Gas turbine combustor

• US 6,701,714 B2
• Filed: 12/05/2001
• Issued: 03/09/2004
• Est. Priority Date: 12/05/2001
• Status: Expired due to Term

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Burd, Steven W., Siskind, Kenneth S., Graves, Charles B.
• Primary Examiner(s): Yu, Justine R.
• Assistant Examiner(s): Liu, Han L
• Application Number:
  US10/010,297
• Publication Number:
  US 20030101731A1
• Time in Patent Office: 825 Days
• Field of Search: 607/52, 607/60, 607/66, 607/72, 607/40, 607/53, 607/54, 607/55, 607/56, 607/57, 607/58, 607/59, 607/96
• US Class Current: 60/752
• CPC Class Codes: F23M 5/02 characterised by the shape of the bricks or blocks used
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A combustor for a gas turbine engine is provided which includes a plurality of liner segments and a support shell. The support shell includes an interior and an exterior surface, a plurality of mounting holes, and a plurality of impingement coolant holes extending through the support shell. Each liner segment includes a panel and a plurality of mounting studs. The panel includes a face surface and a back surface, and a plurality of normal or inclined coolant holes extending therethrough. The back surface of the panel has a surface profile for improving the heat transfer properties of a liner segment without substantial increase in pressure drop across the combustor.

Claims

1. A combustor for a gas turbine engine comprising:

a support shell having an exterior surface, an interior surface and a plurality of impingement coolant holes extending through the support shell between the exterior surface and the interior surface;

at least one liner segment attached to the support shell, the liner segment comprising a panel having a face surface, a back surface and a plurality of coolant holes where in the back surface of the panel faces and is spaced from the the interior surface of the support shell and defines therebetween a gap, wherein at least a portion of the back surface of the panel has a surface profile for improving the heat transfer properties of the liner segment with negligible increase in pressure drop across the combustor when compared to a flat back surface of the panel, wherein the surface profile comprises an array of surface features having a height A of less than 100 mils and a spacing B of greater than 10 mils.

2. A combustor according to claim 1, wherein the surface profile increases the surface area of the back surface of the panel by at least 50% compared to the flat back surface.

4. A combustor according to claim 1 or 3, wherein the heat transfer efficiency is increased at least 20% compared to the flat back surface.

5. A combustor according to claim 4, wherein the heat transfer efficiency is increased between 20% and 50% compared to the flat back surface.

6. A combustor according to claim 1 or 3, wherein the increase in pressure drop is less than 10% compared to the flat back surface.

7. A combustor according to claim 6, wherein the increase in pressure drop is less than 5% compared to the flat back surface.

8. A combustor according to claim 1, wherein the increase in surface area is between 1.5 to 4.75 times compared to the flat back surface.

9. A combustor according to claim 1 or 3, wherein the surface profile comprises an array of surface features selected from the group consisting of square-base pins, circular-base pins, square-base pyramids, circular base cones, tapered pins, pyramids with polygonal bases, frustums conical convex cones, concave cones, serpentine micro ribs, hemispheres, dimples and combinations thereof.

3. A combustor for a gas turbine engine comprising:

a support shell having an exterior surface, an interior surface and a plurality of impingement coolant holes extending through the support shell between the exterior surface and the interior surface;

at least one liner segment attached to the support shell, the liner segment comprising a panel having a face surface, a back surface and a plurality of coolant holes wherein the back surface of the panel faces and is spaced from the interior surface of the support shell and defines therebetween a gap, wherein at least a portion of the back surface of the panel has a surface profile for improving the heat transfer properties of the liner segment with negligible increase in pressure drop across the combustor when compared to a flat back surface of the panel, wherein the surface profile increases the surface area of the back surface of the panel to between 1.5 to 4.75 times compared to the flat back surface.

10. A combustor according to claim 3, wherein the surface profile comprises an array of surface features having a height A of less than 100 mils and a spacing B of greater than 10 mils.

11. A combustor according to claim 10, wherein height A is between 4 and 45 mils and spacing B is between 15 and 50 mils.