Patent ID: 9341083
Filing Date: 2016-05-17
CPC Classification: B64D,F01D,F02K,F05D

Claim Text:
1. A turbojet engine nacelle having a middle section comprising a fan case of a turbojet engine, and a downstream section comprising at least one front frame, wherein the downstream section is rigidly fixed to the middle section by the fan case and flexibly connected to a fastening pylon of said turbo jet engine by at least one swiveled connecting rod, said downstream section being equipped with at least one rail or slide extending in a substantially longitudinal direction of the nacelle and configured to cooperate with at least one corresponding slide or rail of a fastening pylon of the turbojet engine, wherein the at least one rail or slide of the downstream section is connected to the at least one swiveled connecting rod, and a flange of said at least one swiveled connecting rod being directly attached on a periphery of the front frame.