Gas turbine engine airfoil
AssigneeUnited Technologies Corporation
InventorsEdward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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AssigneeUnited Technologies Corporation
InventorsEdward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
Estimating the term…
An airfoil for 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 total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). The curve is at least a third order polynomial and has an initial positive slope.
An airfoil for a turbine engine comprising:
A gas turbine engine comprising:
A gas turbine engine comprising:
Dependencies are inferred from the claim text.