Thrust reverser with adjustable section nozzle for aircraft jet engine

摘要

The invention relates to a thrust reverser for a bypass jet engine that reverses the fan flow. The thrust reverser is installed in the fixed outer cowl and is comprised of pivoting doors that block the fan flow in order to create reverse thrust. A translating annular nozzle is located aft of the pivoting doors in the stowed position, preventing in flight inadvertent deployment. When the nozzle are translated aft, the doors are free to pivot and, at the same time, the section of the fan nozzle can be adjusted to produce more or less fan flow.