Gas turbine engine airfoil

摘要

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 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 crosses an initial axial stacking offset that corresponds to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is between 1.5 and 2.0 or less than 1.4.

主权项

1. An airfoil for a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a 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 aftward and the negative slope leans forward relative to an engine axis, wherein the positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position, a first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve, a second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve, a ratio of the second to first axial stacking offset X2/X1 is between 1.5 and 2.0 or less than 1.4.