Patent ID: 9115668
Filing Date: 2015-08-25
Classification: F02K

Abstract:
1. A thrust reverser device for a turbojet engine nacelle comprising: means for deflecting at least part of a flow of air from the turbojet engine, and at least one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle and having at least one flap pivotably mounted by one end on said at least one cowl, said at least one cowl configured to translate from a closing position in which said at least one cowl ensures an aerodynamic continuity of the nacelle with said at least one flap being in a retracted position and covers the deflecting means, to an opening position in which said at least one cowl opens a passage in the nacelle and exposes the deflecting means, said at least one flap being in a pivoted position in which the flap is capable of covering part of an annular channel of the nacelle, wherein said at least one cowl is equipped with at least one driving lead screw comprising over at least part of a length thereof a backlash portion and a helical groove portion, each portion engaging with a stationary guide means of the nacelle during translational movement of said at least one cowl, whereby said helical groove portion rotates said at least one driving lead screw and said backlash portion does not rotate said at least one driving lead screw so as to delay said opening of said at least one flap, and wherein said at least one driving lead screw is associated with at least one means for transmitting rotational movement thereof towards at least one drive system of said at least one flap.