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

Christophe J Thorel

Gerard E Jourdain

Eric Conete

Gerard C Berger

Didier L Auffret

Frederic Delage

Bruno Albert Beutin

Jean-Marie N Pincemin

Michel G Hugues

Gilles Claude Massot

Carole Claudine Touron

Francis Georges Garnier

Claude P Maignan

Jean-Loic H Lecordix

Jean-Pierre Donnadieu

Joel Creti

Gerard M Vennin

A system is disclosed for regulating oil and fuel temperatures in a turbojet engine having an engine accessory driven at constant speed by a power transmission which is driven by the turbojet engine. The system has a first closed oil circuit for circulating oil through the turbojet engine, a second closed oil circuit for circulating oil through the power transmission, a fuel circuit for supplying fuel to the turbojet engine, an air/oil heat exchanger connected to the first closed oil circuit to pass oil in heat exchange relationship with air, an oil/fuel heat exchanger connected to the fuel circuit and to the first closed oil circuit downstream of the air/oil heat exchanger to pass oil and fuel in heat exchange relationship, and an oil/oil heat exchanger connected to the first and second closed oil circuits to pass oil in heat exchange relationship, the connection to the first closed oil circuit being downstream of the oil/fuel heat exchanger.

System for regulating oil and fuel temperatures of a turbojet engine

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

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Paris, France

Christophe J Thorel