Endwall contouring

Patent metadata

Field	Value
Publication number	US-9212558-B2
Application number	US-201213663977-A
Country	US
Kind code	B2
Filing date	Oct 30, 2012
Priority date	Sep 28, 2012
Publication date	Dec 15, 2015
Grant date	Dec 15, 2015

Abstract

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 airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

First claim

What is claimed is:

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;
a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils, the convex profiled region gradually increasing in radial height from the first side of said at least one of said plurality of airfoils to a local maximum in radial extent, the local maximum in radial extent being separated by a predetermined distance from the first side of said at least one of said plurality of airfoils; and
a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

2. The airfoil array of claim 1 , wherein the concave profiled region begins where the convex profiled region ends.

3. The airfoil array of claim 1 , wherein the concave profiled region is near mid-chord of the airfoil.

4. The airfoil array of claim 1 , wherein the local maximum in radial extent of the convex profiled region is positioned between the leading edge and mid-chord.

5. The airfoil array of claim 1 , wherein a local minimum in radial extent of the concave profiled region is positioned near mid-chord.

6. The airfoil array of claim 1 , wherein each airfoil has an axial chord, and a local maximum in radial extent of the convex profiled region is disposed between about 0% to about 50% of the axial chord.

7. The airfoil array of claim 1 , wherein each airfoil has an axial chord, and a local minimum in radial extent of the concave profiled region is disposed between about 30% to about 80% of the axial chord.

8. The airfoil array of claim 1 , wherein the airfoils are circumferentially spaced apart thereby defining a plurality of flow passages between adjacent airfoils, and each flow passage has a passage width.

9. The airfoil array of claim 8 , wherein the local maximum in radial extent of the convex profiled region is disposed between about 0% to about 50% of the passage width.

10. The airfoil array of claim 8 , wherein a local minimum in radial extent of the concave profiled region is disposed between about 0% to about 50% of the passage width.

11. The airfoil array of claim 1 , wherein the first side is a pressure side of an airfoil.

12. The airfoil array of claim 1 , wherein the opposite second side is a suction side of an airfoil.

13. 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 having a plurality of airfoils circumferentially spaced apart and projecting radially from an endwall, the airfoils and endwall 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 adjacent to the first side of at least one of said plurality of airfoils a convex profiled surface near the leading edge and a concave profiled surface aft of the convex profiled surface, the convex profiled surface gradually increasing in radial height from the first side of said at least one of said plurality of airfoils to a local maximum in radial extent, the local maximum in radial extent being separated by a predetermined distance from the first side of said at least one of said plurality of airfoils.

14. The gas turbine engine of claim 13 , wherein the convex profiled surface gradually increases in radial height to the local maximum in radial extent from a surface of the endwall adjacent to the convex profiled surface.

15. The gas turbine engine of claim 14 , wherein each airfoil has an axial chord, and the local maximum in radial extent of the convex profiled surface is disposed between about 0% to about 50% of the axial chord.

16. The gas turbine engine of claim 15 , wherein each flow passage has a passage width, and the local maximum in radial extent of the convex profiled surface is disposed between about 0% to about 50% of the passage width.

17. The gas turbine engine of claim 13 , wherein the concave profiled surface gradually decreases in radial height to a local minimum in radial extent from a surface of the endwall adjacent to the concave profiled surface.

18. The gas turbine engine of claim 17 , wherein each airfoil has an axial chord, and the local minimum in radial extent of the concave profiled surface is disposed between about 30% to about 80% of the axial chord.

19. The gas turbine engine of claim 18 , wherein each flow passage has a passage width, and the local minimum in radial extent of the concave profiled surface is disposed between about 0% to about 50% of the passage width.

20. The gas turbine engine of claim 13 , wherein the first side is a pressure side of an airfoil and the opposite second side is a suction side of an airfoil.

Assignees

• United Technologies Corp

Inventors

• Praisner Thomas J
• Aggarwala Andrew S
• Grover Eric A
• Jurek Renee J

Classifications

• F05D2240/305

  related to the pressure side of a rotor blade · CPC title

• F05D2240/123

  related to the pressure side of a stator vane · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F05D2250/712

  concave · CPC title