US 12,270,356 B2
Thrust reverser cascade with one or more flow disrupters
Julian Winkler, Glastonbury, CT (US); Wentaur E. Chien, San Diego, CA (US); and Xiaolan Hu, San Diego, 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. 17/878,531.
Prior Publication US 2024/0035429 A1, Feb. 1, 2024
Int. Cl. F02K 1/72 (2006.01); F02K 1/50 (2006.01); F02K 1/54 (2006.01); F02K 1/56 (2006.01); F02K 1/60 (2006.01); F02K 1/62 (2006.01); F02K 1/64 (2006.01); F02K 1/68 (2006.01); F02K 1/70 (2006.01)
CPC F02K 1/72 (2013.01) [F02K 1/50 (2013.01); F02K 1/54 (2013.01); F02K 1/56 (2013.01); F02K 1/60 (2013.01); F02K 1/62 (2013.01); F02K 1/64 (2013.01); F02K 1/68 (2013.01); F02K 1/70 (2013.01); F05D 2220/323 (2013.01); F05D 2240/129 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An apparatus for an aircraft propulsion system, comprising:
a propulsion system structure including a flowpath and a pivoting door thrust reverser system;
the flowpath extending within the propulsion system structure to an exhaust nozzle;
the pivoting door thrust reverser system including a cascade structure and a thrust reverser door;
the cascade structure including a thrust reverser cascade and a flow disruptor;
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, the thrust reverser cascade extending radially between an inner face and an outer face, and the thrust reverser cascade comprising a plurality of vanes arranged in a longitudinally extending array along the inner face;
the flow disruptor arranged at an inner aerodynamic flow surface of the inner face and forward of a bullnose for the plurality of vanes, the inner aerodynamic flow surface extending axially toward the cascade forward end, and the flow disruptor configured to disrupt boundary layer air flowing towards the plurality of vanes; and
the thrust reverser door configured to pivot outward into an environment external to the aircraft propulsion system and open an opening through the pivoting door thrust reverser system, and the thrust reverser door further configured to pivot inward into the flowpath to block the exhaust nozzle.