초록 ▼

The invention relates to a thrust reverser (1) comprising an opening with fixed grids (4) that is closed by a sliding lid (2) in case of direct thrust, and opened by the downstream longitudinal translation displacement of the lid (2) in case of thrust reversal. A flap (20) is pivotally mounted at on

The invention relates to a thrust reverser (1) comprising an opening with fixed grids (4) that is closed by a sliding lid (2) in case of direct thrust, and opened by the downstream longitudinal translation displacement of the lid (2) in case of thrust reversal. A flap (20) is pivotally mounted at one upstream end on the lid (2) and can move between a retracted position and an expanded position in which, in case of thrust reversal, it blocks an annular channel (10) in order to redirect a gas flow towards the grid opening (4). A slider (24) for driving the flap (20) is mounted so as to be capable of displacement in at least one translation guiding rail (33) provided in the structure of the lid (2), and is connected to a downstream end of the flap (20) through a driving connecting rod (30) so that a translation movement of the slider (24) in the guiding rail (33) results in a pivoting of the connecting rod (30) and of the flap (20). Actuation means (22) are provided for driving the slider (24) in a translation movement in the guiding rail (33) when the lid (2) is in a downstream translation phase.

대표청구항 ▼

1. A thrust reverser for a turbofan nacelle comprising: means for deflecting at least a fraction of an airflow of the turbofan toward an opening formed in an outer panel of the nacelle and at least one movable cowl which can move translationally in a substantially parallel direction to a longitudina

1. A thrust reverser for a turbofan nacelle comprising: means for deflecting at least a fraction of an airflow of the turbofan toward an opening formed in an outer panel of the nacelle and at least one movable cowl which can move translationally in a substantially parallel direction to a longitudinal axis of the nacelle and which has at least one flap pivotably movable relative to a pivoting axis located on an upstream end of the flap, said movable cowl being able to switch alternately from a closed position in which the movable cowl covers the deflection means, to an open position in which the movable cowl opens a passage into the outer panel of the nacelle and uncovers the deflection means,wherein the movable cowl in the closed position provides aerodynamic continuity together with the flap being in a retracted position, the flap able to block off part of an annular duct of the nacelle in a pivoted position,wherein a slider for driving the flap is movably mounted in at least one translation-guiding track formed in a structure of the movable cowl, the slider connected to the flap via a driving link such that a translational movement of the slider in the translation-guiding track is accompanied by a pivoting of the link, and therefore of the flap, and actuating means are provided for translationally driving the slider in the translation-guiding track when the movable cowl is in a translation phase in a downstream direction. 2. The thrust reverser as claimed in claim 1, wherein the actuating means are provided for translationally driving the slider in the translation-guiding track when the movable cowl is in a terminal phase of its translational travel in the downstream direction. 3. The thrust reverser as claimed in claim 1, wherein the slider forms an intermediate movable portion of an actuating cylinder arranged along a longitudinal axis of the thrust reverser, said actuating cylinder comprising a tubular base connected to the external nacelle upstream of the reverser, the tubular base housing the slider and a terminal rod, wherein the slider and the terminal rod are mounted, independently one from the other, in an axially sliding manner in the base of the cylinder, a downstream end of the terminal rod being connected to the movable cowl. 4. The thrust reverser as claimed in claim 3, wherein the downstream end of the terminal rod of the actuating cylinder is connected to the movable cowl via a transverse driving pin housed in a cavity of oblong shape perpendicularly to a direction of travel of the cowl, said cavity being formed in a structure of the movable cowl. 5. The thrust reverser as claimed in claim 3, wherein there are two translation-guiding tracks for translationally guiding the slider, said translation-guiding tracks being arranged on each side of the slider, each of said translation-guiding tracks receiving one end of a transverse hinge pin for hinging a driving link on the slider. 6. The thrust reverser as claimed in claim 1, wherein the translation-guiding track for translationally guiding the slider extends lengthwise in a transverse plane of the movable cowl and forms a circular arc substantially concentric with a circumference of the movable cowl, and wherein said driving link is hinged on the flap and on the slider about pins which are substantially parallel to a longitudinal axis of the thrust reverser. 7. The thrust reverser as claimed in claim 6, wherein the slider is connected to a plurality of flaps distributed over the circumference of the movable cowl. 8. The thrust reverser as claimed in claim 6, wherein the slider has a length portion provided with a set of teeth intended to engage with a pinion driven to rotate, in a transverse plane of the movable cowl, by an actuator. 9. The thrust reverser as claimed in claim 8, wherein the actuator is electric and energized when the movable cowl reaches a terminal phase of its translational travel in the downstream direction. 10. The thrust reverser as claimed in claim 6, wherein the actuating cylinder for the slider, arranged parallel to the translation-guiding track for the slider, is hinged by a first end on a structure of the movable cowl and by a second end on the slider. 11. The thrust reverser as claimed in claim 1, wherein the movable cowl comprises a plurality of flaps distributed over its circumference and each flap comprising driving links of different lengths. 12. A turbofan nacelle, wherein the turbofan nacelle comprises at least one thrust reverser as claimed in claim 1.