Gas turbine engine airfoil
An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.
1. An airfoil, comprising:
pressure and suction sides extending between a leading edge and a trailing edge, the airfoil having a camber line along an airfoil section that is equidistant between an exterior surface of the pressure and suction sides, the camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge, wherein a ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5, and wherein the maximum thickness is located along the camber line between 13% and 38% camber position;
wherein the pressure and suction sides extend in a radial direction from a 0% span position to a 100% span position, and the airfoil section is between 5% and 95% span; and
wherein a thickness of the airfoil as a percentage of the maximum thickness is between 28% and 76% at a 5% camber position.
2. The airfoil according to claim 1 , wherein the thickness of the airfoil as the percentage of the maximum thickness is between 4% and 20% at a 95% camber position.
3. The airfoil according to claim 1 , wherein the thickness of the airfoil as the percentage of the maximum thickness over a camber position of the airfoil section is within a first and a second thickness trend line as shown in FIG. 5 .
4. The airfoil according to claim 3 , wherein the pressure side has a radius of curvature divided by the axial chord length over an axial chord position of the airfoil section within a first and a second curvature trend line as shown in FIG. 6 .
5. The airfoil according to claim 1 , wherein the pressure side has a radius of curvature divided by the axial chord length over an axial chord position of the airfoil section within a first and a second curvature trend line as shown in FIG. 6 .
6. The airfoil according to claim 1 , wherein the airfoil is a rotor airfoil.
7. An airfoil comprising:
pressure and suction sides extending between a leading edge and a trailing edge, the airfoil having a camber line along an airfoil section that is equidistant between an exterior surface of the pressure and suction sides, the camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge, wherein a ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5, and wherein the maximum thickness is located along the camber line between 13% and 38% camber position;
wherein the pressure and suction sides extend in a radial direction from a 0% span position to a 100% span position, and the airfoil section is between 5% and 95% span; and
wherein the pressure side has a radius of curvature divided by the axial chord length of between −1 and −3 at a 46% axial position.
8. The airfoil according to claim 7 , wherein the pressure side has the radius of curvature divided by the axial chord length of between 1.6 and 5.2 at a 5% axial position.
9. The airfoil according to claim 8 , wherein the pressure side has the radius of curvature divided by the axial chord length of between −0.1 and −1.6 at a 95% axial position.
10. The airfoil according to claim 7 , wherein the airfoil is a stator airfoil.
11. The airfoil according to claim 7 , wherein the airfoil is a rotor airfoil.
12. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
an airfoil arranged in one of the compressor section and the turbine section, the airfoil having pressure and suction sides extending between a leading edge and a trailing edge, the airfoil having a camber line along an airfoil section that is equidistant between an exterior surface of the pressure and suction sides, the camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge, wherein a ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5, wherein the maximum thickness is located along the camber line between 13% and 38% camber position; and
wherein a thickness of the airfoil as a percentage of the maximum thickness is between 28% and 76% at a 5% camber position, and the thickness of the airfoil as the percentage of the maximum thickness is between 4% and 20% at a 95% camber position.
13. The gas turbine engine according to claim 12 , wherein the airfoil is a stator airfoil.
14. The gas turbine engine according to claim 12 , wherein the airfoil is a rotor airfoil.
15. The gas turbine engine according to claim 12 , wherein the airfoil is arranged in the turbine section.
16. The gas turbine engine according to claim 12 , wherein the pressure side has a radius of curvature divided by the axial chord length of between 1.6 and 5.2 at a 5% axial position, and the radius of curvature divided by the axial chord length of between −0.1 and −1.6 at a 95% axial position.
17. The gas turbine engine according to claim 16 , wherein the pressure side has the radius of curvature divided by the axial chord length of between −1 and −3 at about a 46% axial position.
18. The gas turbine engine according to claim 12 , wherein the thickness of the airfoil as the percentage of the maximum thickness over a camber position of the airfoil section is within a first and a second thickness trend line as shown in FIG. 5 .
19. The gas turbine engine according to claim 18 , wherein the pressure side has a radius of curvature divided by the axial chord length over an axial chord position within a first and a second curvature trend line as shown in FIG. 6 .
20. The gas turbine engine according to claim 12 , wherein the pressure side has a radius of curvature divided by the axial chord length over an axial chord position within a first and a second curvature trend line as shown in FIG. 6 .