Patent ID: 8869505
Filing Date: 2014-10-28
Classification: F02K,F05D

Abstract:
1. A nozzle for use in a gas turbine engine, comprising: 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 end and the second end; a linkage connected with the nozzle door; and an actuator coupled with the linkage, wherein 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 to influence a bypass airflow through a fan bypass passage having a radially outward side defined by a nacelle in at least one position, wherein at least a portion of the nozzle door is radially outward of the nacelle, wherein the nozzle door includes a lip that extends from the nozzle door at a location between the first pivot and one of the first end and the second end, wherein the actuator is configured to retract an actuator rod to move the nozzle door towards a thrust reverse position.