Abstract: The invention relates to a dual-flow turbojet engine comprising an engine which is disposed in a nacelle and is provided with case which defines jointly with the said nacelle an annular passage through which a secondary flow supplied by a fan placed upstream of the engine can flow, a primary nozzle which is fixed to the case downstream of the engine, an internal wall for guiding the main hot flow supplied by the engine and an external wall contacting the secondary flow. Said invention is characterized in that sound attenuating means is provided for at least one part of the internal wall and the external wall is provided with means for cooling said internal wall.

Abstract: The present invention relates to a nacelle (1) of a turbojet engine (4), which nacelle is intended to be attached to a structure (2) of an aeroplane by a connecting pylori (3) and comprises at least one moving part (9?, 9?) above to be opened in order to provide access to the interior of the nacelle, characterized in that the said moving part is mounted to pivot about a pivot axis (25) directed along a line more or less perpendicular to the plane of the structure of the aeroplane to which the nacelle is attached.

Abstract: A turbojet-engine thrust reverser is provided with thrust reverser door assemblies each having a pivoting thrust reverser door (7). The thrust reverser door is connected to two pivots (22, 23) that rest on a support fitting (24) to constitute a structural frame that is attached to longitudinal beam cowling portions (20, 21) and a downstream cowling portion (3) of a stationary thrust-reverser structure in order to constitute a rigid assembly between the upstream and downstream cowling portions (4, 3). At least one primary mechanical lock (26) is placed on at least one longitudinal side of the door (7) and the interface loads of the lock (26) are absorbed by the beam cowling portions (20, 21).

Abstract: A thrust reverser for a turbojet engine is provided with at least one displaceable assembly including a displaceable cowling portion and a flap. The displaceable cowling portion and the flap each subtend stationary upstream and downstream cowling portions such that the displaceable cowling portion forms a portion of the external engine cowling covering a reverse thrust opening and the flap forms a portion of the outer boundary of the gas flow in a forward thrust position. In a reverse thrust position, the reverse thrust opening is uncovered, and the displaceable cowling portion and the flap are displaced downstream such that the displaceable cowling portion extends downstream, parallel to the longitudinal engine axis and above, without interference, the downstream cowling portion.