Gas turbine airfoil with leading edge cooling

• US 7,997,866 B2
• Filed: 08/15/2007
• Issued: 08/16/2011
• Est. Priority Date: 08/25/2006
• Status: Active Grant

• Current Assignee: General Electric Technology GmbH (GE Aerospace)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Vogel, Gregory, Naik, Shailendra
• Primary Examiner(s): Nguyen; Ninh H
• Application Number:
  US11/838,960
• Publication Number:
  US 20080095622A1
• Time in Patent Office: 1,462 Days
• Field of Search: 415/115, 416/97.R
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: Y10T 29/49341 with cooling passage

Abstract

A gas turbine airfoil (1) includes a pressure sidewall (15) and a suction sidewall (16), extending from a root to a tip and from a leading edge region to a trailing edge and having at least one cooling passage between the pressure sidewall (15) and the suction sidewall (16) for cooling air to pass through and cool the airfoil from within. One or several of the cooling passages (3) extend along the leading edge of the airfoil (1) and several film cooling holes (1,2) extend from the internal cooling passages (3) along the leading edge region to the outer surface of the leading edge region. The film cooling holes (1,2) each have a shape that is diffused in a radial outward direction of the leading edge of the airfoil (1) at least over a part of the length of the film cooling hole (1,2). Improved cooling in the leading edge region can be achieved because the cooling holes (1, 2) have a principal axis (17), and the shape is asymmetrically diffused in that it is diffused in the radial outward direction from the principal axis (17) along a forward inclination axis (20), and it is additionally diffused in a second lateral direction from the principal axis (17) along a lateral inclination axis (21).

Claims

1. A gas turbine airfoil comprising:

a pressure sidewall and a suction sidewall defining and extending from a root to a tip and from a leading edge region to a trailing edge;

at least one cooling passage between the pressure sidewall and the suction sidewall configured and arranged to permit cooling air to pass through and cool the airfoil from within;

wherein at least one of the at least one cooling passage extends along the leading edge of the airfoil;

a plurality of film cooling holes extending from the at least one cooling passage along the leading edge region to the outer surface of the leading edge region, the plurality of film cooling holes each having a shape that is diffused in a radial outward direction of the leading edge of the airfoil at least over a part of the length of the film cooling hole;

wherein the plurality of film cooling holes each comprise a principal axis and a shape that is asymmetrically diffused, said shape being diffused in the radial outward direction from the principal axis along a forward inclination axis, and additionally diffused in a second lateral direction from the principal axis along a lateral inclination axis; and

wherein the shape is diffused cylindrically in the radial outward direction along the forward inclination axis and in the second lateral direction along a lateral inclination axis.

2. An airfoil according to claim 1, wherein the shape between the two cylindrical diffusions is smoothed.

3. An airfoil according to claim 2, wherein the smoothed shape between the two cylindrical includes connected surfaces essentially tangential to both cylindrical diffusions.

4. An airfoil according to claim 1, wherein the principal axis is radially inclined by 50-70°

from the horizontal plane.

5. An airfoil according to claim 1, wherein the forward inclination axis is tilted from the principal axis towards the radial direction of the airfoil, and wherein the angle (β

) between the principal axis and the forward inclination axis is in the range of 5-20°

.

6. An airfoil according to claim 5, wherein the angle (β

) between the principal axis and the forward inclination axis is in the range of 5-15°

.

7. An airfoil according to claim 1, wherein the lateral inclination axis is tilted from the principal axis along a direction perpendicular to a stagnation line on the leading-edge, and wherein the angle (γ

) between the principal axis and the lateral inclination axis is in the range of 5-20°

.

8. An airfoil according to claim 7, wherein the angle (γ

) between the principal axis and the lateral inclination axis is in the range of 5-15°

.

9. An airfoil according to claim 1, wherein the airfoil defines a stagnation line, and wherein the plurality of cooling holes comprises a first row of cooling holes located on the pressure side of the stagnation line and a second row of cooling holes located on the suction side of the stagnation line.

10. An airfoil according to claim 9, wherein the cooling holes in the first and second rows are staggered along the radial direction.

11. An airfoil according to claim 10, wherein the holes in the first and second rows are staggered by one hole pitch from each other.

12. An airfoil according to claim 9, wherein each row of holes is located at least 3 hole diameters from the stagnation line.

13. An airfoil according to claim 12, wherein each row of holes is located 3-3.5 hole diameters from the stagnation line.

14. An airfoil according to claim 9, wherein the first and second rows are equally distanced from the stagnation line.

15. An airfoil according to claim 14, wherein the holes of each of the first and second rows are equally distanced from the stagnation line.

16. An airfoil according to claim 1, wherein each of the plurality of cooling holes comprises a cylindrical section at an entry portion facing the cooling passage.

17. An airfoil according to claim 1, wherein each of the plurality of cooling holes has a hole length-to-diameter ratio ranging from 1.5-6.

18. An airfoil according to claim 17, wherein each of the plurality of cooling holes has a hole length-to-diameter ratio ranging from 2-5.

19. An airfoil according to claim 1, wherein the ratio of the cross-section (D) in the widening portion of each of the plurality of cooling holes to the cross-section in the cylindrical section of the holes is in the range of 1.5-2.45.

20. An airfoil according to claim 19, wherein the ratio of the cross-section (D) in the widening portion of each of the plurality of cooling holes to the cross-section in the cylindrical section of the holes is in the range of 1.8-2.0.

21. An airfoil according to claim 19, wherein the lateral inclination axis is tilted from the principal axis along a direction such that, at the transition of the cylindrical and the widening portion, the axis of the cylindrical section and the axis of the inclination cross.

22. An airfoil according to claim 1, wherein the lateral inclination axis is located at or between a forward edge (A) and a backward edge (B) of the exit portion of each hole.

23. A method for producing cooling holes in an airfoil, the method comprising:

drilling a cylindrical, fully penetrating hole defining a principal axis and a cylindrical section; and

subsequently performing two cylindrical drillings along a lateral inclination axis and along a forward inclination axis from the outer side of the airfoil.

24. A method according to claim 23, further comprising:

smoothing a widening inner surface of a diffusion region of the cooling holes.