Thrust reverser for fan type turbojet engines using independently actuated pivoted thrust deflectors

A turbojet-engine thrust reverser, comprising:

• a fan bypass duct having an outlet and a primary engine cowling assembly having an outer wall, said primary engine cowling having a longitudinal axis and being located downstream of the outlet of the bypass duct;
• a plurality of movable thrust deflectors (3) circumferentially spaced about the primary cowling assembly periphery which in a forward thrust mode are retracted into the outer wall of the primary cowling (4), wherein said thrust deflectors (3) are each independently movable relative to the primary cowling assembly and not drivingly connected to another of said thrust deflectors, and each having a downstream portion and an upstream portion;
• each thrust deflector having at least one displaceable pivot (12) and at least one pivotable linkage element (9, 20) connecting each of said deflectors (3) to said primary cowling assembly (4) for rotation about its respective displaceable pivot (12);
• at least one linear actuator (6) and at least two guide elements (38, 42) connected to the primary cowling assembly (4), wherein each at least one linear actuator and at least two guide elements associated with a respective thrust deflector extend parallel with respect to one another, said at least one displaceable pivot (12) connected to at least one of said guide elements (38, 42) of said respective thrust deflector, said at least one linear actuator connected to and effecting movement of said respective thrust deflector to cause movement of said at least one pivot (12) along at least one of said guide elements (38, 42) when actuated;
• each said guide elements extending in a fore and aft direction;
• actuation of each linear actuator and displacement of each at least one displaceable pivot (12) along a respective guide element in a forward direction relative to engine bypass flow further effecting pivotal and translational motion of a respective thrust deflector (3) in cooperation with said at least one linkage element (9, 20) in a thrust reversed position aft of and adjacent the fan bypass duct to deflect bypass flow forwardly.