Cascade type aircraft engine thrust reverser with hidden link actuator

In a thrust reverser system for a fan jet aircraft turbine engine having a nacelle including an engine body and a ring forming the aft portion of the nacelle, an engine core within said nacelle forming an air duct therebetween, means for translating said ring aft and uncovering an gap between said nacelle body and ring, a plurality of cascade sets in said gap and secured to said nacelle body, a plurality of islands separating said cascade sets and a blocker door associated with each cascade set;

• the improvement comprising:
• each blocker door forming the inner wall of said nacelle adjacent to each cascade set when said ring is in the forward position;
• each blocker door hingedly attached at the forward end to said ring;
• a single link connected between the aft end of each blocker door and the aft end of each cascade set;
• said translating means positioned within said islands and out of the path of air through said duct during normal engine flight operation and entirely out of the air flow deflected by said blocker doors through said cascade sets during reverse thrust operation;
• whereby as said ring is translated aft to uncover said cascade sets, said blocker doors are pivoted to positions substantially blocking air flow through said duct and directing that air flow through said cascade sets.