Turbofan engine nozzle assembly and method of operating same

Details Turbofan engine nozzle assembly and method of operating same Turbofan engine nozzle assembly and method of operating same

2006-11-14

2010-06-01

Rodríguez, William H (Department: 3741)

Power plants

Reaction motor

Interrelated reaction motors

C060S226100

Reexamination Certificate

active

07726116

ABSTRACT:
A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other defining an annular fan bypass duct. A first member couples the nacelle to the core cowl and includes a first flap hingedly coupled to each sidewall of the first member. An opposing second member couples the nacelle to the core cowl and includes a second flap hingedly coupled to each sidewall of the second member. The first flaps and the second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct. A turbofan engine assembly and a method for operating the same are also provided.

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