Patent ID: 7866141

Claim:
A dual-flow turbojet engine comprising an engine housed in a nacelle, said engine comprising a casing defining with the nacelle an annular passage in which a secondary flow supplied by a fan situated upstream of the engine can flow, a primary nozzle being fixed on the casing downstream of the engine and comprising, on the one hand, an internal wall able to channel a principal hot flow supplied by the engine and, on the other hand, an external wall in contact with the secondary flow, wherein sound attenuation means equip at least a part of the internal wall, and in that the external wall comprises means for cooling the internal wall, and the means for cooling the internal wall including means of taking in cooling air from the secondary flow, at least one ducting means that allows the cooling air to flow over the sound attenuation means, disposed between the means of taking in cooling air and a means of distributing cooling air to a location spaced from the sound attenuation means.