US Patent 8418436 Variable area fan nozzle and thrust reverser

A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a first pivot on the door between the first and second ends. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions, such as stowed, intermediate, and thrust reverse positions to influence bypass airflow through a fan bypass passage. The fan bypass passage has a radially outward side defined by a nacelle in at least one position. At least a portion of the nozzle door is radially outward of the nacelle and includes a lip extending from the nozzle door between the first pivot and one of the first end and second end.