Turbine vane
A turbine vane for a gas turbine engine, including: a first airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform, wherein a portion of the exterior airfoil surface of the first airfoil is formed in conformance with a set of Cartesian coordinates set forth in Table 1 as offset by corresponding values in Table 4, and wherein the values of Table 4 are offset from a point of origin that is a point where a radially outward surface of the inner platform meets a surface of a trailing edge of the inner platform and a surface of a mate face of the inner platform.
1. A turbine vane for a gas turbine engine, comprising:
a first airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform, wherein a portion of the exterior airfoil surface of the first airfoil is formed in conformance with a set of Cartesian coordinates set forth in Table 1 as offset by corresponding values in Table 4, and wherein the values of Table 4 are offset from a point of origin that is a point where a radially outward surface of the inner platform meets a surface of a trailing edge of the inner platform and a surface of a mate face of the inner platform, wherein the set of Cartesian coordinates in Table 1 have a tolerance of ±0.020 inches (±0.508 mm).
2. The turbine vane according to claim 1 , wherein the turbine vane is a second stage turbine vane.
3. The turbine vane of claim 1 , wherein the inner platform, the first airfoil and the outer platform are cast as a single part.
4. The turbine vane of claim 1 , wherein other portions of the exterior airfoil surface of the first airfoil are formed in conformance with a set of Cartesian coordinates set forth in Tables 2 and 3 as offset by corresponding values in Table 4.
5. The turbine vane of claim 1 , further comprising:
a second airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from the inner platform in a radial direction to the outer platform.
6. A turbine stator assembly for a gas turbine engine, comprising:
a plurality of turbine vanes secured about an axis, each of the plurality of turbine vanes having:
a first airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform, wherein a portion of the exterior airfoil surface of the first airfoil is formed in conformance with a set of Cartesian coordinates set forth in Table 1 as offset by corresponding values in Table 4, and wherein the values of Table 4 are offset from a point of origin that is a point where a radially outward surface of the inner platform meets a surface of a trailing edge of the inner platform and a surface of a mate face of the inner platform, wherein the set of Cartesian coordinates in Table 1 have a tolerance of ±0.020 inches (±0.508 mm).
7. The turbine stator assembly of claim 6 , wherein the turbine stator assembly is a second stage turbine stator assembly of a high pressure turbine of the gas turbine engine.
8. The turbine stator assembly of claim 6 , wherein each of the plurality of turbine vanes further comprises:
a second airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from the inner platform in a radial direction to the outer platform.
9. The turbine stator assembly of claim 8 , wherein the inner platform, the first airfoil, the second airfoil and the outer platform are cast as a single part.
10. The turbine stator assembly of claim 6 , wherein other portions of the exterior airfoil surface of the first airfoil are formed in conformance with a set of Cartesian coordinates set forth in Tables 2 and 3 as offset by corresponding values in Table 4.
11. 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 a high pressure compressor of the compressor section via a shaft;
a low pressure turbine; and
wherein the high pressure turbine includes a turbine stator assembly comprising:
a plurality of turbine vanes secured about an axis, each of the plurality of turbine vanes having:
a first airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform, wherein a portion of the exterior airfoil surface of the first airfoil is formed in conformance with a set of Cartesian coordinates set forth in Table 1 as offset by corresponding values in Table 4, and wherein the values of Table 4 are offset from a point of origin that is a point where a radially outward surface of the inner platform meets a surface of a trailing edge of the inner platform and a surface of a mate face of the inner platform, wherein the set of Cartesian coordinates in Table 1 have a tolerance of ±0.020 inches (±0.508 mm).
12. The gas turbine engine of claim 11 , wherein the turbine stator assembly is a second stage turbine stator assembly of the gas turbine engine.
13. The gas turbine engine of claim 11 , wherein the inner platform, the first airfoil, and the outer platform are cast as a single part.
14. The gas turbine engine of claim 11 , further comprising:
a second airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from the inner platform in a radial direction to the outer platform.