Gas turbine engine airfoil
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United States of America Patent
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Aug 6, 2019
Grant Date -
Feb 4, 2016
app pub date -
Aug 26, 2015
filing date -
Feb 19, 2014
priority date (Note) -
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Abstract
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.
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