Endwall contouring
An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages.
1. An airfoil array, comprising:
an endwall;
a plurality of airfoils radially projecting from the endwall, each airfoil having a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge, the airfoils circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils;
a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils; and
a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages, the concave profiled region gradually decreasing in radial height from a surface of the endwall adjacent the concave profiled region to a local minimum in radial extent, the local minimum in radial extent centered mid-chord of the at least one of said plurality of airfoils.
2. The airfoil array of claim 1 , wherein the convex profiled region is adjacent to the leading edge of the airfoil.
3. The airfoil array of claim 1 , wherein a local maximum in radial extent of the convex profiled region is positioned axially upstream of the leading edge of the airfoil.
4. The airfoil array of claim 1 , wherein the local minimum in radial extent of the concave profiled region is disposed and near mid-passage of the flow passage.
5. The airfoil array of claim 1 , wherein the concave profiled region extends along a majority of an axial chord of the airfoil.
6. The airfoil array of claim 1 , wherein the local minimum in radial extent of the concave profiled region is disposed between about 30% to about 80% of an axial chord.
7. The airfoil array of claim 1 , wherein the local minimum in radial extent of the concave profiled region is disposed between about 30% to about 70% of a passage width.
8. The airfoil array of claim 1 , wherein the first side is a pressure side of an airfoil.
9. The airfoil array of claim 1 , wherein the opposite second side is a suction side of an airfoil.
10. A gas turbine engine, comprising:
a compressor section;
a combustor section downstream of the compressor section; and
a turbine section downstream of the combustor section, one of the compressor section and the turbine section having at least one airfoil array including a plurality of airfoils circumferentially spaced apart and projecting radially from an endwall, the airfoils establishing a plurality of flow passages, each airfoil having a first side, an opposite second side, a leading edge, and a trailing edge, the endwall having a convex profiled surface near the leading edge of at least one of said plurality of airfoils and a concave profiled surface near a center of at least one of said plurality of flow passages, the concave profiled surface gradually decreasing in radial height from a surface of the endwall adjacent the concave profiled surface to a local minimum in radial extent, the local minimum in radial extent centered mid-chord of the at least one of said plurality of airfoils.
11. The gas turbine engine of claim 10 , wherein the convex profiled surface gradually increases in radial height to a local maximum in radial extent from a surface of the endwall adjacent to the convex profiled surface.
12. The gas turbine engine of claim 10 , wherein a local maximum in radial extent is disposed adjacent to and axially upstream of the leading edge of the airfoil.
13. The gas turbine engine of claim 10 , wherein a radial height of the convex profiled surface decreases as the convex profiled surface extends axially upstream from the leading edge of the airfoil.
14. The gas turbine engine of claim 10 , wherein the local minimum in radial extent is positioned near the center of the flow passage.
15. The gas turbine engine of claim 10 , wherein a radial height of the concave profiled surface increases as the concave profiled surface extends axially and laterally from the local minimum in radial extent of the concave profiled surface to a surface of the endwall that is adjacent to the concave profiled surface.
16. The gas turbine engine of claim 10 , wherein the convex profiled surface and the concave profiled surface of the endwall are configured to direct flow throughout the flow passage.
17. The gas turbine engine of claim 10 , wherein the first side is a pressure side of an airfoil.
18. The gas turbine engine of claim 10 , wherein the opposite second side is a suction side of an airfoil.