Patent ID: 8578698

Claim:
A cascade type thrust reverser with cascade vanes for a jet engine, comprising a cowling in which there is formed an opening which, when gases are in a direct-thrust situation, is closed by a sliding cowl and which, in a thrust reversal situation, is uncovered by a downstream, with respect to a direction in which the gases flow through the engine, translational movement of the sliding cowl, a fan duct being defined between an inner skin and an outer skin into which an inner skin of the sliding cowl fits in the direct thrust situation, the inner skin of the sliding cowl comprising an annular part extending radially inward and able, in the thrust reversal situation, to come to face a larger diameter annular part of the inner skin of the fan duct, wherein said annular part of the inner skin of the sliding cowl comprises at least one flap mounted to pivot about a substantially central axis of rotation, between a position in which it is retracted into the inner skin of the sliding cowl and a deployed position in which a front part of the flap, upstream of its central axis of rotation, projects into the fan duct, and in that translational movement halting means are provided to, in the thrust reversal situation, act on a rear part of the flap, downstream of its central axis of rotation, so as to cause the flap to pivot into its deployed position to block off the fan duct.