An aircraft propulsion system may include a generally annular fan case defined by a fan configured to be disposed at a forward end thereof and a stator blade array configured to be disposed at an aft end thereof, a thrust reversing assembly comprising at least a portion of the fan case, the fan case comprising a generally annular cascade array, and/or a sleeve situated at least partially about the cascade array, the sleeve configured to deploy to expose the cascade array. The aircraft propulsion system may further comprise a blocker door coupled to at least one of the cascade array and an inner surface of the fan case, the blocker door configured to deploy to redirect airflow through the cascade array.