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US 2011/0030338 A1Published application
Bypass turbojet engine nacelle
AssigneeAircelle
InventorGuy Bernard Vauchel
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AssigneeAircelle
InventorGuy Bernard Vauchel
Estimating the term…
The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl (6) mounted such that it can move in translation in a direction substantially parallel to a longitudinal axis of the nacelle and able to move alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle and covers deflection means (70) and an open position in which it opens a passage in the nacelle and uncovers the deflection means, the said moving cowl also being extended by at least one nozzle section (7) mounted at a downstream end of the said moving cowl, characterized in that the nozzle section comprises at least one panel (10) mounted such that it can rotate about at least one pivot about an axis substantially perpendicular to a longitudinal axis of the nacelle, the said panel further being connected to a fixed fairing structure (2) of the turbojet engine by at least one link rod (11) mounted such that it can rotate about anchor points on the panel of the nozzle section and on the fixed structure, respectively.
A bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl mounted such that the cowl can move in translation in a direction substantially parallel to a longitudinal axis of the nacelle and able to move alternately from a closed position in which the cowl ensures the aerodynamic continuity of the nacelle and covers deflection means and an open position in which the cowl opens a passage in the nacelle and uncovers the deflection means, said moving cowl also being extended by at least one nozzle section mounted at a downstream end of said moving cowl, wherein the nozzle section comprises at least one panel mounted such that the panel can rotate about at least one pivot about an axis substantially perpendicular to a longitudinal axis of the nacelle, said panel further being connected to a fixed fairing structure of the turbojet engine by at least one link rod mounted such that it can rotate about anchor points on the panel of the nozzle section and on the fixed structure, respectively.
Dependencies are inferred from the claim text.