Patent ID: 8739552

Claim:
A nacelle for a turbofan comprising a front air intake section, a mid-section designed to surround a fan of a turbojet and a rear section, said rear section having an internal structure designed to serve as a casing to rear portion of the turbojet and an external structure, wherein the internal structure has coupling means suitable for allowing an attachment of the nacelle to a pylon designed to be connected to a fixed structure of an aircraft on at least one portion of said internal structure, wherein the internal structure comprises at least one external wall forming an aerodynamic surface adjacent a cold flow stream that flows between the internal structure and the external structure, the external wall mounted over a framework made from plurality of radial frames distributed over the length of the internal structure and each radial frame comprising a circumferential ring, wherein each adjacent circumferential ring is connected together by at least one reinforcement between them.