TURBINE BLADE HAVING IMPROVED FLUTTER CAPABILITY AND INCREASED TURBINE STAGE OUTPUT

• US 20130202445A1
• Filed: 02/06/2012
• Published: 08/08/2013
• Est. Priority Date: 02/06/2012
• Status: Active Grant

• Current Assignee: H2 IP UK Limited
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: RAMIREZ, RICHARD, HART, ADAM LEE, FREDMONSKI, ADAM JOHN, DIETRICH, DOUGLAS JAMES, ABDEL-WAHAB, SAMER, FIEBIGER, STEPHEN WAYNE, HSIA, KUO-TING, DAY, W. DAVID
• Granted Patent: US 8,821,125 B2
• Time in Patent Office: Days
• US Class Current: 416/241.R
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• 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 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: F05D 2300/175 Superalloys

Abstract

A turbine blade, airfoil configuration, and rotor stage are disclosed in which through the airfoil profile disclosed in Table 1, a modification in airfoil flutter and swirl are achieved. Through the airfoil configuration, the swirl and improved platform sealing configuration, result in the turbine blades having the airfoil profile with an increased performance output from the turbine.

Claims

1. A turbine blade having an attachment, a neck extending radially outward from the attachment, a platform extending radially outward from the neck, an airfoil extending radially outward from the platform, and a shroud extending radially outward from the airfoil, where the airfoil has 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 the platform.

2. The turbine blade of claim 1, wherein the airfoil has manufacturing tolerances of about ±

0.030 inches.

3. The turbine blade of claim 1, wherein a recessed region extends along a portion of an axial length of the platform.

4. The turbine blade of claim 3 further comprising a seal positioned within the recessed region.

5. The turbine blade of claim 1, wherein the blade is fabricated from a nickel-based alloy.

6. The turbine blade of claim 1 further comprising a MCrAlY bond coating applied to the airfoil.

7. The turbine blade of claim 6, wherein the coating is applied up to approximately 0.0055″

thick to the airfoil.

8. An airfoil for a turbine blade 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 the airfoil has manufacturing tolerances of about ±

0.030 inches.

10. The airfoil of claim 9 further comprising a coating up to 0.0055 inches thick.

11. The airfoil of claim 10, wherein the coating is a MCrAlY bond coating.

12. A plurality of turbine blades secured to a rotor disk to form a rotor stage, the turbine blades each having an airfoil having an uncoated profile substantially in accordance with Cartesian Coordinates values of X, Y, and Z as set forth in Table 1, wherein the profiles have a reduced swirl exiting from the rotor stage.

13. The plurality of turbine blades of claim 12, wherein adjacent turbine blades form a throat area of approximately 3,625 square inches.

14. The plurality of turbine blades of claim 12 further comprising a plurality of seal positioned between adjacent turbine blades.

15. The plurality of turbine blades of claim 14, wherein the seal are placed in a plurality of recessed regions that extends along a majority of a length of the platform of each turbine blade.

16. The plurality of turbine blades of claim 12, wherein the airfoil has manufacturing tolerances of about ±

0.030 inches.

17. The plurality of turbine blades of claim 12 further comprising a MCrAlY bond coating applied to the airfoil.

18. The plurality of turbine blades of claim 17, wherein the bond coating is approximately 0.0055 inches thick.