COMPRESSOR AIRFOIL

• US 20090290987A1
• Filed: 07/18/2008
• Published: 11/26/2009
• Est. Priority Date: 05/21/2008
• Status: Active Grant

• Current Assignee: Ansaldo Energia Switzerland AG
• Original Assignee: Alstom Limited (Alstom SA)
• Inventors: RAMIREZ, RICHARD, PARKER, DAVID, MOORE, ROBERT, STROHL, J. PAGE
• Granted Patent: US 8,057,188 B2
• Time in Patent Office: Days
• US Class Current: 416/241.00R
• 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: F05D 2220/3216 for a special compressor stage

Abstract

A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.

Claims

1. A compressor component having an attachment, a first platform extending radially outward from the attachment and an airfoil extending radially outward from the platform, the airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values of X and Y, for each distance Z in inches as set forth in Table 1, carried to three decimal places, wherein Z is a distance measured radially outward from the platform, the X and Y coordinate values being joined in smooth continuing splines to form airfoil sections and the airfoil sections joined smoothly to form the profile.

2. The compressor component of claim 1, wherein the airfoil has manufacturing tolerances of approximately +/−

0.090 inches.

3. The compressor component of claim 1, wherein a compressive bending stress is present at a root leading edge location of the airfoil.

4. The compressor component of claim 1, wherein the compressor component is a rotating blade.

5. The compressor component of claim 4, wherein the compressor component is located adjacent to inlet guide vanes of a compressor.

6. The compressor component of claim 1, further comprising a coating applied to at least a portion of the airfoil, the coating having a thickness of up to approximately 0.010 inches.

7. The compressor component of claim 1, wherein the airfoil sections can be scaled uniformly.

8. The compressor component of claim 1, further comprising a second platform located at an end of the airfoil, opposite the first platform.

9. An airfoil for a compressor blade, the 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 in inches, the X and Y coordinate values being joined in smooth continuing splines to form airfoil sections and the airfoil sections joined smoothly to form the profile.

10. The airfoil of claim 9, wherein the airfoil has manufacturing tolerances of approximately +/−

0.090 inches.

11. The airfoil of claim 9, wherein the airfoil is attached to a root of a compressor blade.

12. The airfoil of claim 9, further comprising a coating applied to at least a portion of the airfoil and having a thickness of up to approximately 0.010 inches.

13. The airfoil of claim 9, wherein the airfoil sections can be scaled uniformly.

14. A compressor comprising a compressor disk and a plurality of compressor blades extending radially outward from the compressor disk, each of the plurality of compressor blades having an airfoil with an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z, set forth in inches in Table 1, with the Z coordinate values at perpendicular distances from planes normal to a radius from a platform, wherein airfoil sections are defined at each distance Z by connecting the X and Y coordinate values with smooth continuing splines, and the airfoil sections are joined smoothly to form the airfoil profile.

15. The compressor of claim 14, wherein the plurality of compressor blades have compressive bending stress present at a root leading edge location of the airfoil.

16. The compressor of claim 14, further comprising a coating applied to at least a portion of the airfoil, the coating having a thickness of up to approximately 0.010 inches.

17. The compressor of claim 14, wherein the airfoil for the plurality of blades can be scaled uniformly.

18. The compressor of claim 14, wherein the airfoil profile is within +/−

0.090 inches in a direction normal to the airfoil.