Stepped outlet turbine airfoil

• US 7,246,999 B2
• Filed: 10/06/2004
• Issued: 07/24/2007
• Est. Priority Date: 10/06/2004
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Flodman, David Allen, Manning, Robert Francis, Demarche, Thomas Edward
• Primary Examiner(s): NGUYEN, HOANG M
• Application Number:
  US10/959,615
• Publication Number:
  US 20060073017A1
• Time in Patent Office: 1,021 Days
• Field of Search: 416/96.R, 416/96.A, 416/97.R, 416/97.A, 415/115, 415/116
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall thereof for increasing divergence of the slots to diffuse coolant discharged therethrough.

Claims

1. A turbine airfoil comprising:

opposite pressure and suction sidewalls extending longitudinally in span and axially in chord between opposite leading and trailing edges, and having an internal cooling circuit therein for circulating a coolant therethrough;

said pressure sidewall including a row of diverging outlet slots joined to said cooling circuit, and separated by corresponding converging partitions having opposite sidewalls defining sides of said slots;

each of said slots including in series a converging inlet, a throat of minimum flow area, and a diverging outlet exposed in said pressure sidewall, and separated from an adjacent outlet by an exposed converging land at the aft end of an intervening partition; and

each of said partitions includes a step in said partition sidewall for abruptly decreasing width of said partition and locally increasing divergence of said slots to diffuse said coolant discharged therethrough.

2. An airfoil according to claim 1 wherein each of said partitions converges aft from said slot throat to said step, and further converges aft from said step along said outlet.

3. An airfoil according to claim 2 wherein each of said outlets 44 breaches the external surface of said pressure sidewall at a breakout lip spaced forward from said trailing edge, and is bounded by said exposed lands at the aft ends of said partitions, with forward ends thereof extending forward from said lips.

4. An airfoil according to claim 3 wherein said partition lands converge aft from said lips, and are coplanar with the external surface of said pressure sidewall around said slot outlets.

5. An airfoil according to claim 4 wherein each of said partitions includes a corresponding step on opposite sides thereof for increasing flow area of said adjacent slots on corresponding opposite sides thereof.

6. An airfoil according to claim 5 wherein each of said slots decreases in flow area from said inlet to said throat thereof, and then increases in flow area from said throat to said step in said partition, and then further increases in flow area from said step to said outlet thereof.

7. An airfoil according to claim 6 wherein said steps are aligned coplanar with said breakout lips.

8. An airfoil according to claim 7 wherein said slots have a shallow divergence angle up to about 7.5 degrees between said partitions for diffusing said coolant discharged therethrough, and said divergence angles are substantially equal forward and aft of said steps.

9. An airfoil according to claim 7 wherein said steps are disposed in said partitions only, and the internal surface of said suction sidewall along said slots is smooth.

10. An airfoil according to claim 7 wherein each of said slots includes a single step in each of said partitions, and said partitions have flat and parallel sidewalls forward and aft of said steps.

11. A turbine airfoil comprising:

opposite pressure and suction sidewalls extending longitudinally in span and axially in chord between opposite leading and trailing edges;

said sidewalls being spaced apart between said leading and trailing edges to define an internal cooling circuit therein for circulating a coolant therethrough;

said pressure sidewall including a row of outlet slots extending therethrough along said trailing edge in flow communication with said cooling circuit for discharging said coolant therefrom;

said slots being separated from each other by corresponding partitions having opposite sidewalls defining sides of said slots, and each slot includes an inlet at a forward end of said partitions, a throat following said inlet, and an outlet along an aft end of said partitions; and

each of said slots diverges aft and includes a step in said partition sidewall increasing divergence for diffusing said coolant discharged therethrough.

12. An airfoil according to claim 11 wherein each of said partitions converges aft from said slot throat to said step, and further converges aft from said step along said outlet.

13. An airfoil according to claim 12 wherein each of said outlets breaches the external surface of said pressure sidewall at a breakout lip spaced forward from said trailing edge, and is bounded by exposed lands at the aft ends of said partitions, with forward ends thereof extending forward from said lips.

14. An airfoil according to claim 13 wherein said partition lands converge aft from said lips, and are coplanar with the external surface of said pressure sidewall around said slot outlets.

15. An airfoil according to claim 14 wherein said slots have a shallow divergence angle between said partitions for diffusing said coolant discharged therethrough, and said divergence angles are substantially equal forward and aft of said steps.

16. An airfoil according to claim 14 wherein said partitions have a shallow convergence angle being substantially equal forward and aft of said steps.

17. An airfoil according to claim 11 wherein each of said partitions includes a corresponding step on opposite sides thereof for abruptly decreasing width of said partition and increasing flow area of said adjacent slots on corresponding opposite sides thereof.

18. An airfoil according to claim 14 wherein each of said slots decreases in flow area from said inlet to said throat thereof, and then increases in flow area from said throat to said step in said partition, and then further increase in flow area from said step to said outlet thereof.

19. An airfoil according to claim 14 wherein said steps are aligned coplanar with said breakout lips.

20. An airfoil according to claim 14 wherein said steps are disposed in said partitions only, and the internal surface of said suction sidewall along said slots is smooth.

21. An airfoil according to claim 14 wherein said steps, are disposed both in said partitions and in the internal surface of said suction sidewall along said slots.

22. An airfoil according to claim 14 wherein each of said slots includes a single step in each of said partitions, and said partitions have flat and parallel sidewalls forward and aft of said steps.

23. An airfoil according to claim 14 wherein each of said slots includes a pair of said steps in series in each of said partitions.