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1. A thrust reverser system for a gas turbine engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl, the thrust reverser system comprising:
a translating cowl mounted to the nacelle and adapted to translate in an aft direction of the gas turbine engine away from the fan cowl to define a circumferential opening therebetween; a fixed structure within the nacelle that does not translate when the translating cowl is translated in the aft direction; blocker doors mounted to the nacelle and having stowed positions and deployed positions, each of the blocker doors having a first end, an oppositely-disposed second end, an inner surface between the first and second ends, and at least one slot recessed into the inner surface; and linkage mechanisms connecting the blocker doors to the fixed structure, each of the linkage mechanisms comprising a first link pivotably coupled to the fixed structure and a second link pivotably coupled to one of the blocker doors, the first and second links being received in the slots recessed into the inner surfaces of the blocker doors when the blocker doors are in the stowed position, the linkage mechanisms being pivotably connected to the blocker doors so that translation of the translating cowl in the aft direction causes the first and second links to be displaced from the slots as each of the blocker doors moves to the deployed position thereof whereat each of the blocker doors extends across the bypass duct and diverts bypass air within the bypass duct through the circumferential opening. |
