Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Eric Conete

Gerard E Jourdain

Christophe J Thorel

Didier L Auffret

Frederic Delage

Gerard C Berger

Frederic Paul Eichstadt

An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body of revolution about the central axis, which casings are integrally joined by a plurality of connecting arms extending between the inner and outer casing. The connecting arms are also formed of a composite material and are integrally molded with both the inner and outer casings. The afterburner structure also has a plurality of secondary support arms formed of composite material which extend either from the outer, or the inner casing in a generally radial direction relative to the central axis. Integrally formed with the plurality of secondary support arms is at least one annular flameholder ring which extends around the central axis and is supported by the secondary support arms.

Integral composite gas turbine afterburner structure

An afterburner assembly is disclosed in which the flameholder ring is for by plurality of flameholder ring segments, each segment being integrally formed with a generally radially extending arm. The flameholder ring segments extend beyond each opposite sides of the arm. The arm and flameholder ring segments are attached to the casing of the afterburner by a support element which is pivotally attached to the arm and fixedly attached to the afterburner casing. The distal end of the arm slidably contacts the casing defining the opposite side of the afterburner duct to enable the arm to slide relative to the casing to allow for differential thermal expansion of the respective elements. When each of the arm/flameholder ring segments are attached to the afterburner casing, the flameholder ring segments form a generally annular flameholder ring. The ring has a generally 'U'-shaped cross-sectional configuration with the legs of the 'U'-shape extending generally parallel to a central axis and opening in a downstream direction according to the gas flow flowing through the afterburner duct.

Afterburner assembly for a gas turbine engine

A variable geometry flame trap device for use in an after-burner device of a gas turbine, which is not exposed to deformation forces during its use in the after-burner mode. This is achieved with a plurality of flame trap plate pairs (21), positioned downstream of the turbine at the outlet of a primary air flow duct (9) and mounted so as to pivot on a plurality of diffuser arms (19) located at the outlet of a secondary air flow duct (7), characterized in that the plates (21) of each pair are made from a composite material and in that they have a cam projecting from their facing faces (42), said two cams (43) bearing on one another.

Growing community of inventors

Le Mee S/Seine, France

Eric Conete