Non-axisymmetric end wall contouring with aft mid-passage peak

1. A turbine section comprising:

a pair of adjacent turbine airfoils, each airfoil including a first side, a second side, a leading edge, a trailing edge, and an axial chord length extending between the leading edge and the trailing edge, the pair of turbine airfoils having a first airfoil and a second airfoil; and

an endwall extending between the second side of the first airfoil and the first side of the second airfoil, the endwall comprising:

a first feature adjacent the second side of the first airfoil between the leading edge and the trailing edge, the first feature spanning thirty percent pitch and having a first depression with a maximum depression located only between twenty percent and eighty percent of the axial chord length of the first airfoil;

a second feature adjacent the first feature between the leading edge and the trailing edge of the first airfoil, the second feature spanning thirty percent pitch and having a first peak with a maximum height located only between sixty percent and ninety percent of the axial chord length of the first airfoil; and

a third feature adjacent the second feature and the first side of the second airfoil between the leading edge and the trailing edge, the third feature spanning thirty percent pitch and having a second depression with a maximum depression located only between twenty percent and fifty percent of an axial chord length of the second airfoil.

2. The turbine section of claim 1 , wherein the pair of airfoils are incident tolerant airfoils.

3. The turbine section of claim 1 , wherein the first side of each of the pair of airfoils is a suction side and the second side of each of the pair of airfoils is a pressure side.

4. The turbine section of claim 1 , wherein the first maximum depression of the first depression is located between forty-five and fifty-five percent of the axial chord length of the first airfoil.

5. The turbine section of claim 1 , wherein the maximum height of the first peak is located between seventy-five and eighty-five percent of the axial chord length of the first airfoil.

6. The turbine section of claim 1 , wherein the second maximum depression of the second depression is located between twenty-five and thirty-five percent of the axial chord length of the second airfoil.

7. The turbine section of claim 1 , wherein the endwall extends between an inner diameter of the pair of airfoils.

8. The turbine section of claim 1 , wherein at least a portion of the second feature extends axially rearward of the trailing edge of the first airfoil.

9. The turbine section of claim 1 , wherein the second feature extends from thirty-five percent to sixty-five percent pitch.

10. The turbine section of claim 1 , wherein the second feature extends from forty percent to seventy percent pitch.

11. The turbine section of claim 1 , wherein at least one of the first feature, the second feature, or the third feature includes a flat portion along the first depression, the first peak, or the second depression.

12. A gas turbine engine comprising:

a variable speed power turbine;

an annular turbine stage;

a plurality of airfoils each having a first side, a second side, a leading edge, a trailing edge, the plurality of airfoils having a first airfoil and a second airfoil; and

an endwall extending between the second side of the first airfoil and the first side of the second airfoil, the endwall comprising:

a first feature adjacent the second side of the first airfoil between the leading edge and the trailing edge, the first feature spanning thirty percent pitch and having a first depression with a first maximum depression located only between twenty percent and eighty percent of an axial chord length of the first airfoil;

a second feature adjacent the first feature between the leading edge and the trailing edge of the first airfoil, the second feature spanning thirty percent pitch and having a first peak with a maximum height located only between sixty percent and ninety 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 between the leading edge and the trailing edge, the third feature spanning thirty percent pitch and having a second depression with a second maximum depression located only between twenty percent and fifty percent of an axial chord length of the second airfoil.

13. The gas turbine engine of claim 12 , wherein the plurality of airfoils are incident tolerant airfoils.

14. The gas turbine engine of claim 12 , wherein the first side of each of the plurality of airfoils is a pressure side and the second side of each of the plurality of airfoils is a suction side.

15. The gas turbine engine of claim 12 , wherein the first maximum depression of the first depression is located between forty-five and fifty-five percent of the axial chord length of the first airfoil.

16. The gas turbine engine of claim 12 , wherein the second maximum depression of the second depression is located between twenty-five and thirty-five percent of the axial chord length of the second airfoil.

17. The gas turbine engine of claim 12 , wherein the endwall extends between an inner diameter of the plurality of airfoils.

18. The gas turbine engine of claim 12 , wherein at least a portion of the second feature extends axially rearward of the trailing edge of the first airfoil.

19. The gas turbine engine of claim 12 , wherein the second feature extends from thirty-five percent to sixty-five percent pitch.

20. The gas turbine engine of claim 12 , wherein at least one of the first feature, the second feature, or the third feature includes a flat portion along an adjacent one of the first feature, the second feature, or the third feature.