Integral composite gas turbine afterburner structure

US5367874A · kind A · utility

Assignee

• Societe Nationale d'Etude et de Construction de Moteurs d'Aviation - S.N.E.C.M.A · FR

Inventors

• Didier L. C. Auffret · Combs-la-Ville, FR
• Gerard C. L. Berger · Épinay-sous-Sénart, FR
• Eric Conete · Mérignac, FR
• Frederic Delage · Paris, FR
• Gerard E. A. Jourdain · Saint-Pierre-du-Perray, FR
• Christophe Thorel · Paris, FR

Key dates

• Filing date: Dec 8, 1993
• Grant date: Nov 29, 1994
• Expiry date: Dec 8, 2013

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F23R3/20
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

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.