Patent ID: 8740137
Filing Date: 2014-06-03
Classification: B64D,F02C,F05D,Y02T

Abstract:
1. A nacelle for a turbojet comprising: an air intake structure capable of channeling an air flow toward a fan of the turbofan, a middle structure surrounding said fan and to which the air intake structure is attached so as to provide an aerodynamic continuity, and a rear section aft of the middle structure, said rear section housing a thrust reverser system, the middle structure comprising a casing surrounding the fan and an outer structure, wherein the air intake structure comprises at least one inner panel attached to the middle structure by means of the casing and forming with the casing a fixed structure of the nacelle, and, at least one outer longitudinal panel attached in a removable manner to the fixed structure and incorporating an air intake lip, said at least one outer longitudinal panel being movable between an operating position in which the outer panel provides the aerodynamic continuity with the outer structure of the middle structure and the air intake lip provides the aerodynamic continuity with the inner panel of the air intake structure, and a maintenance position in which the outer panel is separated from the outer structure of the middle structure and the air intake lip is separated from the inner panel of the air intake structure, and wherein the middle structure comprises at least one laterally movable fan cover allowing external access to the nacelle.