Gas turbine engine with axial movable fan variable area nozzle
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United States of America Patent
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Jan 8, 2019
Grant Date -
Jan 11, 2018
app pub date -
Sep 22, 2017
filing date -
Aug 23, 2007
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Abstract
A method of designing a turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, providing a fan section including a plurality of fan blades, providing a low pressure turbine driving the plurality of fan blades through a gear train, providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle, providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and providing a fan variable area nozzle in communication with the fan bypass flow path and defining a fan nozzle exit area between the fan nacelle and the core nacelle.
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