Patent ID: 8109466
Filing Date: 2012-02-07
Classification: F02K,Y02T

Abstract:
1. An aircraft engine thrust reverser cascade assembly comprising: (a) a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end spaced from the aft-most vane so as to define an air flow path between the aft-most vane and aft end through which air passing through the cascade segment flows; and (b) an aft cascade ring removably attached to the aft ends of the cascade segments, the aft cascade ring including a body portion oriented in a plane substantially transverse to a longitudinal axis of the cascade assembly, and a deflector portion that at least partially extends forward of the body portion, extending at least partially across the air flow path; (c) wherein the deflector portion is configured to at least partially redirect at least a portion of air passing along the air flow.