Series impingement cooled airfoil

• US 6,036,441 A
• Filed: 11/16/1998
• Issued: 03/14/2000
• Est. Priority Date: 11/16/1998
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Manning, Robert F., Acquaviva, Paul J., Demers, Daniel E.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): SHANLEY, MATTHEW
• Application Number:
  US09/192,225
• Time in Patent Office: 484 Days
• Field of Search: 415/115, 416/97 R, 416/96 R, 416/97 A, 416/96 A
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling

Abstract

A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and extending longitudinally from a root to a tip. The sidewalls are spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between the sidewalls. The second partition is common to both chambers, and both partitions include respective pluralities of first and second inlet holes sized to meter cooling air therethrough in series between the chambers.

Claims

1. A gas turbine engine airfoil comprising:

first and second sidewalls joined together at opposite leading and trailing edges, and extending from a root to a tip;

said sidewalls being spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between said sidewalls, with said second partition being in common with both said chambers, and obliquely joining said first partition; and

said first and second partitions including a plurality of first and second inlet holes, respectively, sized to meter cooling air therethrough in series impingement in said chambers.

2. A gas turbine engine airfoil comprising:

first and second sidewalls joined together at opposite leasing and trailing edges, and extending from a root to a tip;

said sidewalls being spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between said sidewalls, with said second partition being in common with both said chambers, and obliquely joining said first partition;

said first and second partitions including a plurality of first and second inlet holes, respectively, sized to meter cooling air therethrough in series impingement in said chambers; and

an inlet channel extending longitudinally along said first partition for supplying said cooling air to said first chamber through said first inlet holes.

3. An airfoil according to claim 2 wherein said first and second inlet holes extend obliquely through said partitions to discharge jets of said cooling air in impingement against opposite walls of said chambers.

4. An airfoil according to claim 3 wherein said partitions face respective inner surfaces of at least one of said sidewalls for impingement cooling thereof by said inlet holes.

5. An airfoil according to claim 4 wherein said first partition is disposed generally parallel between said sidewalls, and said first inlet holes are disposed generally perpendicular therein for impinging said cooling air against said second sidewall.

6. An airfoil according to claim 5 wherein said second partition is disposed obliquely to both said second sidewall and said first partition.

7. An airfoil according to claim 6 wherein said second chamber is disposed directly behind said leading edge, and said first chamber is disposed aft therefrom.

8. An airfoil according to claim 7 further comprising a third flow chamber adjoining said second chamber, and defined in part by a third partition extending in common therebetween, with said third partition having a plurality of third inlet holes sized to meter said cooling air from said second chamber into said third chamber.

9. An airfoil according to claim 8 wherein:

said first sidewall is a convex, suction sidewall;

said second sidewall is a concave, pressure sidewall;

said third partition extends between said first sidewall and said first and second partitions; and

said third holes extend obliquely through said third partition to discharge jets of said cooling air in impingement against said sidewall.

10. An airfoil according to claim 9 wherein:

said second sidewall is imperforate at said first chamber;

said leading edge includes a plurality of film cooling holes extending in flow communication with said second chamber for discharging cooling air therefrom; and

said first sidewall includes a plurality of film cooling holes extending in flow communication with said third chamber for discharging cooling air therefrom.

11. A method of cooling a gas turbine engine airfoil comprising:

channeling cooling air obliquely between opposite pressure and suction sidewalls thereof in series impingement therein, with corresponding pressure drops; and

discharging said air through said suction sidewall in rows of cooling air films downstream from a leading edge of said airfoil with corresponding decreasing pressure between said row for reducing difference in blowing ratio therebetween.

12. A method according to claim 11 further comprising channeling said cooling air in series between a plurality of laterally adjoining flow chambers.

13. A method according to claim 12 further comprising discharging said cooling air from two of said chambers for film cooling said airfoil downstream therefrom for reducing said blowing ratio difference therebetween.

14. A method according to claim 13 further comprising effecting said series impingement in three steps, and said film cooling in two steps following ultimate and penultimate ones of said impingement steps.

15. A gas turbine engine airfoil comprising:

first and second sidewalls joined together at opposite leading and trailing edges, and extending from a root to a tip;

said sidewalls being spaced apart from each other to define in part a pair of adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding partitions including a common partition positioning a leading edge one of said chambers directly behind said leading edge and a first-side one of said chambers disposed aft therefrom along only said first sidewall; and

each of said partitions including a row of inlet holes sized to meter cooling air therethrough in series impingement in said chambers.

16. An airfoil according to claim 15 further comprising a second-side one of said flow chambers disposed aft of said leading edge chamber along said second sidewall, and having a common partition therewith including another row of inlet holes therein sized to meter cooling air therethrough in series impingement with said other rows of inlet holes.

17. An airfoil according to claim 16 further comprising:

a row of film cooling holes disposed through said second sidewall in flow communication with said leading edge chamber; and

another row of film cooling holes disposed through said second sidewall in flow communication with said second-side chamber.

18. An airfoil according to claim 17 wherein said airfoil second sidewall is a convex suction sidewall, and said inlet holes are sized to meter air in series through said chambers to decrease pressure thereof to reduce blowing ratio difference between said rows of film cooling holes at said leading edge chamber and said second-side chamber.

19. An airfoil according to claim 18 further comprising an inlet channel adjoining both said first-side and second-side chambers, and disposed in flow communication with said inlet holes for said first-side chamber for supplying said cooling air thereto.

20. An airfoil according to claim 19 wherein said second-side chamber is isolated from said inlet channel, and is disposed solely in flow communication with said leading edge chamber for receiving said air therefrom.