Combustor liner having cooling ring with fin having space filling curve

Inventors: Lawrence Binek (Glastonbury, CT); Frederick Rosenberger (Marlborough, CT); Mark Rohrer (West Hartford, CT)

Assignee: RTX Corporation

F23R3/005 B33Y80/00 F23R3/002 F05D2260/2214 F05D2260/22141 F23R3/50 F23R2900/03043

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Quick Facts

Patent No.: US 12693015
App. No.: 19/373,209
Granted: Jul 28, 2026
Kind: B1

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Abstract

A combustor liner for a gas turbine engine, the combustor liner defining a combustion chamber, includes a curved body and a cooling ring. The curved body includes a closed forward end, an open aft end opposite the forward end, an inner wall, and an outer wall radially outward from the inner wall, the outer wall defining an outer liner wall of the combustor liner. The cooling ring includes a fin that has a space filling curve that is modified such that an outer wall of the cooling ring matches a shape of the inner wall of the curved body. An inner wall of the cooling ring defines an inner liner wall of the combustor liner.

Claims (36)

1 . A combustor liner for a gas turbine engine, the combustor liner defining a combustion chamber and comprising:

a curved body comprising:

a closed forward end;

an open aft end opposite the forward end;

an inner wall, and

an outer wall radially outward from the inner wall, the outer wall defining an outer liner wall of the combustor liner; and

a cooling ring comprising a fin that has a space filling curve that is modified such that an outer wall of the cooling ring matches a shape of the inner wall of the curved body, wherein an inner wall of the cooling ring defines an inner liner wall of the combustor liner and wherein the space filling curve is a Hilbert curve or a Peano curve.

2 . The combustor liner of claim 1 , wherein the cooling ring has an inlet at an upstream end of the cooling ring and an outlet at a downstream end of the cooling ring.

3 . The combustor liner of claim 2 , wherein the cooling ring comprises a channel formed by the fin, the channel extending from the inlet of the cooling ring to the outlet of the cooling ring.

4 . The combustor liner of claim 3 wherein the inner wall of the curved body has a radially outward angle.

5 . The combustor liner of claim 4 , wherein a portion of the channel increases in diameter toward the outlet of the cooling ring.

6 . The combustor liner of claim 1 , wherein the inner wall of the cooling ring is configured to be concentric with an exhaust duct.

7 . The combustor liner of claim 6 , wherein the inner wall of the cooling ring has an inner diameter sized to allow the exhaust duct to extend through the inner wall of the cooling ring with a space gap between the inner wall of the cooling ring and an outer surface of the exhaust duct.

8 . The combustor liner of claim 1 , wherein the cooling ring and the curved body are integral.

9 . The combustor liner of claim 1 , wherein the outer wall of the cooling ring is attached to the inner wall of the curved body.

10 . The combustor liner of claim 1 , wherein the cooling ring is an extruded part of the combustor liner.

11 . The combustor liner of claim 1 , wherein the cooling ring is an additively manufactured part of the combustor liner.

12 . The combustor liner of claim 11 , wherein the cooling ring is formed using laser powder bed fusion.

13 . The combustor liner of claim 1 , wherein the space filling curve of the fin is modified to fit an annular shape of the cooling ring.

14 . A combustor liner for a gas turbine engine, the combustor liner defining a combustion chamber, the combustor liner comprising:

a body defining a combustion chamber, the body comprising:

an inner wall; and

an outer wall radially outward from the inner wall; and

a cooling ring comprising:

a fin, wherein the fin has a Hilbert curve or a Peano curve;

an inlet formed by the fin at an upstream end of the cooling ring;

an outlet formed by the fin at a downstream end of the cooling ring opposite the inlet;

a channel formed by the fin and extending from the inlet of the cooling ring to the outlet of the cooling ring;

an outer wall extending from the inlet to the outlet; and

an inner wall radially inward from the outer wall and extending from the inlet to the outlet;

wherein the outer wall of the cooling ring matches a shape of the inner wall of the body; and

wherein the inner wall of the cooling ring defines an inner liner wall of the combustor liner.

15 . The combustor liner of claim 14 , wherein the Hilbert curve or the Peano curve is modified such that the outer wall of the cooling ring matches a shape of the inner wall of the body.

16 . The combustor liner of claim 15 , wherein a portion of the channel increases in diameter toward the outlet of the cooling ring.

17 . The combustor liner of claim 14 , wherein the inner wall of the cooling ring has an inner diameter sized to allow an exhaust duct to extend through the inner wall of the cooling ring with a space gap between the inner wall of the cooling ring and an outer surface of the exhaust duct.

18 . The combustor liner of claim 14 , wherein the cooling ring and the curved body are integral.