Cooled blade for a gas turbine, method for producing such a blade, and gas turbine having such a blade

• US 8,444,375 B2
• Filed: 04/27/2011
• Issued: 05/21/2013
• Est. Priority Date: 10/27/2008
• Status: Expired due to Fees

• Current Assignee: Ansaldo Energia IP UK Limited (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Naik, Shailendra, Pathak, Gaurav
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US13/095,427
• Publication Number:
  US 20110243755A1
• Time in Patent Office: 755 Days
• Field of Search: 415/115, 416/90.R, 416/92, 416/96.R, 416/96.A, 416/97.R, 416/193.A, 298/897.21, 219/69.17, 219/121.71
• US Class Current: 415/115
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2250/292 tapered
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
• CPC Class Codes: Y10T 29/49341 with cooling passage

Abstract

A blade for a gas turbine includes an airfoil extending in radial direction of the turbine or longitudinal direction of the blade, respectively, between a platform and a blade tip. The airfoil is bordered across the airfoil by a leading edge and a trailing edge and has a suction side and a pressure side. At the trailing edge a first cooling passage runs parallel to the trailing edge from the platform to the blade tip in the interior of the airfoil. The cooling passage is supplied with a cooling air flow from the platform side, and from which cooling air is discharged through a plurality of cooling holes arranged all over the blade. For such a blade the cooling is optimized by providing a first cooling passage, the passage area of which is tapered in radial direction by between 35% and 59%.

Claims

1. A blade for a gas turbine, comprising:

a platform;

a blade tip;

a leading edge;

a trailing edge; and

an airfoil extending between the platform and the blade tip, the airfoil being bounded in at least one direction, by the leading edge and the trailing edge and having a suction side and a pressure side, wherein in a region of the trailing edge and in a direction running parallel to the trailing edge from the platform up to the blade tip, in an interior of the airfoil, there is a first cooling duct for feeding a coolant flow from the platform and from which coolant is guided to an outside of the airfoil via a multiplicity of holes arranged distributed on the blade, wherein a flow cross section of the first cooling duct tapers toward the blade tip from the platform, the taper being between 35% and 59%,

wherein the holes arranged distributed on the blade are elongated cooling bores produced with low geometric tolerance by at least one of Electro-Discharge Machining and laser drilling;

the elongated cooling bores including

first cooling bores arranged distributed along the trailing edge; and

second cooling bores arranged distributed on the blade tip,

wherein the first and second cooling bores open into an exterior on the pressure side of the blade or have been introduced into the blade from the pressure side,

wherein the first cooling bores have a cylindrical shape, a ratio of a length to a diameter of the first cooling bores is between 20 and 35, a spacing of neighboring first cooling bores in a radial direction is 2 to 5 times their diameter, the first cooling bores enclose with a horizontal an angle of 20°

-40°

, and an angle of the first cooling bores to a surface of the blade is between 8° and

15°

.

2. The blade as claimed in claim 1, wherein the airfoil is configured to extend in either a radial direction of a gas turbine or in a longitudinal direction of a blade when installed, and wherein the taper is approximately 42%.

3. The blade as claimed in claim 1, wherein a cross-sectional area of the first cooling duct has a height (H) in a circumferential direction of a gas turbine in which the blade is to be installed, and a width (W) in an axial direction of the gas turbine, and wherein the height/width (H/W) side ratio diminishes toward the blade tip.

4. The blade as claimed in claim 3, wherein the height/width (H/W) side ratio diminishes toward the blade tip by 5% to 14%.

5. The blade as claimed in claim 3, wherein the height/width (H/W) side ratio diminishes toward the blade tip by approximately 9%.

6. The blade as claimed in claim 1, wherein inlets of the first cooling bores are arranged on a centerline of the first cooling duct.

7. The blade as claimed in claim 1, wherein at a transition between the platform and the airfoil, the first cooling bores are aligned with a chord line of the airfoil such that the cooling air is ejected centrally through these cooling bores at an intersection point between the chord line and a profile of the trailing edge.

8. The blade as claimed in claim 1, wherein the first cooling bores merge uniformly at the blade tip into the second cooling bores, the second cooling bores have a cylindrical shape, a ratio of length to diameter of the second cooling bores is between 4 and 15, a spacing of neighboring second cooling bores is 4 to 6 times their diameter, and an angle of the second cooling bores to a surface of the blade is between 25°

and 35°

.

9. The blade as claimed in claim 1, wherein third and fourth cooling bores run through the platform, and the third cooling bores open into an exterior on the suction side of the blade, and the fourth cooling bores open into the exterior on the pressure side of the blade.

10. The blade as claimed in claim 9, wherein the fourth cooling bores have a cylindrical shape and enclose different angles with an edge of the platform, and wherein a spacing of neighboring fourth cooling bores on an outside of the platform is 5 to 8 times their diameter, and wherein a ratio of length to diameter of the fourth cooling bores is between 25 and 35.

11. The blade as claimed in claim 10, wherein a proportion of the fourth cooling bores exit from the first cooling channel on a side of the first cooling channel facing the pressure side of the blade.

12. The blade as claimed in claim 9, wherein the third cooling bores have a cylindrical shape and enclose different angles with an edge of the platform, and a spacing of neighboring third cooling bores on an outside of the platform is 6 to 8 times their diameter, and wherein a ratio of length to diameter of the third cooling bores is between 30 and 45.

13. The blade as claimed in claim 12, wherein the third cooling bores emerge from the first cooling duct on a side of the first cooling duct facing the suction side of the blade.

14. The blade as claimed in claim 9, wherein the fourth cooling bores have a cylindrical shape and enclose different angles with an edge of the platform, and wherein a spacing of neighboring fourth cooling bores on an outside of the platform is 6 times their diameter, and a ratio of length to diameter of the fourth cooling bores is between 25 and 35.

15. The blade as claimed in claim 9, wherein the third cooling bores have a cylindrical shape and enclose different angles with the edge of the platform, and a spacing of neighboring third cooling bores on the outside of the platform is approximately 6.5 times their diameter, and a ratio of length to diameter of the third cooling bores is between 30 and 45.

16. The blade as claimed in claim 1, comprising:

obliquely positioned ribs arranged in the first cooling duct in order to at least one of generate and reinforce a turbulent cooling air flow, wherein in a region of the platform, the first cooling duct is connected via a bend to a parallel running second cooling duct; and

an outwardly guiding dust hole of relatively large diameter provided in the blade tip at the end of the first cooling duct.

17. The blade of claim 1, in combination with a gas turbine having a plurality of moving blades fitted on a rotor, and guide blades fitted in a housing surrounding the rotor, wherein the blade is used as at least one of the moving blades and the guide blades.

18. The blade as claimed in claim 1, wherein the spacing of neighboring first cooling bores in a radial direction is approximately 3.5 times their diameter, the first cooling bores enclose with the horizontal an angle of approximately 30°

, and the angle of the first cooling bores to a surface of the blade is approximately 10°

.

19. The blade as claimed in claim 1, wherein the first cooling bores merge uniformly at the blade tip into the second cooling bores, the second cooling bores have a cylindrical shape, a ratio of length to diameter of the second cooling bores is between 4 and 15, the spacing of neighboring second cooling bores is 5 times their diameter, and an angle of the second cooling bores to the surface of the blade is approximately 30°

.