TURBINE AIRFOIL WITH VARIABLE AND COMPOUND FILLET

• US 20060275112A1
• Filed: 06/06/2005
• Published: 12/07/2006
• Est. Priority Date: 06/06/2005
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bailey, James Robert, Guentert, Joseph Michael, Lee, Ching-Pang
• Granted Patent: US 7,371,046 B2
• Time in Patent Office: Days
• US Class Current: 415/191
• 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: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine airfoil may be a rotating blade having a single platform, or a stationary nozzle having a pair of platforms. The airfoil body has pressure and suction sidewalls extending between leading and trailing edges. A compound fillet is disposed between the airfoil body and at least one of the platforms. The compound fillet includes a concave first fillet having a first radius, and a concave second fillet having a second, greater radius. The second fillet extends from the leading edge downstream along the suction sidewall and terminates at a point upstream of the trailing edge. The second fillet may also extend downstream from the leading edge along the pressure sidewall.

Claims

1. An airfoil for a gas turbine engine, comprising:

an arcuate inner band having an inner platform; and

an airfoil body extending outwardly from inner platform, said airfoil body having opposed pressure and suction sidewalls extending between a leading edge and a trailing edge thereof, said airfoil having an inner compound fillet, comprising;

a concave first inner fillet disposed between said airfoil and said inner platform, said first inner fillet having a first radius and extending around the periphery of said airfoil; and

a concave second inner fillet disposed between said airfoil and said inner platform, said second inner fillet extending from said leading edge aftward along said suction sidewall and terminating at a point axially forward of said trailing edge, said second fillet having a second radius greater than said first radius.

2. The airfoil of claim 1 wherein said suction sidewall includes a high C point defining a transition between relatively less curved forward and aft portions thereof;

and a maximum width of said second inner fillet is disposed at said high C point.

3. The airfoil of claim 1 wherein said width of said second inner fillet smoothly tapers from said maximum width in an aftward direction to merge with said first inner fillet upstream of said trailing edge.

4. The airfoil of claim 1 in which said second inner fillet is disposed radially outward of said first inner fillet and overlaps said first inner fillet in a radial direction.

5. The airfoil of claim 1 wherein said second inner fillet further extends from said leading edge aftward along said pressure sidewall and terminates at a point axially forward of said trailing edge

6. The turbine nozzle segment of claim 5 wherein a width of said second outer fillet along said pressure sidewall is at a maximum near said leading edge and tapers in an aft direction.

7. A turbine nozzle segment, comprising:

an arcuate outer band having an outer platform;

an arcuate inner band having an inner platform; and

an airfoil disposed between said inner and outer bands, said airfoil having opposed pressure and suction sidewalls extending between a leading edge and a trailing edge thereof, said airfoil having an outer compound fillet, comprising;

a concave first outer fillet disposed between said airfoil and said outer platform, said first outer fillet having a first radius; and

a concave second outer fillet disposed between said airfoil and said outer platform, said second outer fillet extending from said leading edge downstream along said suction sidewall and terminating at a point upstream of said trailing edge, said second outer fillet having a second radius greater than said first radius.

8. The turbine nozzle segment of claim 7 wherein said suction sidewall of said airfoil includes a high C point disposed aft of said leading edge, and said second outer fillet extends from said leading edge past said high C point.

9. The turbine nozzle segment of claim 8 wherein said second outer fillet has a maximum width at said high C point, said width tapering in an aft direction.

10. The turbine nozzle segment of claim 7 wherein said second outer fillet further extends from said leading edge downstream along said pressure sidewall and terminates at a point upstream of said trailing edge.

11. The airfoil of claim 7 in which said second outer fillet is disposed radially inward of said first outer fillet and overlaps said first outer fillet in a radial direction.

12. The turbine nozzle segment of claim 7 further including an inner compound fillet, comprising:

a concave first inner fillet disposed between said airfoil and said inner platform, said first fillet having a first radius; and

a concave second inner fillet disposed between said airfoil and said inner platform, said second inner fillet extending from said leading edge downstream along said suction sidewall and terminating at a point upstream of said trailing edge, said second fillet having a second radius greater than said first radius.

13. The airfoil of claim 12 in which said second inner fillet is disposed radially outward of said first inner fillet and overlaps said first inner fillet in a radial direction.

14. The turbine nozzle segment of claim 12 wherein said suction sidewall of said airfoil includes a high C point disposed aft of said leading edge, and said second inner fillet extends from said leading edge past said high C point.

15. The turbine nozzle segment of claim 14 wherein said second inner fillet has a maximum width at said high C point, said width tapering in an aft direction.

16. The turbine nozzle segment of claim 7 wherein said second inner fillet further extends from said leading edge downstream along said pressure sidewall and terminates at a point upstream of said trailing edge.

17. The turbine nozzle segment of claim 16 wherein a width of said inner fillet along said pressure sidewall is at a maximum near said leading edge and tapers in an aft direction.