| 主权项 |
1. A thrust reverser assembly for a gas turbine engine having a core engine, a nacelle surrounding the core engine, and a bypass duct defined by and between the nacelle and the core engine, the thrust reverser assembly comprising:
a translating cowl mounted to the nacelle and adapted to translate a distance in an aft direction of the gas turbine engine, the translating cowl having a radially inner wall that defines a radially outer flow surface of the bypass duct; a fixed structure within the nacelle that does not translate with the translating cowl, the fixed structure comprising at least one opening that is exposed to the bypass duct when the translating cowl is translated in the aft direction; and blocker doors mounted to the nacelle and having stowed positions and deployed positions, each of the blocker doors having an aftward trailing end pivotally and slidably coupled to the fixed structure, an oppositely-disposed leading second end, and a length therebetween pivotally and slidably coupled to the translating cowl so that translation of the translating cowl in the aft direction causes each of the blocker doors to move from the stowed position thereof to the deployed position thereof by initially translating in the aft direction with the translating cowl and relative to the fixed structure while the trailing end thereof slidably travels relative to the fixed structure and then by pivoting toward the aft direction relative to the fixed structure while pivoting at the trailing end thereof and the length thereof pivots and slidably travels relative to the translating cowl, wherein the inner wall of the translating cowl is between each of the blocker doors and the bypass duct when the blocker doors are in their stowed positions, and wherein the leading end of each of the blocker doors projects into the bypass duct and diverts bypass air within the bypass duct through the opening of the fixed structure when the blocker doors are in their deployed positions. |
