Gas turbine engine with intercooling turbine section
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United States of America Patent
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Jun 16, 2015
Grant Date -
May 2, 2013
app pub date -
Nov 1, 2011
filing date -
Nov 1, 2011
priority date (Note) -
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Abstract
A gas turbine engine includes a combustor section, a fan section forward of the combustor section, a low pressure turbine section along the combustor section, and an intercooling turbine section aft of the fan section and forward of the combustor section. The intercooling turbine section includes upstream and downstream intercooling turbine variable vanes. The intercooling turbine section is situated in an intermediate flow path that is inboard of an outer bypass flow path. The intermediate flow path splits downstream from the intercooling turbine section to a second stream bypass flow path and a core flow path. The second stream bypass flow path is inboard of the outer bypass flow path and extends to an exhaust nozzle. The exhaust nozzle is located aft of the low pressure turbine section and inboard of the outer bypass flow path.
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