Patent ID: 6112516
Filing Date: 2000-09-05
Classification: F23R

Abstract:
An afterburner for a bypass turbojet-engine, comprising:a substantially annular outer duct (20) having a longitudinal axis (21);an exhaust duct (22) contained within the outer duct (20), the exhaust duct (22) including an outer annular wall (25) and an inner annular wall (26) each having the same longitudinal axis (21) as the outer duct (20);a first passage (24) for a flow of bypass air which is defined by the outer duct (20) and the outer annular wall (25);a second passage (27) for a flow of combustion gases which is defined by the outer annular wall (25) and the inner annular wall (26);an annular afterburner wall (28) mounted inside the outer duct (20) and spaced a given distance therefrom to define a cooling-air passage therebetween, the afterburner wall (28) also having the same longitudinal axis 21 as the outer duct (20);an afterburner chamber (23) located downstream of the first and second passages (24, 27), the afterburner chamber (23) being defined by the afterburner wall (28);a plurality of flameholders (30) extending in radial planes relative to the longitudinal axis (21) at least inside the second passage (27), each of the flameholders (30) comprising two outer dihedral plates (35, 36) which intersect at a common ridge apex (37) to form a dihedral shape having a V-shaped outer cross section with the ridge apex directed upstream relative to a generally axial flow direction (G) of the combustion gases;at least one radial fuel conduit (44, 45) disposed within each of the flameholders (30), the at least one fuel conduit including fuel injection orifices which inject fuel in a downstream direction; andan air tube (38) supplied with pressurized air disposed within each of the flameholders (30), the air tube (38) having multiple orifices (41) directed so as to discharge air against and cool the outer plates (35, 36), the air tube (38) having an approximately triangular overall cross-section and comprising two sides (39, 40) which extend substantially parallel to the outer plates (35, 36) and a downstream transverse curved side wall (42) which forms a radial trough (43) for receiving the at least one fuel conduit (44, 45), the downstream wall (42) having a plurality of additional orifices (46) directed toward the at least one fuel conduit (44, 45) to discharge air against and cool the at least one fuel conduit (44, 45).