EFFUSION COOLED DUAL WALL GAS TURBINE COMBUSTORS

• US 20110023495A1
• Filed: 07/30/2009
• Published: 02/03/2011
• Est. Priority Date: 07/30/2009
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Rudrapatna, Nagaraja, Zupanc, Frank Joseph, Bronson, Thomas J., Yankowich, Paul
• Granted Patent: US 9,897,320 B2
• Time in Patent Office: Days
• US Class Current: 60/752
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70° and about 90° and a second row disposed at a tangential angle of between about 0° and about 20°.

Claims

1. A gas turbine engine combustor, comprising:

an inner liner having an upstream end and a downstream end, the inner liner extending in an axial direction between the upstream and downstream ends;

a dual wall outer liner having a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end, the outer liner extending in the axial direction between the upstream and downstream ends, the outer liner being spaced apart from, and at least partially surrounding, the inner liner;

a dome assembly coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner; and

a plurality of rows of effusion cooling holes disposed in the hot wall, including a first row of effusion cooling holes disposed at a tangential angle of between about 70° and

about 90°

relative to the axial direction and a second row of effusion cooling holes disposed at a tangential angle of between about 0° and

about 20°

relative to the axial direction.

2. The gas turbine engine combustor of claim 1, wherein the second row of effusion cooling holes is downstream of the first row of the effusion cooling holes.

3. The gas turbine engine combustor of claim 2, wherein the plurality of effusion cooling holes further includes a third row of effusion cooling holes axially between the first and second rows and disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the first row of effusion cooling holes and greater than the tangential angle of the second row of effusion cooling holes.

4. The gas turbine engine combustor of claim 1, further comprising at least one row of dilution openings extending through the hot wall, the dilution opening being generally aligned in a circumferential direction with the second row of the effusion cooling holes.

5. The gas turbine engine combustor of claim 4, wherein the first row of effusion cooling holes is generally at the upstream end of the hot wall, and the plurality of rows of effusion cooling holes further comprises a third row of effusion cooling holes generally immediately downstream of the at least one row of dilution openings, the third row of effusion cooling holes disposed at a tangential angle of between about 70°

and about 90°

relative to the axial direction.

6. The gas turbine engine combustor of claim 1, wherein the first and second rows of effusion cooling holes form a first set of effusion cooling holes, and the plurality of rows of effusion cooling holes includes a second set of effusion cooling holes downstream of the first set of effusion cooling holes, the second set of effusion cooling holes including a third row of effusion cooling holes disposed at a tangential angle of between about 70°

and about 90°

relative to the axial direction and a fourth row of effusion cooling holes disposed at a tangential angle of between about 0° and

about 20°

relative to the axial direction.

7. The gas turbine engine combustor of claim 6, further comprising one or more rows of dilution openings extending through the hot wall immediately upstream of the second set of effusion cooling holes.

8. The gas turbine engine combustor of claim 7, wherein the one or more rows of dilution openings includes a row of primary dilution openings and a row of secondary dilution openings disposed downstream the primary dilution openings.

9. The gas turbine engine combustor of claim 1, wherein each effusion cooling hole in the first and second rows of effusion cooling holes has a diameter between about 0.01 inches and 0.03 inches.

10. The gas turbine engine combustor of claim 1, wherein each effusion cooling hole in the first and second rows of effusion cooling holes extends through the hot wall at an acute angle.

11. The gas turbine engine combustor of claim 1, further comprising a plurality of impingement openings in the cold wall of the outer liner.

12. The gas turbine engine combustor of claim 11, wherein the impingement openings extend through the cold wall at an angle of approximately 90°

.

13. The gas turbine engine combustor of claim 1, wherein the hot wall of the outer liner is a first hot wall and the cold wall of the outer liner is a first cold wall, and

wherein the inner liner is a dual wall liner with a second hot wall and a second cold wall, and

wherein the plurality of rows of effusion cooling holes include a third row of effusion cooling holes disposed in the second hot wall and a fourth row of effusion cooling holes disposed in the second hot wall downstream of the third row of effusion cooling holes, the third row of effusion cooling holes disposed at a tangential angle of between about 70°

and about 90°

relative to the axial direction and the fourth row of effusion cooling holes disposed at a tangential angle of between about 0° and

about 20°

relative to the axial direction.

14. A combustor liner segment, comprising:

a hot side;

a cold side opposing the hot side and having an upstream end and a downstream end, the cold side extending in an axial direction between the upstream and downstream ends; and

a plurality of effusion cooling holes extending from the cold side to the hot side, including a first row of effusion cooling holes disposed at a tangential angle of between about 70° and

about 90°

relative to the axial direction and a second row of effusion cooling holes disposed at a tangential angle of between about 0° and

about 20°

relative to the axial direction.

15. The combustor liner segment of claim 14, wherein the cold side has first and second raised edges extending in an axial direction between the upstream and downstream ends.

16. The combustor liner segment of claim 15, further comprising a third row of effusion cooling holes adjacent to the first rail and extending in an axial direction.

17. The combustor liner segment of claim 16, wherein the third row of effusion cooling holes are disposed at a tangential angle of between about 70°

and about 90°

relative to the axial direction

18. The combustor liner segment of claim 14, wherein the plurality of effusion cooling holes further include a third row of effusion cooling holes disposed at a tangential angle, relative to the axial direction, that is less than the tangential angle of the first row effusion cooling holes and greater than the tangential angle of the second row of effusion cooling holes.

19. The combustor liner segment of claim 14, further comprising at least one row of dilution openings extending between the hot and cold sides, the dilution opening being generally aligned in a circumferential direction with the second row of the effusion cooling holes.

20. A combustor liner segment, comprising:

a hot side;

a cold side opposing the hot side and having an upstream end and a downstream end, the cold side extending in an axial direction between the upstream and downstream ends, the cold wall having at least one raised edge extending in an axial direction between the upstream and downstream ends; and

a plurality of effusion cooling holes extending from the cold side to the hot side, including

a first row of effusion cooling holes extending in a circumferential direction and disposed at a tangential angle of between about 70° and

about 90°

relative to the axial direction,

a second row of effusion cooling holes extending in a circumferential direction, downstream of the first row, and disposed at a tangential angle of between about 0° and

about 20°

relative to the axial direction,

a third row of effusion cooling holes extending in a circumferential direction, downstream of the second row, and disposed at a tangential angle of between about 70° and

about 90°

relative to the axial direction,

a fourth row of effusion cooling holes extending in a circumferential direction, downstream of the third row, and disposed at a tangential angle of between about 0° and

about 20°

relative to the axial direction, and

a fifth row of effusion cooling holes adjacent to the at least one raised edge and extending in an axial direction; and

at least one row of dilution openings extending through the hot side, the at least one row of dilution openings being generally aligned in a circumferential direction with the second row of the effusion cooling holes.