THRUST REVERSER CASCADE WITH ONE OR MORE FLOW STABILIZERS

An apparatus (20) is provided for an aircraft propulsion system (22). This apparatus (20) includes a thrust reverser cascade (64) extending longitudinally between a cascade forward end (68) and a cascade aft end (70). The thrust reverser cascade (64) extends laterally between a cascade first side (72) and a cascade second side (74). The thrust reverser cascade (64) extends radially between a cascade inner face (76) and a cascade outer face (78). The thrust reverser cascade (64) includes a plurality of vanes (86) and a wall (100). The vanes (86) are arranged in a longitudinally extending array along the cascade inner face (76). The vanes (86) include a first vane (86B) and a second vane (86C). The wall (100) is configured to block gas flow radially through the thrust reverser cascade (64) between the first vane (86B) and the second vane (86C).