Patent ID: 9127623
Filing Date: 2015-09-08
Classification: F02K,F05D,Y02T

Abstract:
1. A thrust reverser device for a turbojet engine nacelle comprising at least one cowl mounted so as to move in a translational manner in a direction substantially parallel to a longitudinal axis of the nacelle between a closing position in which the cowl provides an aerodynamic continuity of the nacelle and covers deflecting means for deflecting at least one portion of an air flow of the turbojet engine, and an opening position in which the cowl opens a passage in the nacelle and uncovers said deflecting means, the cowl being associated with at least one blocking flap pivotally mounted at one end on the cowl between a retracted position corresponding to the closing position of said movable cowl and a pivoted blocking position corresponding to the opening position in which the blocking flap closes at least partially an air flow path of the nacelle, the blocking flap being equipped with at least one driving mechanism comprising at least one assembly forming a lever pivotally mounted on the cowl and articulated at each of ends thereof, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device, wherein the assembly and the driving links are articulated in an articulation plane substantially perpendicular to the blocking flap and substantially radial to the thrust reverser device.