Patent ID: 7296397

Claim:
A bypass turbojet comprising an afterburn chamber of axis X delimited by an annular wall situated radially inside an annular casing, said annular wall and said casing defining an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber and comprising a circle of convergent flaps hinged at the downstream end of said casing and a circle of divergent flaps hinged at the downstream end of said convergent flaps, 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 said casing, means for creating a film of cooling air on the internal faces of said convergent flaps and means of cooling said divergent flaps, wherein the means of cooling said 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.