Gas turbine engine bifurcation located fan variable area nozzle
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United States of America Patent
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Feb 6, 2018
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N/A
app pub date -
Jan 5, 2012
filing date -
Mar 17, 2009
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Abstract
A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, a fan, and a variable area flow system. The gear system defines a gear reduction ratio of greater than or equal to about 2.3. The fan is driven by the gear system about the axis to generate a bypass flow. The variable area flow system operates to effect the bypass flow.
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