Reverse core gear turbofan
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United States of America Patent
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Oct 23, 2018
Grant Date -
Dec 3, 2015
app pub date -
Aug 12, 2015
filing date -
Mar 27, 2012
priority date (Note) -
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Abstract
A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.
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