CURVED PLATFORM TURBINE BLADE

• US 20100158696A1
• Filed: 12/24/2008
• Published: 06/24/2010
• Est. Priority Date: 12/24/2008
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Clements, Jeffrey Donald, Pandey, Vidhu Shekhar, Lee, Ching-Pang, Schilling, Jan Christopher, Wadia, Aspi Rustom, Keith, Brian David
• Granted Patent: US 8,459,956 B2
• Time in Patent Office: Days
• US Class Current: 416/243
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2270/17 to control boundary layer
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.

Claims

1. A turbine blade comprising:

an airfoil integrally joined to a platform and a dovetail, and having laterally opposite pressure and suction sides extending longitudinally in span from said platform, and axially in chord between opposite leading and trailing edges;

said platform being contoured in elevation to include an elevated ridge and a depressed trough having complementary portions on said opposite sides of said airfoil between laterally opposite first and second splitline edges; and

said dovetail and said first and second edges being axially arcuate at correspondingly constant lateral radii.

2. A blade according to claim 1 wherein both said pressure side and first edge are laterally concave, and both said suction side and second edge are laterally convex.

3. A blade according to claim 2 wherein said ridge adjoins said airfoil, and said trough adjoins said first edge.

4. A blade according to claim 3 wherein said trough extends from said leading edge to said trailing edge along said first edge.

5. A blade according to claim 4 wherein said ridge is disposed aft atop said platform and extends aft from said trailing edge, and said first edge curves aft with said aft ridge.

6. A blade according to claim 5 further comprising an elevated forward ridge adjoining said leading edge along said pressure side, and said first edge curves forward with said forward ridge.

7. A blade according to claim 6 wherein said trough is disposed laterally between said first edge and both said forward and aft ridges.

8. A blade according to claim 6 wherein:

said aft ridge, trough, and first edge converge axially aft together; and

said forward ridge, trough, and first edge converge axially forward together.

9. A blade according to claim 6 wherein said trough is bounded forward by said forward ridge, aft by said aft ridge, and laterally between said pressure side and said first edge.

10. A blade according to claim 9 wherein said forward ridge has a maximum height adjacent said leading edge, said aft ridge has a smaller maximum height adjacent said trailing edge, and said trough has a smaller maximum depth laterally between said first edge and pressure side and axially between said trailing edge and a midchord of said airfoil.

11. A turbine blade comprising:

an airfoil integrally joined to a platform and a dovetail;

said platform being contoured in elevation to include an elevated ridge and a depressed trough; and

both said platform and dovetail being axially arcuate.

12. A blade according to claim 11 wherein said platform has laterally opposite first and second splitline edges being axially arcuate at a lateral radius, and said dovetail has a similar lateral radius.

13. A blade according to claim 12 wherein:

said airfoil includes laterally opposite pressure and suction sides extending longitudinally in span from said platform, and axially in chord between opposite leading and trailing edges; and

both said pressure side and first edge are laterally concave, and both said suction side and second edge are laterally convex.

14. A blade according to claim 13 wherein said ridge adjoins said airfoil, and said trough adjoins said first edge.

15. A blade according to claim 14 wherein said trough extends from said leading edge to said trailing edge along said first edge.

16. A blade according to claim 15 wherein said first edge has a constant lateral radius between said leading and trailing edges.

17. A blade according to claim 15 wherein said ridge is disposed aft atop said platform and extends aft from said trailing edge, and said first edge curves aft with said aft ridge.

18. A blade according to claim 17 wherein said first edge curves laterally from said aft ridge.

19. A blade according to claim 18 wherein said trough is disposed laterally between said aft ridge and said first edge.

20. A blade according to claim 17 wherein said aft ridge, trough, and first edge converge axially aft together.

21. A blade according to claim 17 further comprising an elevated forward ridge adjoining said leading edge along said pressure side, and said first edge curves forward with said forward ridge.

22. A blade according to claim 21 wherein said forward ridge, trough, and first edge converge axially forward together.

23. A blade according to claim 21 wherein said trough is bounded forward by said forward ridge, aft by said aft ridge, and laterally between said pressure side and said first edge.

24. A blade according to claim 23 wherein said forward ridge has a maximum height adjacent said leading edge, said aft ridge has a smaller maximum height adjacent said trailing edge, and said trough has a smaller maximum depth laterally between said first edge and pressure side and axially between said trailing edge and a midchord of said airfoil.

25. A blade according to claim 21 wherein said platform along said suction side includes complementary portions of said forward and aft ridges and trough therebetween extending axially along said second edge.

26. A blade according to claim 21 wherein said first edge of joins a trailing edge of said platform at an acute included angle, and joins a leading edge of said platform at a normal included angle.