DIVERGENT TURBINE NOZZLE

• US 20090155050A1
• Filed: 12/17/2007
• Published: 06/18/2009
• Est. Priority Date: 12/17/2007
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Silva Correia, Victor Hugo, Tung, Stephen Kin-Keung, Manning, Robert Francis, Broomer, Mark, Reddy, Bhanu Mahasamudram
• Granted Patent: US 8,281,604 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2250/324 divergent
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.

Claims

1. A gas turbine engine comprising:

an annular combustor configured for discharging combustion gases;

a turbine nozzle following said combustor and including a row of nozzle vanes extending radially between laterally surrounding inner and outer bands;

a row of turbine rotor blades following said nozzle for extracting energy from said combustion gases;

each of said nozzle vanes including circumferentially opposite pressure and suction sidewalls extending radially in span between said bands and extending axially in chord between opposite leading and trailing edges; and

each vane further including inner and outer patterns of corresponding inner and outer cooling holes distributed along said leading edge and inclined oppositely inwardly toward said inner band and outwardly toward said outer band, respectively.

2. An engine according to claim 1 wherein said inner and outer patterns include multiple radial columns of said inner and outer holes spaced laterally apart along both said pressure and suction sidewalls parallel to said leading edge.

3. An engine according to claim 2 further comprising a plurality of transition holes distributed along said leading edge of said vanes near the midspan thereof to radially adjoin said inner pattern of inner holes with said outer pattern of outer holes.

4. An engine according to claim 3 wherein said inner holes have an acute first inclination angle radially inwardly toward said inner band, and said outer holes have an opposite acute second inclination angle diverging radially outwardly toward said outer band.

5. An engine according to claim 4 wherein said inner and outer patterns include common radial columns of said inner and outer holes.

6. An engine according to claim 4 wherein said transition holes are arranged in a lateral row bridging said pressure and suction sidewalls around said leading edge.

7. An engine according to claim 4 wherein said inner holes vary in said first inclination angle from said outer pattern to said inner band, and said outer holes vary in said second inclination angle from said inner pattern to said outer band.

8. An engine according to claim 4 wherein said transition holes are substantially perpendicular to said sidewalls.

9. An engine according to claim 4 wherein said inner holes, outer holes, and transition holes have substantially equal flow diameters, and are disposed laterally perpendicular to said sidewalls.

10. An engine according to claim 4 wherein:

said combustor is configured to effect a radial parabolic first temperature profile in said combustion gases discharged to said nozzle; and

each of said nozzle vanes includes an internal cooling circuit for discharging a coolant through said diverging inner and outer holes to dilute said combustion gases to effect a different radially parabolic second temperature profile through said downstream rotor blades.

11. A gas turbine nozzle comprising:

a row of hollow nozzle vanes extending radially in span between laterally surrounding inner and outer bands;

each vane including circumferentially opposite pressure and suction sidewalls extending radially between said bands and extending axially in chord between leading and trailing edges; and

each vane further including an inner pattern of inner cooling holes distributed along said leading edge and inclined inwardly toward said inner band, and a diverging outer pattern of outer cooling holes distributed along said leading edge and inclined outwardly toward said outer band.

12. A nozzle according to claim 11 wherein said inner holes have an acute first inclination angle radially inwardly toward said inner band, and said outer holes have an opposite acute second inclination angle diverging radially outwardly toward said outer band.

13. A nozzle according to claim 12 wherein said inner holes vary in said first inclination angle from said outer pattern to said inner band, and said outer holes vary in said second inclination angle from said inner pattern to said outer band.

14. A nozzle according to claim 12 wherein both said inner and outer patterns of inner and outer holes laterally bridge said pressure and suction sidewalls along said leading edge.

15. A nozzle according to claim 14 wherein said inner and outer holes are distributed in radial columns parallel to said leading edge.

16. A nozzle according to claim 14 wherein said inner and outer patterns include common radial columns of said inner and outer holes.

17. A nozzle according to claim 14 wherein said inner and outer patterns include multiple radial columns of said inner and outer holes spaced laterally apart along both said pressure and suction sidewalls around said leading edge.

18. A nozzle according to claim 14 further comprising a plurality of transition holes distributed along said leading edge of said vanes near the midspan thereof to radially adjoin said inner pattern of inner holes with said outer pattern of outer holes.

19. A nozzle according to claim 18 wherein said transition holes are arranged in a lateral row bridging said pressure and suction sidewalls around said leading edge.

20. A nozzle according to claim 19 wherein said transition holes are substantially perpendicular to said sidewalls.

21. A nozzle according to claim 18 wherein said inner holes, outer holes, and transition holes have substantially equal flow diameters, and are disposed laterally perpendicular to said sidewalls.

22. A nozzle according to claim 14 wherein each of said vanes includes an internal cooling circuit for discharging a coolant through said diverging inner and outer holes.

23. A nozzle according to claim 14 in combination with downstream turbine stages and an upstream combustor for discharging combustion gases with a radially parabolic first temperature profile through said nozzle, and said inner and outer holes are sized to dilute said combustion gases to effect a different radially parabolic second temperature profile in said downstream turbine stages.