Twin rib turbine blade

• US 6,059,530 A
• Filed: 12/21/1998
• Issued: 05/09/2000
• Est. Priority Date: 12/21/1998
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Lee, Ching-Pang
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Barton, Rhonda
• Application Number:
  US09/217,662
• Time in Patent Office: 505 Days
• Field of Search: 416/96 A, 416/97 A, 416/97 R, 416/90, 416/92, 415/115, 415/173.1, 415/173.5
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence

Abstract

A turbine blade includes an airfoil and integral dovetail. The airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending from a root to a tip plate. Twin ribs extend outwardly from the tip plate between the leading and trailing edges, and are spaced laterally apart to define an open-top tip channel therebetween. Each of the tip ribs has an airfoil profile for extracting energy from combustion gases flowable around the turbine blade.

Claims

1. A turbine blade comprising an airfoil and integral dovetail for mounting said airfoil to a rotor disk inboard of a turbine shroud, said airfoil including:

first and second sidewalls joined together at a leading edge and a trailing edge, and extending from a root disposed adjacent said dovetail to a tip plate for channeling thereover combustion gases, and a cooling channel disposed in said airfoil for receiving cooling fluid through said dovetail;

a first tip rib extending outwardly from said tip plate between said leading and trailing edges;

a second tip rib extending outwardly from said tip plate between said leading and trailing edges, and spaced laterally from said first tip rib to define an open-top tip channel having a tip inlet near said leading edge for receiving said combustion gases, and a tip outlet near said trailing edge for discharging said combustion gases; and

each of said first and second tip ribs has an airfoil profile including opposite concave and convex sides extending from said tip inlet to said tip outlet for extracting energy from said combustion gases.

2. A blade according to claim 1 wherein said first and second tip ribs conform with each other for similarly extracting energy from said combustion gases.

3. A blade according to claim 2 wherein said first and second tip ribs laterally face each other at said tip inlet.

4. A blade according to claim 3 wherein said first and second tip ribs are laterally nested, with said convex side of said first tip rib being aligned with said concave side of said second tip rib.

5. A blade according to claim 4 wherein said first and second tip ribs have equal heights from said tip plate between said leading and trailing edges.

6. A blade according to claim 5 wherein:

said first tip rib extends from said leading edge to said trailing edge; and

said second tip rib extends short of said leading and trailing edges.

7. A blade according to claim 5 wherein said first tip rib is laterally offset from said first sidewall at least in part from said leading edge toward said trailing edge to expose a shelf portion of said tip plate.

8. A blade according to claim 7 wherein said second tip rib is coextensive with said second sidewall.

9. A blade according to claim 8 wherein said first tip rib is disposed in part atop said cooling channel, and said tip plate includes a plurality of tip holes extending therethrough in flow communication between said cooling channel and both said tip shelf and tip channel for channeling said cooling fluid thereto.

10. A blade according to claim 8 wherein said first sidewall is a generally concave, pressure sidewall of said airfoil, and said second sidewall is a generally convex, suction sidewall of said airfoil.

11. A turbine airfoil comprising first and second sidewalls joined together at a tip plate extending between leading and trailing edges, and a pair of laterally spaced apart tip ribs extending outwardly from said tip plate, with each tip rib having laterally opposite concave and convex sides initiating at forward ends thereof and terminating at opposite aft ends thereof.

12. An airfoil according to claim 11 wherein said forward ends of both said tip ribs face chordally toward said leading edge.

13. An airfoil according to claim 12 wherein said rib forward ends define an inlet facing said leading edge for receiving combustion gases.

14. An airfoil according to claim 12 wherein a first one of said ribs is chordally longer than a second one of said ribs, and defines an outlet at an aft end thereof.

15. An airfoil according to claim 14 wherein said first rib extends between said leading and trailing edges on only said first sidewall, and said second rib extends short of said leading and trailing edges on only said second sidewall.

16. An airfoil according to claim 15 wherein said first and second ribs have substantially equal lateral thickness.

17. A turbine airfoil comprising twin tip ribs extending chordally between opposite forward and aft ends thereof with aerodynamically conforming lifting profiles.

18. An airfoil according to claim 17 further comprising a leading edge, and said rib forward ends face forwardly toward said leading edge.

19. An airfoil according to claim 18 wherein said ribs include corresponding convex and concave sides facing each other.

20. An airfoil according to claim 19 further comprising opposite pressure and suction sidewalls, and one of said ribs is coextensive with said suction sidewall, and another one of said ribs is offset from said pressure sidewall between said forward and aft ends thereof.