Patent ID: 7637095

Claim:
A fan nacelle which defines a fan bypass flow for a gas turbine engine comprising: a static ring defined about an axis; a first flap assembly segment pivotally mounted to said static ring; a second flap assembly segment pivotally mounted to said static ring; a first synchronizing ring segment rotatable about said axis relative said static ring; a second synchronizing ring segment rotatable about said axis relative said static ring; a first linkage mounted to said first synchronizing ring and said first flap assembly segment such that a first semi-annular fan exit throat area segment defined by said first flap assembly segment is adjustable in response to rotation of said first synchronizing ring; a second linkage mounted to said second synchronizing ring and said second flap assembly segment such that a second semi-annular fan exit throat area segment defined by said second flap assembly segment is adjustable independently of said first semi-annular fan exit throat area segment in response to rotation of said second synchronizing ring to selectively generate a thrust vector off said axis.