Patent ID: 7409831

Claim:
A jet engine comprising, from an upstream direction to a downstream direction, wherein the upstream and downstream directions are defined by a direction of circulation of a primary flow, said jet engine comprising: a high-pressure compressor, a diffuser grating and a combustion chamber, said high-pressure compressor comprising an external shell which radially delimits a duct for said primary flow and is connected to an annular structure extending radially outward, said diffuser grating comprising in an axial continuation of said external shell an external casing connected to a rearwardly oriented oblique strut delimiting, upstream, an end of said combustion chamber, said strut itself being connected to an external casing shell which extends in the upstream direction and is fastened to said annular structure by fastening means, said strut, said external casing shell and said annular structure defining a cavity around said diffuser grating, air bleed orifices being made in said strut in order to bring the end of the combustion chamber into communication with said cavity, said external casing shell being equipped with air bleed vents, wherein a tube is provided between an orifice in the strut and an outlet vent, a first end of said tube is mounted in said outlet vent by a connection which is free to rotate and prevented from translational movement, and a second end of said tube is mounted in said orifice by a connection which is free to rotate and free to move translationally.