Patent ID: 9068532
Filing Date: 2015-06-30
Classification: F02K

Abstract:
1. A thrust reverser for a turbine engine with a bypass duct, the thrust reverser comprising: a translating sleeve slidable between a forward stowed position and an aft deployed position; and a cascade assembly comprising a number of apertures through which bypass air is directed from the bypass duct in a reverse thrust direction, the cascade assembly being positioned in a stowed position when the translating sleeve is in the forward stowed position and where airflow through the apertures is blocked by the translating sleeve, and the cascade assembly being positioned in a deployed position when the translating sleeve is in the aft deployed position and where bypass air is directed through the apertures; wherein the cascade assembly is at least partially radially displaced inward towards an engine centerline in the deployed position as compared to the stowed position, and wherein a forward end of the cascade assembly is displaced inward towards the engine centerline relative to an aft end of the cascade assembly in the deployed position.