Patent ID: 8733107

Claim:
A convergent-divergent nozzle of a gas turbine engine comprising: an annular ring configured to be connected to an aft portion of the gas turbine engine; a plurality of mechanisms circumferentially connected to the annular ring about a main axis of the gas turbine engine; wherein the plurality of mechanisms each comprise: a convergent flap configured to be kinematically connected to the aft portion of the gas turbine engine; a divergent flap pivotally and directly connected to the convergent flap at a hinged connection; at least one actuator connected to the annular ring and configured to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions; and at least one biasing apparatus configured to position the divergent flap independent of the one or more positions of the actuator by substantially balancing a force on the divergent flap produced by a gas pressure on the nozzle, the at least one biasing apparatus comprising: a biasing linkage directly connected to the divergent flap through a pivotal and sliding connection, the biasing linkage configured to kinematically connect the divergent flap to the aft portion of the gas turbine engine; and a spring connected to the biasing linkage and the annular ring.