Patent ID: 8127529
Filing Date: 2012-03-06
Classification: F02K,F05D

Abstract:
1. A gas turbine engine system comprising: a fan; a nacelle arranged about the fan; a gas turbine engine core having a compressor and a turbine at least partially within the nacelle; a fan bypass passage downstream of the fan for conveying a bypass airflow, between the nacelle and the gas turbine engine core; a nozzle door associated with the fan bypass passage that moves between a stowed position, an intermediate position, and a thrust reverse position to influence the bypass airflow, the nozzle door having a first end, a second end opposed from the first end, and a first pivot between the first end and the second end; a linkage connected with the nozzle door; 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 the bypass airflow through the fan bypass passage; a controller that selectively commands the actuator to move the nozzle door; and a frame member supporting the nozzle door, wherein the frame is pivotally secured to an aftmost end of the nacelle relative to the bypass airflow.