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 -
Feb 1, 2018
app pub date -
Sep 22, 2017
filing date -
Aug 23, 2007
priority date (Note) -
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Abstract
A turbofan engine includes fan section including a plurality of fan blades, a gear train, a low spool including a low pressure turbine and a low pressure compressor, the low pressure turbine driving the plurality of fan blades through the gear train, and a high spool including a high pressure turbine driving a high pressure compressor. A fan nacelle at least partially surrounds a core nacelle to define a fan bypass flow path. A fan variable area nozzle is in communication with the fan bypass flow path and defines a fan nozzle exit area between the fan nacelle and the core nacelle. The fan variable area nozzle varies the fan nozzle exit area.
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