Patent ID: 9169026
Filing Date: 2015-10-27
Classification: B64D,Y10T

Abstract:
1. A turbojet engine nacelle comprising: an air intake structure to channel a flow of air towards a fan of the turbojet engine, comprising an air intake lip upstream of the nacelle and attached at its ends to an outer panel and an inner panel; a central structure to surround said fan and to which the air intake structure is attached in such a way as to provide aerodynamic continuity, said central structure comprising a secondary, or bypass, flow path outer ring section surrounding the turbojet engine and a central outer cowl; and a downstream section to which the central structure is attached, wherein the outer panel comprises a moving part attached to the air intake lip and extending downstream, and guide means configured to guide the moving part and forming an outer contour of the outer panel, the guide means comprising at least one fixed part fixed to the central structure or to the downstream section, said at least one fixed part having a complementary shape to nest together with and to guide the moving part along longitudinal side edges of the at least one fixed part, wherein the at least one fixed part comprises a ramp mounted around an attachment pylon of the nacelle, and the ramp is connected to the moving part by sealing means, the sealing means being placed along the longitudinal side edges of the at least one fixed part where the moving part comes into contact with the at least one fixed part.