US-12618330-B2 - Turbine engine airfoil

Abstract

An apparatus is provided for a turbine engine. This apparatus includes an airfoil, and the airfoil includes a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil. The exterior airfoil surface is formed in conformance with a plurality of cross-section 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 scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.

Inventors

• Abdulhalim Twahir
• Panagiota Tsifourdaris
• Francis GEMME

Assignees

• PRATT & WHITNEY CANADA CORP.

Dates

Publication Date

20260505

Application Date

20240614

Claims (17)

1. 1 . An apparatus for a turbine engine, comprising: an airfoil including a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side; the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil; the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil described by a set of Cartesian coordinates which includes each Cartesian coordinate 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; and the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.
2. 2 . The apparatus of claim 1 , wherein the span location corresponds to a distance from a rotational axis of the turbine engine.
3. 3 . The apparatus of claim 1 , further comprising: an inner platform connected to the airfoil at the first end of the airfoil; and an outer platform connected to the airfoil at the second end of the airfoil.
4. 4 . The apparatus of claim 1 , wherein the apparatus comprises a turbine vane.
5. 5 . The apparatus of claim 4 , wherein the turbine vane is a low pressure turbine vane.
6. 6 . The apparatus of claim 1 , wherein the exterior airfoil surface is an uncoated exterior airfoil surface.
7. 7 . The apparatus of claim 1 , wherein the airfoil is configured without an internal cooling passage.
8. 8 . The apparatus of claim 1 , wherein the airfoil is one of thirty-five airfoils arranged circumferentially about an axis in an annular array.
9. 9 . A stator vane structure for a turbine engine, comprising: a first platform; a second platform; and a plurality of stator vanes arranged circumferentially about an axis in an array, each of the plurality of stator vanes comprising an airfoil; the airfoil including a leading edge, a trailing edge, a pressure side and a suction side; the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first platform to the second platform; the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil defined by a set of Cartesian coordinates which includes each Cartesian coordinate set forth in Table 1, wherein the set of Cartesian coordinates have a tolerance of +/−0.050 inches; 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; and the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.
10. 10 . The stator vane structure of claim 9 , wherein the span location corresponds to a distance from the axis.
11. 11 . The stator vane structure of claim 9 , wherein the plurality of stator vanes are turbine vanes.
12. 12 . The stator vane structure of claim 9 , wherein the exterior airfoil surface is an uncoated exterior airfoil surface.
13. 13 . The stator vane structure of claim 9 , wherein the plurality of stator vanes consist of thirty-five stator vanes.
14. 14 . A turbine engine, comprising: a flowpath, a compressor section, a combustor section and a turbine section; the flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath; the turbine section including a plurality of turbine vanes arranged circumferentially about an axis in an array, each of the plurality of turbine vanes comprising an airfoil located in the flowpath; the airfoil including a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side; the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil; the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil defined by a set of Cartesian coordinates which includes each Cartesian coordinate 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; and the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.
15. 15 . The turbine engine of claim 14 , wherein the turbine section includes a high pressure turbine section and a low pressure turbine section, and the low pressure turbine section includes the plurality of turbine vanes.
16. 16 . The turbine engine of claim 15 , wherein the plurality of turbine vanes are part of a first stage of the low pressure turbine section.
17. 17 . The turbine engine of claim 15 , wherein the exterior airfoil surface is an uncoated exterior airfoil surface.

Description

TECHNICAL FIELD This disclosure relates generally to a turbine engine and, more particularly, to an airfoil for the turbine engine. BACKGROUND INFORMATION A turbine section in a gas turbine engine typically includes one or more stator vane arrays for conditioning (e.g., guiding, turning, etc.) combustion products flowing through a flowpath. Various airfoil designs are known in the art for such turbine stator vane array applications. While these known airfoil designs have various benefits, there is still room in the art for improvement. SUMMARY According to an aspect of the present disclosure, an apparatus is provided for a turbine engine. This apparatus includes an airfoil, and the airfoil includes a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil. The exterior airfoil surface is formed in conformance with a plurality of cross-section 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 scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location. According to another aspect of the present disclosure, a stator vane structure is provided for a turbine engine. This stator vane structure includes a first platform, a second platform and a plurality of stator vanes arranged circumferentially about an axis in an array. Each of the stator vanes include an airfoil. The airfoil includes a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first platform to the second platform. The exterior airfoil surface is formed in conformance with a plurality of cross-section profiles of the airfoil defined 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 scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location. According to still another aspect of the present disclosure, a turbine engine is provided that includes a flowpath, a compressor section, a combustor section and a turbine section. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The turbine section includes a plurality of turbine vanes arranged circumferentially about an axis in an array. Each of the turbine vanes includes an airfoil located in the flowpath. The airfoil includes a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side. The leading edge and the trailing edge are joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil. The exterior airfoil surface is formed in conformance with a plurality of cross-section profiles of the airfoil defined 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 scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location. The turbine section may include a high pressure turbine section and a low pressure turbine section. The low pressure turbine section may include the turbine vanes. The turbine vanes may be part of a second stage of the low pressure turbine section. The set of Cartesian coordinates set forth in the Table 1 may have a tolerance of +/−0.050 inches. The exterior airfoil surface may be an uncoated exterior airfoil surface. The set of Cartesian coordinates set forth in the Table 1 may have a tolerance of +/−0.050 inches. The span location may correspond to a distance from the axis. The stator vanes may be turbine vanes. The exterior airfoil surface may be an uncoated exterior airfoil surface. The stator vanes may only include thirty-five stator vanes. The set of Cartesian coordinates set forth in the Table 1 may have a tolerance of +/−0.050 inches. The span location may correspond to a distance from a rotational axis of the turbine engine. The apparatus may also include an inner platform and an outer platform. T