Gas turbine engine airfoil
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United States of America Patent
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Sep 26, 2023
Grant Date -
N/A
app pub date -
Dec 15, 2021
filing date -
Feb 19, 2014
priority date (Note) -
In Force
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Abstract
An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.
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