Gas turbine engine with non-axisymmetric surface contoured rotor blade platform

Patent metadata

Field	Value
Publication number	US-9976433-B2
Application number	US-75321110-A
Country	US
Kind code	B2
Filing date	Apr 2, 2010
Priority date	Apr 2, 2010
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a compressor section;
a combustor section; and
a turbine section,
said turbine section including at least one stator vane and at least one rotating blade,
said at least one stator vane including an inner vane platform section, said inner vane platform section having a leading edge, a trailing edge, and two circumferentially spaced edges, and
said at least one rotating blade including a root section, an airfoil section, and a rotor platform section between said root section and said airfoil section, said rotor platform having a leading edge, a trailing edge, and two circumferentially spaced edges;
wherein said at least one stator vane and said at least one rotating blade define a clearance gap in a radial direction between an upper surface of one of said inner vane platform section and said rotor platform section and an undersurface of the other one of said inner vane platform section and said rotor platform section;
wherein at least one of said rotor platform section and said inner vane platform section has a non-axisymmetric surface contour on a surface defining a portion of said clearance gap, said surface contour being curved and non-axisymmetric about an axis defined extending from the leading edge to the trailing edge of said at least one of said rotor platform section and said inner vane platform section, wherein said surface contour is designed to counteract non-uniform static pressure distortions engendered by combustion products flowing within said clearance gap.

2. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour is located on said undersurface of said at least one of said rotor platform section and said inner vane platform section.

3. The gas turbine engine of claim 2 , wherein said undersurface is contoured in a radial direction.

4. The gas turbine engine of claim 2 , wherein said undersurface is contoured in an axial direction.

5. The gas turbine engine of claim 1 , wherein said turbine section includes a plurality of circumferentially spaced stator vanes and a plurality of circumferentially spaced rotating blades.

6. The gas turbine engine of claim 1 , wherein said rotor platform includes a surface contoured in an axial direction.

7. The gas turbine engine of claim 1 , wherein said rotor platform section includes a surface contoured in a radial direction.

8. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour is located on said upper surface of said rotor platform section.

9. The gas turbine engine of claim 8 , wherein said non-axisymmetric surface contour is contoured in a radial direction.

10. The gas turbine engine of claim 8 , wherein said rotor platform includes a surface contoured in an axial direction.

11. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour defines a portion of a core flow path.

12. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour defines a vertical face located along a trailing edge of said rotor platform section.

13. The gas turbine engine of claim 12 , wherein said non-axisymmetric surface contour is contoured in an axial direction.

14. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour defines a vertical face located along a leading edge of said rotor platform section.

15. The gas turbine engine of claim 14 , wherein said non-axisymmetric surface contour is contoured in an axial direction.

16. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour is a first non-axisymmetric surface contour being contoured in a radial direction, and wherein said platform includes a second non-axisymmetric surface contour being contoured in an axial direction.

17. The gas turbine engine of claim 16 , wherein said first and second non-axisymmetric surface contours are both located on one of a leading portion and a trailing portion of said rotor platform section.

18. The gas turbine engine of claim 1 , wherein said rotor platform section includes an intermediate face extending in a radial direction and positioned between said leading edge and said trailing edge of said rotor platform section.

19. The gas turbine engine of claim 18 , wherein said non-axisymmetric surface contour is located on said intermediate face.

20. The gas turbine engine of claim 19 , wherein said rotor platform section includes a second non-axisymmetric surface contour.

21. The gas turbine engine of claim 1 , wherein said inner vane platform section and said rotor platform section overlap each other in an axial direction.

22. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour includes at least one concave segment.

23. The gas turbine engine of claim 1 , wherein said non-axisymmetric surface contour includes at least two convex segments.

Assignees

• Praisner Thomas J
• Grover Eric A
• United Technologies Corp

Inventors

• Praisner Thomas J
• Grover Eric A

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2250/61

  corrugated · CPC title

• F01D5/225

  by shrouding · CPC title

• F01D5/143

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

• F01D11/00 Primary

  Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) · CPC title