Cascade-type thrust reverser for jet engine

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) 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 articulation, 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 articulation, 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 articulation, so as to cause the flap to pivot into its deployed position to block off the fan duct.