Gas turbine engine airfoil
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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. X LE corresponds to an axial distance from a leading edge to the reference point at a given span position. X TE corresponds to a axial distance from a trailing edge to the reference point at a given span position. X d corresponds to an axial stacking offset at a given span position. (X LE −X d )/(X d −X TE ) at 100% span position is about 1 and (X LE −X d )/(X d −X TE ) at 90% span position is about 1.
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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve, wherein the airfoil extends from a root, and a zero axial reference point corresponds to axial center of the root, X LE corresponds to a axial distance from a leading edge to the reference point at a given span position, X TE corresponds to a axial distance from a trailing edge to the reference point at a given span position, X d corresponds to an axial stacking offset at a given span position, wherein (X LE −X d )/(X d −X TE ) at 100% span position is 1+/−0.10 and (X LE −X d )/(X d −X TE ) at 90% span position is 1+/−0.10.
2. The airfoil according to claim 1 , wherein (X LE −X d )/(X d −X TE ) at 60% span position is 1.2+/−0.10 and (X LE −X d )/(X d −X TE ) at 50% span position is 0.92+/−0.10.
3. The airfoil according to claim 1 , wherein (X LE −X d )/(X d −X TE ) at 40% span position is 0.92+/−0.10 and (X LE −X d )/(X d −X TE ) at 20% span position is 0.92+/−0.10.
4. The airfoil according to claim 1 , wherein (X LE −X d )/(X d −X TE ) at 60% span position is 0.92+/−0.10 and (X LE −X d )/(X d −X TE ) at 50% span position is 0.92+/−0.10.
5. The airfoil according to claim 1 , wherein (X LE −X d )/(X d −X TE ) at 60% span position is 0.89+/−0.10 and (X LE −X d )/(X d −X TE ) at 50% span position is 1+/−0.10.
6. The airfoil according to claim 1 , wherein (X LE −X d )/(X d −X TE ) at 40% span position is 1+/−0.10 and (X LE −X d )/(X d −X TE ) at 20% span position is 1+/−0.10.
7. The airfoil according to claim 1 , wherein the airfoil is a fan blade for a gas turbine engine.
8. The airfoil according to claim 1 , wherein (X LE −X d )/(X d −X TE ) has a tolerance of +/−0.05.
9. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a low fan pressure ratio of less than 1.55;
a geared architecture coupling the fan section to the turbine section or the compressor section; and
wherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends 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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve, wherein the airfoil extends from a root, and a zero axial reference point corresponds to axial center of the root, X LE corresponds to an axial distance from a leading edge to the reference point at a given span position, X TE corresponds to an axial distance from a trailing edge to the reference point at a given span position, X d corresponds to an axial stacking offset at a given span position, wherein (X LE −X d )/(X d −X TE ) at 100% span position is 1+/−0.10 and (X LE X d )/(X d −X TE ) at 90% span position is 1+/−0.10.
10. The gas turbine engine according to claim 9 , wherein (X LE −X d )/(X d −X TE ) has a tolerance of +/−0.05.