Patent ID: 8333344
Filing Date: 2012-12-18
Classification: B64D,F02C,F05D

Abstract:
1. A nacelle for a turbojet engine comprising: an air intake structure able to channel a flow of air toward a fan of the turbojet engine, and comprising at least one longitudinal outer panel incorporating an air intake lip, a central structure intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, at least one inner panel comprising an acoustic shell ring, said acoustic shell ring having a downstream end attached to an upstream end of the central structure and therewith forming a fixed structure of the nacelle, and guide means for guiding the outer panel or panels and able to allow substantially rectilinear movement of the outer panel toward the upstream end of the nacelle so that the air intake structure can be opened, wherein the guide means are entirely attached to the central structure.