Patent ID: 8650854

Claim:
A turbofan engine comprising: a core nacelle housing a spool supporting a turbine; a fan nacelle and the core nacelle providing a nozzle which includes a nozzle exit area, the nozzle fully within an annulus arranged radially between the core and fan nacelles and that provides a bypass flow path; a turbofan surrounded by the fan nacelle and coupled to the spool and arranged upstream from the core nacelle, the turbofan adapted to produce a bypass flow through the bypass flow path that is exhausted through the nozzle; a passage selectively in fluid communication with the bypass flow path for exhausting a portion of the bypass flow through the passage instead of the nozzle to a vent that is located in the pylon and outside the annulus to change an effective nozzle exit area; and a bifurcation arranged in the bypass flow path and supporting the core nacelle relative to the fan nacelle, the bifurcation including an inlet for selectively providing the portion of bypass flow to the passage.