Combustor liner with inverted turbulators

• US 7,104,067 B2
• Filed: 10/24/2002
• Issued: 09/12/2006
• Est. Priority Date: 10/24/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bunker, Ronald Scott
• Primary Examiner(s): Rodriguez, William H.
• Application Number:
  US10/065,495
• Publication Number:
  US 20040079082A1
• Time in Patent Office: 1,419 Days
• Field of Search: 60752-760, 126/99.C, 431/350, 431/185, 431/9, 431/353
• 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 annular grooves formed in an outside surface of said combustor liner, each groove having a uniform, substantially semi-circular cross-section and extending continuously about a circumference of said liner.

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

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

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

a flow sleeve surrounding said liner;

a first plurality of axially spaced, continuous circumferential grooves formed in an outside surface of said liner, angled relative to a direction of cooling air flowing between said liner and said flow sleeve; and

a second plurality of axially spaced, continuous circumferential grooves cris-crossed with said first plurality of axially spaced circumferential grooves wherein said first and second plurality of axially spaced circumferential grooves are uniformly curved in cross-section.

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

and a plurality of axially spaced annular grooves formed in an outside surface of said combustor liner, each groove extending continuously about a circumference of said liner;

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

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

4D.

7. The combustor liner of claim 5 wherein said grooves are arranged transversely to a direction of cooling air flow.

8. The combustor liner of claim 5 wherein said grooves are angled relative to a direction of cooling air flow.

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

a first plurality of axially spaced, continuous circumferential grooves formed in an outside surface of said liner, angled relative to a direction of cooling air flow; and

a second plurality of axially spaced, continuous circumferential grooves cris-crossed with said first plurality of axially spaced circumferential grooves, and wherein said first and second plurality of axially spaced circumferential grooves are uniformly smoothly curved in cross-section.