Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately thirty percent pitch and having a first depression with a maximum depression located between twenty percent and eighty percent of the axial chord length of the first airfoil, a second feature spanning approximately thirty percent pitch and having a first peak with a maximum height located between sixty percent and ninety percent of the axial chord length of the first airfoil, and a third feature spanning approximately thirty percent pitch and having a second depression with a maximum depression located between twenty percent and fifty percent of the axial chord length of the second airfoil.

Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil, a second feature adjacent the first feature with the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil, and a third feature adjacent the second feature and first side of the second airfoil with the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil.

Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately thirty percent pitch and having a first depression with a maximum depression located between twenty percent and eighty percent of the axial chord length of the first airfoil, a second feature spanning approximately thirty percent pitch and having a first peak with a maximum height located between sixty percent and ninety percent of the axial chord length of the first airfoil, and a third feature spanning approximately thirty percent pitch and having a second depression with a maximum depression located between twenty percent and fifty percent of the axial chord length of the second airfoil.

Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil, a second feature adjacent the first feature with the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil, and a third feature adjacent the second feature and first side of the second airfoil with the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil.

Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.

Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. 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 scaled by a 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, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. 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 scaled by a 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, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).