AIR INLET STRUCTURE FOR A TURBOJET ENGINE NACELLE OF LAMINAR TYPE

摘要

An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.

主权项

1. An air inlet structure for a turbojet engine nacelle comprising:
at least one inner panel fastened to a fan casing of the turbojet engine, said at least one inner panel forming an inner fixed part of said air inlet structure; and at least one outer mobile panel configured to translate along a substantially longitudinal direction of the nacelle, said at least one outer mobile panel integrating a portion of an air inlet lip configured to provide a junction between said at least one inner panel and said outer mobile panel, wherein said portion of the air inlet lip and said at least one inner panel each have a junction end, and each of the junction ends is equipped with an acoustic attenuation panel, and wherein at least one of the junction ends is equipped with at least one radial buffer configured to come into contact with a corresponding junction flange carried by other junction end when the outer mobile panel is in a closed position.