Light weight and highly cooled turbine blade

• US 8,057,183 B1
• Filed: 12/16/2008
• Issued: 11/15/2011
• Est. Priority Date: 12/16/2008
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Liang, George
• Primary Examiner(s): Zarneke; David
• Application Number:
  US12/335,569
• Time in Patent Office: 1,064 Days
• Field of Search: 416/97.R, 416/96.A
• US Class Current: 416/97.R
• 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
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface

Abstract

A turbine rotor blade formed from a main support spar and having a thin thermal skin bonded or formed to the support spar to form the outer airfoil surface of the blade. The main support spar is formed from a plurality of ribs arranged to form a cooling air supply cavity near the leading edge region, a plurality of impingement chambers and a plurality of spent air collector chambers arranged along the pressure side and suction side of the airfoil to form a series of impingement chambers and collector chambers to provide near wall cooling for the thermal skin. A row of exit cooling holes located along the trailing edge discharges the cooling air from the last collector chamber. In another embodiment, some of the collector chambers are connected to rows of film cooling air to discharge film cooling onto the outer airfoil surface. The thermal skin includes micro pin fins on the inner wall to enhance the cooling effect of the impinging cooling air. The entire blade comprises a spar support structure, a thin thermal skin, external coating formed using a metal molecular depositing process to build up the blade as a single piece but with multiple material.

Claims

1. A turbine rotor blade comprising:

a main support spar forming a support structure for the blade;

the blade having an airfoil extending from a platform and an attachment section;

the main support spar formed from a plurality of ribs that define a cooling air supply cavity in a leading edge region of the airfoil, a plurality of impingement chambers spaced along the pressure side and the suction side of the airfoil, and a plurality of spent cooling air chambers spaced along the pressure side and the suction side of the airfoil; and

,

the plurality of impingement chambers and spent cooling air chambers are arranged together in series such that cooling air flowing into an impingement chamber then flows into a collector chamber and then into another impingement chamber.

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

a leading edge impingement chamber located at a leading edge of the airfoil; and

,

a metering and impingement hole connecting the leading edge impingement chamber to the cooling air supply chamber.

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

a first metering and impingement hole connecting the leading edge impingement chamber to the series of impingement chambers and collector chamber positioned along the suction side of the airfoil; and

,

a second metering and impingement hole connecting the leading edge impingement chamber to the series of impingement chambers and collector chamber positioned along the pressure side of the airfoil.

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

the collector chambers located aft of the cooling air supply cavity extend from the pressure side wall to the suction side wall to form a series of collector chambers extending from the cooling air supply cavity to a trailing edge region of the airfoil.

5. The turbine rotor blade of claim 4, and further comprising:

a row of exit cooling holes in the trailing edge of the airfoil connected to the collector chamber located adjacent to the trailing edge region of the airfoil.

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

a thin thermal skin bonded to the main support spar to form an outer airfoil surface of the rotor blade.

7. The turbine rotor blade of claim 6, and further comprising:

the thin thermal skin includes a plurality of micro pin fins on the backside wall.

8. The turbine rotor blade of claim 7, and further comprising:

the thermal skin has a thickness of 0.010 inches to 0.030 inches; and

,

the micro pin fins have a diameter to height ratio about equal to the thickness of the thermal skin.

9. The turbine rotor blade of claim 6, and further comprising:

the thermal skin has a thickness of 0.010 inches to 0.030 inches.

10. The turbine rotor blade of claim 8, and further comprising:

the micro pin fins have a density of from 50% to 75%.

11. The turbine rotor blade of claim 6, and further comprising:

a TBC applied to the thermal skin.

12. The turbine rotor blade of claim 1, and further comprising:

the main support spar is formed as a single piece by a metal depositing process.

13. The turbine rotor blade of claim 2, and further comprising:

the series of impingement chambers and collector chambers form a closed cooling air path from the leading edge impingement chamber to the collector chamber positioned adjacent to the trailing edge region of the airfoil.

14. The turbine rotor blade of claim 2, and further comprising:

the series of impingement chambers and collector chambers form a cooling air path from the leading edge impingement chamber to the collector chamber positioned adjacent to the trailing edge region of the airfoil; and

,

a first row of film cooling holes opening onto the suction side wall of the airfoil and connected to one of the collector chambers; and

,

a second row of film cooling holes opening onto the pressure side wall of the airfoil and connected to another one of the collector chambers.

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

a third row of film cooling holes opening onto the suction side wall of the airfoil and connected to the same collector chamber as the second row of film cooling holes.

16. The turbine rotor blade of claim 2, and further comprising:

the ribs include metering and impingement holes to discharge cooling air into the impingement chambers and spent air holes to discharge cooling air from the impingement chambers into the collector chambers.

17. The turbine rotor blade of claim 1, and further comprising:

the impingement chambers and the collector chambers extend along the entire airfoil surface in the spanwise direction of the rotor blade.

18. The turbine rotor blade of claim 6, and further comprising:

the thin thermal skin is formed with the spar as a single piece.

19. The turbine rotor blade of claim 18, and further comprising:

the thin thermal skin is formed from a different material than the spar.

20. The turbine rotor blade of claim 19, and further comprising:

the spar and the thin thermal skin are formed by a metal depositing process.

21. The turbine rotor blade of claim 19, and further comprising:

a TBC is formed on the thin thermal skin.

22. The turbine rotor blade of claim 21, and further comprising:

the TBC and the thin thermal skin are formed by a metal depositing process in which the metallic material gradually changes into the ceramic material of the TBC.