Thrust reverser device
A thrust reverser device for a turbojet engine nacelle includes a cowl mounted translating between a closing position and an opening position in which the cowl opens a passage in the nacelle and uncovers deflecting cascades. The cowl is associated with a blocking flap pivotally mounted on the cowl between a retracted position and a pivoted blocking position in which the blocking flap closes partially an air flow path of the nacelle. The blocking flap is equipped with a driving mechanism including an assembly forming a lever pivotally mounted on the cowl and articulated at each of ends of the lever, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device. In particular, 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.
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.
2. The thrust reverser device according to claim 1 , wherein the assembly forming the lever comprises a first and a second lever arms, each respectively fixed, by means of the driving links, on a front frame and on the flap and pivotally mounted on the cowl.
3. The thrust reverser device according to claim 1 , wherein, when the thrust reverser device is in the opening position and the flap in the pivoted blocking position, the lever forms with the driving link, connected to the fixed structure of the thrust reverser device, an angle substantially equal to 160 degrees.
4. The thrust reverser device according to claim 3 , wherein the angle is obtained by providing for a lever length substantially equal to half a stroke of the cowl between the closing position and the opening position.
5. The thrust reverser device according to claim 4 , wherein the lever length ranges between 5 mm and 10 mm.
6. The thrust reverser device according to claim 1 , wherein at least one portion of the lever and the driving links of the driving mechanism are adapted to imbricate into each other when the flap is in the retracted position.
7. The thrust reverser device according to claim 1 , wherein the articulation plane of the driving mechanism comprises a center axis of the flap.
8. The thrust reverser device according to claim 7 , wherein when the flap is in the retracted position, the driving mechanism is folded and housed substantially in a plane of the flap at the center axis of said flap.
9. The thrust reverser device according to claim 1 , wherein the driving mechanism is substantially located between two flaps.
10. A nacelle of a turbofan engine comprising a thrust reverser device according to claim 1 .