Fuel-cooled bladed rotor of a gas turbine engine
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United States of America Patent
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Oct 11, 2016
Grant Date -
Jul 10, 2014
app pub date -
Mar 14, 2014
filing date -
Apr 9, 2008
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Abstract
Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.
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