Gas turbine engine turbine blade airfoil profile
A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial 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 are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
1. A turbine blade for a gas turbine engine comprising:
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 radial direction to a tip; and
wherein 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, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
2. The turbine blade according to claim 1 , wherein the airfoil is a second stage turbine blade.
3. The turbine blade according to claim 1 , wherein the span location corresponds to a distance from a rotational axis of the airfoil.
4. 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).
5. A gas turbine engine comprising:
a compressor section;
a combustor fluidly connected to the compressor section;
a turbine section fluidly connected to the combustor, the turbine section comprising:
a high pressure turbine coupled to the high pressure compressor via a shaft;
a low pressure turbine; and
wherein the high pressure turbine includes an array of turbine blades, wherein at least one turbine blade includes 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 radial direction to a tip; and
wherein 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, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
6. The gas turbine engine according to claim 5 , wherein the array is a second stage array of turbine blades.
7. The gas turbine engine according to claim 6 , wherein the high pressure turbine includes an array of fixed stator vanes upstream from the first stage array of turbine blades.
8. The gas turbine engine according to claim 6 , wherein the second stage array of turbine blades includes forty-four turbine blades.
9. The gas turbine engine according to claim 5 , wherein the span location corresponds to a distance from a rotational axis of the airfoil.
10. The gas turbine engine according to claim 5 , wherein the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.050 inches (±1.27 mm).
11. The gas turbine engine according to claim 5 , wherein the high pressure turbine consists of two arrays of turbine blades and two arrays of fixed stator vanes.