BLADE LEADING EDGE TIP RIB
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United States of America Patent
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Issued Date -
Aug 28, 2014
app pub date -
Feb 25, 2013
filing date -
Feb 25, 2013
priority date (Note) -
Abandoned
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Abstract
A rotor blade for a gas turbine engine includes a leading edge tip rib projecting outwardly from an airfoil of the blade at a tip region thereof. The tip rib continuously surrounds a leading edge of the airfoil and extends rearwardly from the leading edge along respective pressure and suction side surfaces to thereby alter the blade tip leakage vortex structure and strength, resulting in a stage efficiency benefit.
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