Cowl damper for combustor

Patent metadata

Field	Value
Publication number	US-12504168-B2
Application number	US-202318314414-A
Country	US
Kind code	B2
Filing date	May 9, 2023
Priority date	Oct 20, 2022
Publication date	Dec 23, 2025
Grant date	Dec 23, 2025

Abstract

A combustor for a turbomachine engine. The combustor includes a combustion chamber, and a cowl having an annular shape that is symmetric around a centerline axis of the turbomachine engine. The cowl includes a hollow cavity that is in fluid communication with the combustion chamber. The hollow cavity is a damper that reduces combustion dynamics of the combustor.

First claim

The invention claimed is:

1 . A combustor for a turbomachine engine, the combustor comprising:
a combustion chamber in which fuel and air are combusted to generate combustion gases, the generating of the combustion gases creating combustion dynamics in the combustion chamber; a fuel nozzle feeding the fuel to the combustion chamber; a dome having an outer wall and an inner wall, the dome at least partially defining the combustion chamber; and a cowl coupled directly to the outer wall and the inner wall of the dome, the cowl including a wall, the wall of the cowl being hollow and having an arcuate, annular shape that is symmetric around a centerline axis of the turbomachine engine, the cowl comprising a hollow cavity embedded within the wall of the cowl, the hollow cavity being in fluid communication with the combustion chamber to provide the air to the combustion chamber, a volume of the hollow cavity being configured such that the hollow cavity resonates at a frequency that damps the combustion dynamics in the combustion chamber so that the hollow cavity is a damper that reduces the combustion dynamics in the combustion chamber.

2 . The combustor of claim 1 , wherein reducing combustion dynamics of the combustor comprises at least one of reducing viscous losses and increasing heat dissipation.

3 . The combustor of claim 1 , wherein the damper damps combustion dynamics for at least one frequency between one hundred twenty Hertz to six hundred ninety Hertz.

4 . The combustor of claim 1 , wherein the cowl is a unitary component with an outer radius and an inner radius, the outer radius being greater than the inner radius, and
wherein the cowl comprises a plurality of holes positioned circumferentially around the centerline axis to receive a plurality of fuel nozzles of the turbomachine engine.

5 . The combustor of claim 1 , wherein the hollow cavity includes a first hollow cavity configured as an acoustic cavity that is a Helmholtz resonator and a second hollow cavity configured as a cooling cavity, the second hollow cavity being in fluid communication with the combustion chamber and having a plurality of intake holes for air to enter into the cooling cavity and a plurality of exit holes for air to exit from the cooling cavity into the combustion chamber.

6 . The combustor of claim 5 , wherein the acoustic cavity and the cooling cavity are adjacent to one another and are separated by a shared partition.

7 . The combustor of claim 1 , wherein the cowl comprises an outer component and an inner component, the outer component being annular in shape with a first radius around the centerline axis of the turbomachine engine, the inner component being annular in shape with a second radius around the centerline axis of the turbomachine engine, the second radius being smaller than the first radius to define a gap between the outer component and the inner component, and
wherein the gap is configured to receive a plurality of fuel nozzles of the turbomachine engine.

8 . The combustor of claim 7 , wherein the hollow cavity is a first hollow cavity in the outer component, the damper being an outer damper, and
wherein the cowl comprises a second hollow cavity in the inner component, the second hollow cavity being configured as an inner damper to reduce combustion dynamics of the combustor.

9 . The combustor of claim 8 , wherein the outer damper is configured to damp combustion dynamics for a first frequency, and the inner damper is configured to damp combustion dynamics for a second frequency that is different from the first frequency.

10 . The combustor of claim 9 , wherein the first frequency is between one hundred eighty Hertz and four hundred Hertz.

11 . The combustor of claim 9 , wherein the second frequency is between four hundred Hertz and two thousand Hertz.

12 . The combustor of claim 1 , further comprising an inner liner and an outer liner forming a circumferential boundary of the combustion chamber,
wherein a plurality of fasteners secure the dome, the inner liner and the outer liner, and a portion of the cowl therebetween, and the dome is positioned aft of the cowl and defines a forward boundary of the combustion chamber.

13 . The combustor of claim 12 , wherein the cowl comprises a plurality of solid portions proximate to the inner liner or the outer liner and the dome, wherein the fasteners pass through the plurality of solid portions of the cowl.

14 . The combustor of claim 1 , further comprising an inner liner and an outer liner together forming a circumferential boundary of the combustion chamber,
wherein the hollow cavity includes a damper neck that is partially forward or entirely forward of the inner liner or the outer liner, the damper neck directing (i) cooling air from the hollow cavity into the combustion chamber so that the cooling air cools the outer liner or the inner liner and (ii) acoustics of the combustion chamber into the hollow cavity such that the hollow cavity reduces at least one of acoustic noise and mechanical vibration.

15 . The combustor of claim 14 , wherein the hollow cavity is an acoustic cavity configured as a Helmholtz resonator to damp combustion dynamics for a particular frequency.

16 . The combustor of claim 15 , wherein the damper has a plurality of metering holes through which air enters the acoustic cavity.

17 . The combustor of claim 15 , wherein the hollow cavity includes a first hollow cavity configured as a first acoustic cavity and a first damper damping the combustion dynamics at a first frequency, and
wherein the hollow cavity includes a second hollow cavity configured as a second acoustic cavity and a second damper damping the combustion dynamics at a second frequency.

18 . The combustor of claim 17 , wherein the first frequency is between one hundred eighty Hertz and four hundred Hertz.

19 . The combustor of claim 17 , wherein the second frequency is between four hundred Hertz and two thousand Hertz.

20 . The combustor of claim 17 ,
wherein the first acoustic cavity includes a first damper neck opening into the combustion chamber of the combustor, and is configured as a first the Helmholtz resonator to damp the combustion dynamics at the first frequency, and wherein the second acoustic cavity has a second damper neck opening into the combustion chamber of the combustor, and is configured as a second the Helmholtz resonator to damp the combustion dynamics at the second frequency.

Assignees

• Gen Electric

Inventors

• Nath Hiranya
• Ganiger Ravindra Shankar
• Mohan Sripathi
• Vukanti Perumallu
• Kim Kwanwoo

Classifications

• F23R3/42 Primary

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/16 Primary

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title