rotatable ring mounted for rotation about said axis at the downstream end of said first wall and to which the front parts of said arms are fixed, and drive means for rotating said ring about said axis between a first position, for dry operation, in which said front parts are joined with the rear parts of said arms and combine with said rear parts to provide said arms with streamlined profiles having low drag and zero angle of incidence, and a second position, for afterburn operation, in which said front parts are separated from said rear parts and alternate therewith circumferentially about said axis.