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 exterior 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 described 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 edge and a trailing edge joined by a pressure side and a suction side to provide an exterior airfoil surface extending from a platform in a spanwise direction to a tip; and
wherein the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described 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 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 high pressure turbine blade.
3. The turbine blade according to claim 1 , wherein the airfoil is a first-stage high 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 Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.050 inches (±1.27 mm).
6. The turbine blade according to claim 1 , wherein the Cartesian coordinates define points on a cold, uncoated airfoil surface at nominal restagger, in a plane at the span location.
7. A first-stage high 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 conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates set forth in Table 1.
8. The first-stage high pressure turbine blade according to claim 7 , wherein the Cartesian coordinates in Table 1 have Cartesian coordinate values for a cold uncoated condition at nominal restagger.
9. The first-stage high pressure turbine blade according to claim 7 , wherein the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.050 inches (±1.27 mm).
10. A gas turbine engine comprising:
a high pressure turbine configured to drive a high pressure compressor;
wherein the high pressure turbine comprises a first stage array of turbine blades, wherein at least one of the turbine blades of the first stage array comprises an airfoil having leading and trailing edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a span direction to a tip; and
wherein the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described 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 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.
11. The gas turbine engine according to claim 10 , wherein the span location corresponds to a distance from a rotation axis of the airfoil.
12. The gas turbine engine according to claim 10 , wherein the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.050 inches (±1.27 mm).
13. The gas turbine engine according to claim 10 , wherein the Cartesian coordinates define points on a cold, uncoated airfoil surface at nominal restagger, in a plane at the span location.
14. The gas turbine engine according to claim 10 , wherein the high pressure turbine has a single stage of high pressure turbine blades.
15. The gas turbine engine according to claim 10 , wherein the high pressure compressor has a single stage of compressor blades.
16. The gas turbine engine according to claim 10 , wherein the first stage array of turbine blades of the high pressure turbine comprises 27 turbine airfoils.
17. The gas turbine engine according to claim 10 , wherein the gas turbine engine has an output shaft connectable to a load.