Tri-body variable area fan nozzle and thrust reverser

The gas turbine engine system as recited in claim 6, wherein the first telescoping section is concentric with the second telescoping section.

A method of controlling a gas turbine engine system including a nozzle having a first nozzle section that is moveable to control a bypass airflow within a bypass passage and a second nozzle section having a stowed position and a thrust reverse position for slowing a vehicle and, the method comprising:

• (a) selectively independently moving the first nozzle section in an axial direction between an open position and a closed position using a first telescoping section of an actuator to vary an effective cross-sectional area of the nozzle to control the bypass airflow;
• and
• (b) selectively independently moving the second nozzle section in the axial direction between the stowed position and the thrust reverse position using a second telescoping section of the actuator to reverse a direction of the bypass flow and produce a thrust reversal force.

The method as recited in claim 12, further including selectively moving the first nozzle section independently of the second nozzle section, and moving the second nozzle section independently of the first nozzle section.

The method as recited in claim 16, including moving a first telescoping section of the telescoping member relative to a second telescoping section of the telescoping member that is concentric with the first telescoping section to move the first nozzle section.

The method as recited in claim 18, wherein said step (a) includes increasing the effective cross-sectional area in response to an aircraft take-off condition.