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

Pascal Michel Le Jeune

Xavier Jean Guyonnet

Philippe Louis Alassoeur

An afterburn device for a turbojet engine comprises a flame arrester formed by a plurality of radial arms distributed evenly around the rotational axis of the engine at the upstream end of the afterburn chamber. Each arm consists of a fixed rear part, and a front part which is separable from the rear part in a circumferential direction along a median joint plane, the front parts being carried on a ring which is rotatably mounted on the outer casing of the engine. Drive means is provided for rotating the ring between a first position for dry operation, and a second position for afterburn operation. In the first position the front and rear parts of the arms are aligned and joined to provide the arms with a streamlined, low-drag, zero angle of incidence profile suitable for dry operation. In the second position the front parts of the arms are separated circumferentially from the rear parts so as to alternate with the rear parts, the front and rear parts creating turbulence which acts to arrest the flame during afterburn operation.

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Samoreau, France

Pascal Michel Le Jeune