Patent ID: 8490382

Claim:
A gas turbine engine system comprising: an annular fan bypass passage extending between an inner flow surface and an outer flow surface relative to an engine centerline axis; a cooling passage having an inlet for receiving a bleed flow from the annular fan bypass passage and an outlet at the inner flow surface for discharging the bleed flow into the annular fan bypass passage; and a nozzle, disposed at an aft end of the annular fan bypass passage, having a variable cross-sectional area for controlling an airflow within the annular fan bypass passage, the nozzle including at least one flap located at the outer flow surface that pivots about a hinge that is selectively moveable to change the variable cross-sectional area thereby controlling an amount of the bleed flow through the cooling passage, wherein the outlet of the cooling passage is axially aligned with the hinge relative to the engine centerline axis.