Turbine blade with near-wall multi-metering and diffusion cooling circuit

• US 7,625,180 B1
• Filed: 11/16/2006
• Issued: 12/01/2009
• Est. Priority Date: 11/16/2006
• Status: Expired due to Fees

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Liang, George
• Primary Examiner(s): Nguyen; Ninh H
• Application Number:
  US11/600,447
• Time in Patent Office: 1,111 Days
• Field of Search: 416/97.R, 416/96.R, 416/96.A, 415/115, 298/892
• 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: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y10T 29/4932 Turbomachine making

Abstract

A turbine airfoil with a near wall cooling design that reduces the airfoil main body metal temperature and reduces the cooling flow requirement for increased turbine efficiency. The airfoil includes a main body portion with internal cooling air supply cavities separated by one or more ribs, and a plurality of impingement cells formed on the outer surface on the pressure side and suction side of the airfoil main body. The impingement cells with film cooling holes are formed by placing a filler material within the cells and partially formed film cooling holes extending from the side wall of the cell. A thin outer airfoil wall is formed over the main body with the filler material filled cells. The filler material is leached out from the airfoil, leaving the impingement cells with the film cooling hole extending out from the side and covered by the thin outer airfoil wall. The airfoil is thus formed with a thin outer wall and the film cooling holes are formed within the outer wall without machining. The film cooling holes can be formed as straight holes, diffusion holes, or metering and diffusions holes. Also, the metering and diffusion hole connecting the cooling supply cavity to the impingement cell can be varied throughout the airfoil to regulate the pressure and cooling flow over the airfoil to control the metal temperature thereof.

Claims

1. A turbine airfoil comprising:

an airfoil main structure having the general shape of the airfoil and forming a leading edge and a trailing edge, and a pressure side and a suction side of the airfoil structure, the airfoil main structure forming a cooling air supply cavity;

a plurality of impingement cells formed on the airfoil main structure on the pressure side and the suction side;

an impingement hole connecting the cooling air supply cavity to the impingement cell;

a film cooling hole connecting the impingement cell to an outer surface of the airfoil;

a thin outer wall secured over the airfoil main structure, the thin outer wall enclosing the impingement cell and forming part of the film cooling hole; and

,

the rows of impingement cells are staggered in which an impingement cell in a first row is positioned between adjacent impingement cells in an adjacent second row.

2. The turbine airfoil of claim 1, and further comprising:

a rib extending from the pressure side to the suction side of the airfoil main structure, the rib separating a first cooling air supply cavity from a second cooling air supply cavity.

3. The turbine airfoil of claim 2, and further comprising:

a plurality of the impingement cells formed along the pressure side and the suction side of the airfoil main structure, each impingement cell being connected to one of the two cooling air supply cavities through an impingement hole.

4. The turbine airfoil of claim 3, and further comprising:

the plurality of impingement cells are substantially rectangular in shape and arranged along rows in the airfoil span-wise direction.

5. The turbine airfoil of claim 2, and further comprising:

A second rib separating the second cooling air supply cavity from a third cooling supply cavity;

A plurality of impingement cells formed on the airfoil main structure on the pressure side and the suction side and connected to the third cooling air supply cavity through impingement holes; and

,

A plurality of cooling air exit holes in the trailing edge region of the airfoil and in fluid communication with the third cooling air supply cavity.

6. The turbine airfoil of claim 1, and further comprising:

the film cooling hole is a diffuser slot.

7. The turbine airfoil of claim 1, and further comprising:

the film cooling hole is a metering hole and a diffuser hole with the diffuser located downstream from the metering portion.

8. The turbine airfoil of claim 1, and further comprising:

cooling air turbulator means are formed on the outer wall surface within the impingement cell.

9. The turbine airfoil of claim 1, and further comprising:

the plurality of impingement cells each have a span-wise length of about one inch and a chord-wise length of about one half an inch.

10. The turbine airfoil of claim 9, and further comprising:

the plurality of impingement cells each have a depth of from about 0.05 inches to about 0.2 inches.

11. The turbine airfoil of claim 1, and further comprising:

the impingement hole is a metering and impingement hole.

12. The turbine airfoil of claim 11, and further comprising:

cooling air turbulator means are formed on the outer wall surface within the impingement cell.

13. The turbine airfoil of claim 1, and further comprising:

the plurality of impingement cells each have a span-wise length of about one inch and a chord-wise length of about one half an inch.

14. The turbine airfoil of claim 13, and further comprising:

the plurality of impingement cells each have a depth of from about 0.05 inches to about 0.2 inches.

15. The turbine airfoil of claim 14, and further comprising:

the impingement hole is a metering and impingement hole.

22. The turbine airfoil of claim 6, and further comprising:

each of the impingement cavities includes a diffuser slot with a width about as wide as the impingement cavity.

23. The turbine airfoil of claim 6, and further comprising:

the diffusion slots in the second row are wide enough to cover gaps formed between the diffusion slots in the first row.

16. A process of forming a turbine airfoil having an internal cooling air supply cavity and a plurality of film cooling holes, the process comprising the steps of:

forming an airfoil main structure with a plurality of impingement cells on the pressure side and the suction side of the airfoil;

forming part of a film cooling hole on the airfoil main structure and leading from the impingement cell;

drilling an impingement hole into the impingement cell connected to the cooling air supply cavity;

placing a filler material in the impingement cell and the partial film cooling hole having the form of the impingement cell and the film cooling hole;

forming a thin outer airfoil wall over the airfoil main structure and the impingement cell; and

,

leaching out the filler material to form an open space forming the impingement cell and the film cooling hole leading out from the impingement cell.

17. The process of forming a turbine airfoil of claim 16, and further comprising the step of:

providing the filler material with turbulator forming means on the surface forming the thin airfoil wall such that when the filler material is leached away the inner surface of the airfoil wall includes turbulator means thereon.

18. The process of forming a turbine airfoil of claim 16, and further comprising the step of:

staggering the rows of impingement cells.

19. The process of forming a turbine airfoil of claim 16, and further comprising the step of:

forming the filler material in the film cooling hole forming portion with a diffuser forming shape.

20. The process of forming a turbine airfoil of claim 16, and further comprising the step of:

the impingement cell and the film cooling hole is formed in the airfoil by forming the outer airfoil wall over the cell and the partially formed film cooling hole and leaching out the filler material, leaving the complete impingement cell and film cooling hole opening into the impingement cell.

21. The process of forming a turbine airfoil of claim 16, and further comprising the step of:

varying the size of the impingement holes in the plurality of impingement cells to regulate the metal temperature to eliminate hot spots on the airfoil outer wall.