Gas turbine engine with axial movable fan variable area nozzle
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United States of America Patent
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Oct 2, 2018
Grant Date -
Feb 15, 2018
app pub date -
Oct 11, 2017
filing date -
Aug 23, 2007
priority date (Note) -
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Abstract
A turbofan engine according to an example of the present disclosure includes, among other things, a fan section including a plurality of fan blades, the plurality of fan blades having a fixed stagger angle and a design angle of incidence, a low pressure turbine driving the plurality of fan blades through a gear train, a fan nacelle and a core nacelle extending along an engine axis of rotation, the fan nacelle at least partially surrounding the core nacelle and the plurality of fan blades, a fan bypass flow path defined between the core nacelle and the fan nacelle, the core nacelle contoured along the fan bypass flow path with respect to the engine axis of rotation, and a fan variable area nozzle in communication with a controller and 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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