| 摘要 |
<p>The present invention relates to a turbojet engine nacelle thrust reverser and to a nacelle equipped with at least one thrust reverser as aforementioned, said thrust reverser comprising: - at least one outer cowl (2), produced as two half-cowls (3) articulated on hinges (5), capable of translational movement from a position referred to as the closed position into at least one position referred to as open, - first actuating means (8) for actuating the translational movement of the downstream frame (18), - second actuating means (9) for actuating the rotation of each half-cowl (3), - locking/unlocking means (7) that lock/unlock the half-cowls (3) relative to one another, - thrust reversal means (13) comprising at least cascades of deflection veins (14) supported at their upstream end (15) by an upstream frame (16) and at their downstream end (17) by a downstream frame (18) and enclosed in a shroud (19) formed by a fan casing (20) and a fan cowl (11), means (21) of connection between the downstream frame (18) and the external cowl (2).</p> |
