Patent ID: 9726110
Date: 2017-08-08
CPC Classifications: F02K,F05D

Claim:
1. An aircraft propulsion system comprising: a generally annular fan case, axially defined with respect to a longitudinal axis of the generally annular fan case 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 generally annular fan case, the generally annular fan case comprising a generally annular cascade array; wherein the thrust reversing assembly is located axially between the fan and the stator blade array; a blocker door configured to pivot radially inward to expose the generally annular cascade array; a sleeve situated at least partially about the generally annular cascade array, the sleeve configured to deploy to expose the cascade array; and a substantially annular outer barrel, the substantially annular outer barrel comprising a fan cowl situated concentrically about the generally annular fan case, the sleeve comprising a portion of the fan cowl, wherein the sleeve is translatable along the axial direction with respect to the longitudinal axis of the fan case, and the blacker door is configured to cover an inner surface of the generally annular cascade array such that bypass air flows through a bypass air duct defined between the blacker door and an inner fixed structure disposed radially inward of the blacker door, wherein translation of the sleeve along the cascade array to produce reverse thrust, and wherein the blacker door pivots via a hinge located axially forward of the stator blade array corresponding to an axial location of the cascade array with respect to the longitudinal axis of the generally annular fan case.