Combustor liner with inverted turbulators

• US 20040079082A1
• Filed: 10/24/2002
• Published: 04/29/2004
• Est. Priority Date: 10/24/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bunker, Ronald Scott
• Granted Patent: US 7,104,067 B2
• Time in Patent Office: Days
• US Class Current: 60/752
• CPC Class Codes: F05B 2240/122 Vortex generators, turbulators, or the like, for mixing by creating turbulence F05B2260/222
• CPC Class Codes: F05B 2260/222 by creating turbulence
• CPC Class Codes: F23M 5/00 Casings; Linings; Walls
• CPC Class Codes: F23M 5/085 using air or other gas as the cooling medium
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers

Abstract

A combustor liner for a gas turbine, the combustor liner having a substantially cylindrical shape; and a plurality of axially spaced circumferential grooves formed in an outside surface of the combustor liner.

Claims

1. A combustor liner for a gas turbine, the combustor liner having a substantially cylindrical shape;

and a plurality of axially spaced circumferential grooves formed in an outside surface of said combustor liner.

2. The combustor liner of claim 1 wherein said grooves are substantially semicircular in cross-section.

3. The combustor liner of claim 1 wherein said grooves are arranged transversely to a direction of cooling air flow.

4. The combustor liner of claim 1 wherein said grooves are semi-circular in cross-section, and have a diameter D, and wherein a depth of said grooves is equal to about 0.05 to 0.50D.

5. The combustor liner of claim 4 wherein a center-to-center distance between adjacent grooves is equal to about 1.5-4D.

6. The combustor liner of claim 1 wherein a center-to-center distance between adjacent grooves is equal to about 1.5-4D.

7. The combustor liner of claim 1 wherein said grooves are each comprised of overlapping circular concavities.

8. The combustor liner of claim 1 wherein said grooves are angled relative to a direction of cooling air.

9. The combustor liner of claim 8 including a second plurality of circumferential grooves cris-crossed with said first plurality of circumferential grooves.

10. A combustor liner for a gas turbine, the combustor liner having a substantially cylindrical shape;

and a plurality of axially spaced circumferential grooves formed in an outside surface of said combustor liner;

wherein said grooves are semi-circular in cross-section, and have a diameter D, and wherein a depth of said grooves is equal to about 0.05 to 0.50D.

11. The combustor liner of claim 10 wherein a center-to-center distance between adjacent grooves is equal to about 1.5-4D.

12. The combustor liner of claim 10 wherein said grooves are substantially semi-circular in cross-section.

13. The combustor liner of claim 12 wherein a center-to-center distance between adjacent grooves is equal to about 1.5-4D.

14. The combustor liner of claim 10 wherein said grooves are arranged transversely to a direction of cooling air flow.

15. The combustor liner of claim 10 wherein said grooves are angled relative to a direction of cooling air flow.