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An aircraft engine thrust reverser cascade assembly includes 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. The cascade assembly also includes an aft cascade ring removably attached to t

An aircraft engine thrust reverser cascade assembly includes 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. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments.

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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 betwee

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. 2. An aircraft engine thrust reverser cascade assembly according to claim 1 wherein the deflector portion has a substantially frusto-conical shape. 3. An aircraft engine thrust reverser cascade assembly according to claim 1 wherein the deflector portion has a substantially arcuate cross-sectional shape. 4. An aircraft engine thrust reverser cascade assembly according to claim 1 wherein the body portion of the aft cascade ring further includes an outer edge and an inner edge, and an inner portion connected to the inner edge, and wherein the deflector portion is connected to the outer edge. 5. An aircraft engine thrust reverser cascade assembly according to claim 1 wherein the deflector portion is non-orthogonal to the body portion. 6. An aircraft engine thrust reverser cascade assembly according to claim 1 wherein the aft cascade ring is removably attached to the aft ends of the cascade segments by a plurality of removable fasteners. 7. An aft cascade ring for an aircraft engine thrust reverser cascade assembly having a plurality of cascade segments, the aft cascade ring comprising: (a) a body portion having a major axis, an outer edge and an inner edge, the body portion lying in a plane substantially transverse to a longitudinal axis of the cascade assembly and configured for removable attachment to aft ends of the cascade segments for attaching the aft ends of cascade segments in series; and(b) a deflector portion connected to the outer edge of the body portion and extending forward of the body portion and the aft ends of the cascade segments, the deflector portion being configured to redirect at least some reverse thrust exhaust air passing between aft-most vanes and the aft ends of the cascade segments;(c) wherein the deflector portion is non-orthogonal with the major axis of the body portion. 8. An aft cascade ring according to claim 7 wherein the deflector portion has a substantially frusta-conical shape. 9. An aft cascade ring according to claim 7 wherein the deflector portion has a substantially arcuate cross-sectional shape. 10. An aft cascade ring according to claim 7 and further comprising at least one aft-extending portion. 11. An aft cascade ring according to claim 10 wherein the aft-extending portion is attached to the inner edge of the body portion. 12. An aft cascade ring according to claim 10 wherein the aftward extending portion has a substantially cylindrical shape. 13. An aircraft engine nacelle with a thrust reverser cascade assembly comprising: (a) a plurality of circumferentially spaced cascade segments, each cascade segment including an aft-most vane and an aft end; and(b) an aft cascade ring having a substantially flat body segment adjacent the aft-ends of the cascade segments in a plane substantially transverse to a longitudinal axis of the cascade assembly and adapted to be removably attached to the aft ends of the cascade segments further adapted for attaching the aft-ends of the cascade segments together to form the cascade assembly;(c) wherein the aft cascade ring includes a deflecting means extending across an air flow oath between the aft-most vanes and aft ends of the cascade segments for redirecting at least a portion of a volume of air passing through the air flow. 14. An aircraft engine nacelle according to claim 13 wherein the deflecting means comprises a deflector portion positioned aft of the aft-most vanes and forward of the aft ends of the cascade segments. 15. An aircraft engine nacelle according to claim 14 wherein the deflector portion of the aft cascade ring has a substantially frusto-conical shape. 16. An aircraft engine nacelle according to claim 14 wherein the deflector portion of the aft cascade ring has a substantially arcuate cross-sectional shape. 17. An aircraft engine nacelle according to claim 13 wherein the body segment of the aft cascade ring comprises an outer edge and an inner edge and an inner segment connected to the inner edge, wherein the deflecting means is a deflector portion connected to the outer edge of the body segment, and wherein the deflector portion extends outward and forward of the outer edge. 18. An aircraft engine nacelle according to claim 17 wherein the deflector portion of the aft cascade ring is non-orthogonal to the body segment. 19. An aircraft engine nacelle according to claim 13 wherein the aft cascade ring is removably attached to the aft ends of the cascade segments by a plurality of removable fasteners. 20. An aircraft engine nacelle according to claim 13 wherein the aft cascade ring comprises two or arcuate ring segments.