Turbine blade airfoil profile
A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
1. A turbine blade for a gas turbine engine, the turbine blade comprising:
an airfoil having a leading and a trailing edge joined by a pressure and a suction side to provide an external airfoil surface extending from a platform in a spanwise direction to a tip; and
wherein the external airfoil surface is formed in substantial conformance with cross-section profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1 and incorporated by reference herein, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.
2. The turbine blade according to claim 1 , wherein the airfoil is a low pressure turbine blade.
3. The turbine blade according to claim 1 , wherein the airfoil is a first-stage, second-stage, third-stage, fourth-stage or a fifth-stage low pressure turbine blade.
4. The turbine blade according to claim 1 , wherein the span location corresponds to a distance from a rotation axis of the airfoil.
5. The turbine blade according to claim 1 , wherein the external airfoil surface is formed in the substantial conformance with the cross-section profiles of the airfoil defined by the set of Cartesian coordinates set forth in Table 1 to a tolerance of ±0.050 inches (±1.27 mm) relative to the Cartesian coordinates.
6. The turbine blade according to claim 1 , wherein the external airfoil surface is a cold, uncoated airfoil surface at nominal definition.
7. The turbine blade according to claim 6 , further comprising a coating over the external airfoil surface.
8. A low pressure turbine blade comprising:
a platform; and
an airfoil extending in a spanwise direction from the platform to a tip, the airfoil having an external airfoil surface formed in substantial conformance with cross-section airfoil profiles defined by a set of Cartesian coordinates set forth in Table 1 and incorporated by reference herein.
9. The low pressure turbine blade according to claim 8 , wherein the Cartesian coordinates in Table 1 have Cartesian coordinate values provided for a cold uncoated condition at nominal definition.
10. The low pressure turbine blade according to claim 8 , wherein the tip is shrouded.
11. The low pressure turbine blade according to claim 8 , wherein the external airfoil surface is formed in the substantial conformance with the cross-section profiles of the airfoil defined by the set of Cartesian coordinates set forth in Table 1 to a tolerance of ±0.050 inches (±1.27 mm) relative to the Cartesian coordinates.
12. The low pressure turbine blade according to claim 9 , further comprising a coating over the external airfoil surface.
13. A gas turbine engine comprising:
a low pressure (LP) turbine configured to drive a low pressure compressor;
wherein the LP turbine comprises at least one stage of turbine blades, wherein at least one of the turbine blades of the at least one stage comprises an airfoil having leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a span direction to a tip; and
wherein the external airfoil surface is formed in substantial conformance with cross-section profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1 and incorporated by reference herein, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
14. The gas turbine engine according to claim 13 , wherein the span location corresponds to a distance from a rotation axis of the airfoil.
15. The gas turbine engine according to claim 13 , wherein the external airfoil surface is formed in the substantial conformance with the cross-section profiles of the airfoil defined by the set of Cartesian coordinates set forth in Table 1 to a tolerance of ±0.050 inches (±1.27 mm) relative to the Cartesian coordinates.
16. The gas turbine engine according to claim 13 , wherein the exterior airfoil surface is a cold, uncoated airfoil surface at nominal definition.
17. The gas turbine engine according to claim 13 , wherein the at least one stage of turbine blades includes between 1 to 5 stages, and wherein at least one of the 1 to 5 stages comprises the at least one of the turbine blades.
18. The gas turbine engine according to claim 17 , wherein the at least one of the turbine blades is a first stage LP turbine blade.
19. The gas turbine engine according to claim 13 , wherein the at least one stage of turbine blades includes an array of fifty-one (51) turbine airfoils.
20. The gas turbine engine according to claim 13 , wherein the gas turbine engine is a turboprop or a turboshaft engine having 1 to 3 independently rotatable spools.