Thrust reverser comprising at least one deployable deflecting membrane

Thrust reverser for an aircraft propulsion unit, the reverser comprising a fixed structure equipped with a wall for the radially internal delimitation of a secondary flow duct of the propulsion unit intended to have a secondary flow pass through it, the reverser also comprising a movable structure comprising at least one movable reverser cowl equipped with a radially internal reverser cowl wall delimiting the secondary flow duct radially outwards, the movable structure being movable in translation with respect to the fixed structure on a longitudinal central axis of the reverser, between an advanced direct-thrust position and a retracted thrust-reversal position in which the movable structure and the fixed structure define axially between them, on the secondary flow duct, an opening for radial extraction of at least part of the secondary flow,

• wherein the thrust reverser also comprises at least one deployable deflecting membrane designed to deflect at least part of the secondary flow escaping from the radial extraction opening, when this deflecting membrane is in a deployed configuration adopted when the movable structure is in the retracted thrust-reversal position, and in that, in this deployed configuration said at least one deflecting membrane extends radially outwards beyond the movable reverser cowl in the retracted thrust-reversal position.