Thrust reverser cascade with one or more flow disrupters

An apparatus for an aircraft propulsion system, comprising:

• a propulsion system structure including a flowpath and a thrust reverser system;
• the flowpath extending within the propulsion system structure to an exhaust nozzle;
• the thrust reverser system comprising a cascade structure and a thrust reverser door;
• the cascade structure including a thrust reverser cascade and a groove;
• 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, the thrust reverser cascade comprising a plurality of vanes distributed along the inner face, and the plurality of vanes exposed to the flowpath when the thrust reverser door is in a stowed position;
• the groove disposed forward of a ramp for the plurality of vanes, the groove extending radially into the cascade structure from the inner face, and the groove disposed at an axially extending portion of the cascade forward end;
• and
• the thrust reverser door configured to pivot between the 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.

An apparatus for an aircraft propulsion system, comprising:

• a propulsion system structure including a flowpath and a thrust reverser system;
• the flowpath extending within the propulsion system structure to an exhaust nozzle;
• the thrust reverser system comprising a cascade structure and a thrust reverser door;
• the cascade structure including a thrust reverser cascade and a fence;
• 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, the thrust reverser cascade comprising a plurality of vanes distributed along the inner face, and the plurality of vanes exposed to the flowpath when the thrust reverser door is in a stowed position;
• the fence disposed at an axially extending portion of the cascade forward end, the fence disposed forward of a bullnose for the plurality of vanes, the fence extending radially out from the inner face to a distal end, and the fence extending laterally along the thrust reverser cascade;
• and
• the thrust reverser door configured to pivot between the 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.