Thrust reverser for an aircraft turbojet engine nacelle

A thrust reverser for an aircraft turbojet engine nacelle comprising:

• a thrust reverser cowl movable in translation along a direction substantially parallel to a longitudinal axis (A) of the aircraft turbojet engine nacelle, between a direct jet position and a reverse jet position;
• an outlet nozzle with a variable section which is arranged in the downstream extension of said cowl and which is movable between at least one reduced ejection section position, one increased ejection section position and one intermediate neutral position;
• at least one actuator which comprises a body mounted on a fixed structure of the thrust reverser and an actuating rod, said rod being adapted to drive in displacement the variable nozzle and the movable cowl;
• and
• a passive coupler comprising:
• a hollow housing secured to the thrust reverser cowl, and which delimits internally a cavity extending axially generally along an axis (B) of the actuating rod and which is delimited radially by a radial upstream wall and by a radial downstream wall;
• a piston fastened on the actuating rod of the actuator and which is slidably mounted in the housing of the passive coupler by hermetically dividing said cavity into two compartments comprising an upstream compartment located between the upstream wall and the piston and a downstream compartment located between the downstream wall and the piston, each compartment being filled with a fluid;
• and
• a unidirectional flow limiter providing the fluid connection between the two compartments of the housing, said flow limiter limiting the fluid circulation rate in the direction of a fluid flow from the downstream compartment to the upstream compartment, and enabling a free circulation of the fluid in the direction of fluid flow from the upstream compartment to the downstream compartment.