Turbine blade with enhanced cooling and profile optimization

• US 5,980,209 A
• Filed: 06/27/1997
• Issued: 11/09/1999
• Est. Priority Date: 06/27/1997
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Barry, Vincent Anthony, Gregory, Brent A., Abuaf, Nesim
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US08/884,091
• Time in Patent Office: 865 Days
• Field of Search: 416/223 R, 416/223 A, 416/193 A, 416/95, 416/96 R, 416/96 A, 416/97 R, 416/241 R, 416/92, 416/DIG. 2, 416/DIG. 5, 415/115, 415/915
• US Class Current: 416/223.00A
• 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
• CPC Class Codes: Y10S 416/05 Variable camber or chord length

Abstract

A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.

Claims

1. An airfoil for a turbine blade having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform.

2. An airfoil for a turbine blade having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform, said airfoil including a camber angle as set forth in the chart of FIG. 11B with the camber angle and the radius being carried only to three decimal points.

3. An airfoil according to claim 2 wherein manufacturing tolerances for the airfoil are about ±

0.010 inches.

4. An airfoil according to claim 2 wherein said blade has a coating increasing the X and Y values of Table I by no greater than about 0.015 inches.

5. An airfoil according to claim 2 wherein manufacturing tolerances for the airfoil are no greater than ±

0.010 inches, said airfoil having a coating increasing the X and Y values of Table I by no greater than about 0.015 inches.

6. An airfoil according to claim 2 wherein manufacturing tolerances for the airfoil are about ±

0.008 inches.

7. An airfoil according to claim 2 wherein said blade has a coating increasing the X and Y values of Table I within a range of 005-0.012 inches.

8. An airfoil according to claim 2 in combination with a shank carrying said platform, said airfoil being integrally cast, a plurality of cooling passages formed through said cast airfoil and extending from root to tip portions thereof and adjacent each of pressure and suction sides of the airfoil.

9. An airfoil/shank combination according to claim 8 wherein the passages extend linearly from the root to the tip portions of the airfoil.

10. An airfoil/shank combination according to claim 9 wherein at least certain of said passages have inwardly extending projections at axial spaced positions therealong for providing turbulent flow.

11. An airfoil according to claim 2 in combination with a shank carrying said platform, said airfoil having passages formed therethrough extending from root to tip portions thereof for flowing a cooling medium, a recess formed in said tip portion of the airfoil for receiving the cooling medium carried by the passages, the airfoil having suction and pressure sides, the tip portion having an opening through the suction side of said airfoil in communication with said recess.

12. An airfoil/shank combination according to claim 11 wherein said passages extend along and adjacent each of the pressure and suction sides of the airfoils, said passages forming a pair of laterally spaced rows thereof along the pressure and suction sides and extending between leading and trailing edges of the airfoil at least at a location adjacent a thickest portion of the airfoil.

13. An airfoil/shank combination according to claim 12 wherein said rows lie between a camber of the airfoil and the suction and pressure sides, respectively.

14. An airfoil for a turbine blade having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform, said airfoil including a stagger angle as set forth in the chart of FIG. 9B with the stagger angle and radius being carried only to three decimal places.

15. An airfoil according to claim 14 in combination with a shank carrying said platform, said airfoil being integrally cast, a plurality of cooling passages formed through said cast airfoil and extending from root to tip portions thereof and adjacent each of pressure and suction sides of the airfoil.

16. An airfoil/shank combination according to claim 15 wherein the passages extend linearly from the root to the tip portions of the airfoil.

17. An airfoil/shank combination according to claim 16 wherein at least certain of said passages have inwardly extending projections at axial spaced positions therealong for providing turbulent flow.

18. An airfoil according to claim 17 in combination with a shank carrying said platform, said airfoil having passages formed therethrough extending from root to tip portions thereof for flowing a cooling medium, a recess formed in said tip portion of the airfoil for receiving the cooling medium carried by the passages, the tip portion having an opening through the suction side of said airfoil in communication with said recess.

19. An airfoil/shank combination according to claim 18 wherein said passages extend along and adjacent each of the pressure and suction sides of the airfoils, said passages forming a pair of laterally spaced rows thereof along the pressure and suction sides and extending between leading and trailing edges of the airfoil at least at a location adjacent a thickest portion of the airfoil.

20. An airfoil for a turbine blade having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform, said airfoil including a throat as set forth in the chart of FIG. 10B with the throat distance and radius being carried only to three decimal places.

21. An airfoil according to claim 20 in combination with a shank carrying said platform, said airfoil being integrally cast, a plurality of cooling passages formed through said cast airfoil and extending from root to tip portions thereof and adjacent each of pressure and suction sides of the airfoil.

22. An airfoil/shank combination according to claim 21 wherein the passages extend linearly from the root to the tip portions of the airfoil.

23. An airfoil/shank combination according to claim 22 wherein at least certain of said passages have inwardly extending projections at axial spaced positions therealong for providing turbulent flow.

24. An airfoil according to claim 23 in combination with a shank carrying said platform, said airfoil having passages formed therethrough extending from root to tip portions thereof for flowing a cooling medium, a recess formed in said tip portion of the airfoil for receiving the cooling medium carried by the passages, the tip portion having an opening through the suction side of said airfoil in communication with said recess.

25. An airfoil/shank combination according to claim 24 wherein said passages extend along and adjacent each of the pressure and suction sides of the airfoils, said passages forming a pair of laterally spaced rows thereof along the pressure and suction sides and extending between leading and trailing edges of the airfoil at least at a location adjacent a thickest portion of the airfoil.

26. A cast turbine airfoil having a camber and a plurality of cooling passages extending from a root portion to a tip portion thereof, said passages including first and second rows thereof on opposite sides of said camber and lying adjacent suction and pressure sides of said airfoil, respectively, said airfoil including a turbine blade having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform.

27. An airfoil according to claim 26 wherein said passages extend linearly between said root portion and said tip portion.

28. An airfoil according to claim 26 in combination with a shank connected to said root portion of said airfoil at one end of said shank and a dovetail at an opposite end of said shank, said shank and said dovetail having at least one cavity each in communication with one another and said passages, said cavity in said dovetail opening through a surface thereof for communication with a plenum of a wheel disk to which the dovetail is adapted for attachment.