US 12,435,682 B2
Thrust reverser cascade with offset vane leading edges
Julian Winkler, Glastonbury, CT (US); Wentaur E. Chien, San Diego, CA (US); Xiaolan Hu, San Diego, CA (US); and Landy Dong, La Jolla, CA (US)
Assigned to ROHR, INC., Chula Vista, CA (US)
Filed by Rohr, Inc., Chula Vista, CA (US)
Filed on Aug. 1, 2022, as Appl. No. 17/878,468.
Prior Publication US 2024/0035427 A1, Feb. 1, 2024
Int. Cl. F02K 1/60 (2006.01); F02K 1/70 (2006.01)
CPC F02K 1/605 (2013.01) [F02K 1/70 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An apparatus for an aircraft propulsion system, comprising:
a propulsion system structure extending along an axial centerline including a nacelle having a fixed structure, a flowpath and a thrust reverser system, the flowpath extending within the propulsion system structure to an exhaust nozzle, and the thrust reverser system comprising a thrust reverser cascade and a thrust reverser door;
the thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end, the thrust reverser cascade extending laterally between a cascade first side and a cascade second side, and the thrust reverser cascade extending radially between a cascade inner face and a cascade outer face, the thrust reverser cascade is fixed to the fixed structure;
the thrust reverser cascade including a plurality of vanes and a plurality of rails;
the plurality of vanes arranged in a plurality of longitudinally extending arrays, the plurality of vanes comprising a first vane and a second vane, a leading edge of the first vane disposed on the cascade inner face, and a leading edge of the second vane recessed radially into the thrust reverser cascade from the cascade inner face;
the plurality of rails extending longitudinally along and connected to the plurality of vanes, the plurality of rails comprising a first rail with a first radial height, and the first radial height of the first rail decreasing as the first rail extends longitudinally from the cascade forward end to the cascade aft end, wherein each of the plurality of arrays is arranged between a respective laterally neighboring or adjacent pair of rails; and
the thrust reverser door configured to pivot between a stowed position and a deployed position, a first portion of the thrust reverser door radially outboard of and axially covering the thrust reverser cascade when the thrust reverser door is in the stowed position, and a second portion of the thrust reverser door forming a radial outer peripheral boundary of the flowpath between the thrust reverser cascade and the exhaust nozzle when the thrust reverser door is in the stowed position,
wherein:
a trailing edge of the first vane is disposed on the cascade outer face; and
a trailing edge of the second vane is spaced radially from the cascade outer face.