Snecma Moteurs

Raphael Curtelin

Guy Lapergue

Didier Georges Feder

Didier Noel Durand

Marc Doussinault

The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing. The means of cooling the divergent flaps comprise an annular plenum chamber delimited downstream by said conical shell and fed with cooling air through drillings made in a boundary wall between said plenum chamber and the downstream end of said annular passage, a plurality of distribution cells surrounding the plenum chamber and linked to the latter, said cells being delimited downstream by said conical shell and being arranged around the X axis in the planes of symmetry of the follower flaps and telescopic pipelines each linking a cell to the follower divergent flap situated in the same plane of symmetry as said cell.

Ventilation system for a convergent divergent exhaust nozzle

A device for supplying cooling air to a hollow flap of an exhaust nozzle in a turbojet engine. The device includes a tube connecting the hollow flap to a cooling air source. The tube comprises at least one telescopic portion and at least one ball-joint connection.

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Saint Mery, France

Raphael Curtelin