TURBINE BLADE AIRFOIL HAVING IMPROVED CREEP CAPABILITY

• US 20050111978A1
• Filed: 11/21/2003
• Published: 05/26/2005
• Est. Priority Date: 11/21/2003
• Status: Active Grant

• Current Assignee: Ansaldo Energia Switzerland AG (Ansaldo Energia SPA)
• Original Assignee: Power Systems Mfg. LLC (Hanwha Corporation)
• Inventors: Barrett, Michael, Strohl, J. Page, Parker, David G.
• Granted Patent: US 6,932,577 B2
• Time in Patent Office: Days
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/187 Convection cooling

Abstract

A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil. The aerodynamic profile of the airfoil has been reconfigured to reduce airfoil stress for a given operating temperature, thereby resulting in increased creep rupture life of the airfoil.

Claims

1. A turbine blade having an attachment, a platform extending generally radially outward from said attachment, an airfoil extending generally radially outward from said platform, and a shroud extending generally radially outward from said airfoil, said airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to three decimal places, wherein Z is a distance measured radially from said platform.

2. The turbine blade of claim 1 wherein said airfoil has an envelope within +/−

0.100 inches of the profile generated by said Cartesian coordinate values of X, Y, and Z as set forth in Table 1.

3. The turbine blade of claim 1 further comprising a plurality of generally radially extending holes, said holes extending from said attachment, through said platform, said airfoil, and said shroud.

4. The turbine blade of claim 3 wherein said plurality of radially extending holes pass a cooling medium through said blade to cool said airfoil.

5. The turbine blade of claim 4 wherein said cooling medium is air or steam.

6. The turbine blade of claim 5 wherein said plurality of holes comprises six holes.

7. The turbine blade of claim 1 wherein said Cartesian coordinate values of X, Y, and Z as set forth in Table 1 are scaled as a function of the same constant to create a scaled-up or scaled down airfoil.

8. An airfoil for a turbine blade having a shroud, said airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to three decimal places, wherein Z is a distance measured radially from a platform.

9. The airfoil of claim 8 wherein said airfoil has an envelope within +/−

0.100 inches of the profile generated by said Cartesian coordinate values of X, Y, and Z as set forth in Table 1.

10. The airfoil of claim 8 wherein said Cartesian coordinate values of X, Y, and Z as set forth in Table 1 are scaled as a function of the same constant to create a scaled-up or scaled down airfoil.