Asymmetric introduction of steam into turbine engine combustion chamber

Patent metadata

Field	Value
Publication number	US-12416258-B2
Application number	US-202318120835-A
Country	US
Kind code	B2
Filing date	Mar 13, 2023
Priority date	Mar 13, 2023
Publication date	Sep 16, 2025
Grant date	Sep 16, 2025

Abstract

A method is provided for operating a turbine engine. During this method, fuel is injected into a combustion chamber of a combustor of the turbine engine. The combustion chamber extends circumferentially around a centerline. The fuel is combusted within the combustion chamber. Steam is introduced into the combustion chamber in an asymmetric pattern around the centerline.

First claim

What is claimed is:

1. A method for operating a turbine engine, comprising:
injecting fuel into a combustion chamber of a combustor of the turbine engine, the fuel injected into the combustion chamber through a plurality of fuel injector assemblies, wherein the combustion chamber is an annulus that extends circumferentially around a centerline;
combusting the fuel within the combustion chamber; and
introducing steam into the combustion chamber in an asymmetric pattern around the centerline using a plurality of steam delivery devices, the steam introduced into the combustion chamber through respective tips of the plurality of fuel injector assemblies, wherein the asymmetric pattern is divided into N number of sectors around a circumference of the centerline with equal arc lengths, the N number of sectors includes a first sector and a second sector, the first sector includes a first of the plurality of steam delivery devices, the second sector includes a second of the plurality of steam delivery devices, the steam is introduced into the combustion chamber in a first pattern about the centerline in the first sector, and the steam is introduced into the combustion chamber in a second pattern about the centerline in the second sector, and the second pattern is different than the first pattern;
wherein a first quantity of the steam is introduced into the combustion chamber in the first sector, and a second quantity of the steam is introduced into the combustion chamber in the second sector, and the second quantity of the steam is different than the first quantity of the steam.

2. The method of claim 1 , further comprising attenuating acoustic modes generated by the combustion of the fuel using the steam introduced into the combustion chamber in the asymmetric pattern.

3. The method of claim 1 , wherein the N number is an even number.

4. The method of claim 1 , wherein the N number is an odd number.

5. The method of claim 1 , wherein the plurality of steam delivery devices are arranged in an array and equally spaced around the centerline.

6. The method of claim 1 , wherein the steam is introduced into the combustion chamber in the asymmetric pattern through a first orifice and a second orifice with a different size than the first orifice.

7. The method of claim 1 , wherein the steam is introduced into the combustion chamber in the asymmetric pattern along a bulkhead of the combustor.

8. The method of claim 1 , wherein the fuel is injected into the combustion chamber in a symmetric pattern around the centerline.

9. The method of claim 1 , further comprising changing the asymmetric pattern based on an operating mode of the turbine engine.

10. An assembly for a turbine engine, comprising:
a combustor comprising a combustion chamber and a centerline, wherein the combustion chamber is an annulus that extends circumferentially around the centerline;
a fuel system configured to inject fuel into the combustion chamber for combustion; and
a steam system configured to introduce steam into the combustion chamber in an asymmetric pattern around the annulus using a plurality of steam delivery devices, the steam system comprising a steam source, a steam delivery circuit, and a plurality of steam delivery devices, wherein the asymmetric pattern is divided into a first half sector and a second half sector around the centerline, the steam system is configured to introduce the steam into the combustion chamber in a first pattern about the centerline in the first half sector, the steam system is configured to introduce the steam into the combustion chamber in a second pattern about the centerline in the second half sector, and the second pattern is different than the first pattern;
the steam delivery circuit including a supply circuit and a plurality of feed circuits, the supply circuit extending from the steam source to an interface of the plurality of feed circuits, each of the plurality of feed circuits extending from the interface to a respective one of the plurality of steam delivery devices.

11. The assembly of claim 10 , wherein
the steam system is configured to introduce a first quantity of the steam into the combustion chamber in the first half sector; and
the steam system is configured to introduce a second quantity of the steam into the combustion chamber in the second half sector, and the second quantity of the steam is different than the first quantity of the steam.

12. An assembly for a turbine engine, comprising:
a combustor comprising an annular combustion chamber and a centerline, the annular combustion chamber extending circumferentially around the centerline;
a fuel system configured to inject fuel into the annular combustion chamber for combustion; and
a steam system configured to introduce steam into the annular combustion chamber through at least a plurality of first orifices and a plurality of second orifices, the steam system including a first feed circuit, a second feed circuit and a supply circuit, the first feed circuit in communication with the plurality of first orifices, the second feed circuit in communication with the plurality of second orifices, the supply circuit in parallel fluid communication with the first feed circuit and the second feed circuit, the plurality of first orifices and the plurality of second orifices arranged in a non-repeating pattern circumferentially around the centerline, the steam system configured to introduce the steam into the annular combustion chamber through each of the plurality of first orifices at a first flowrate, and the steam system configured to introduce the steam into the annular combustion chamber through each of the plurality of second orifices at a second flowrate that is different than the first flowrate.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Boardman Gregory

Classifications

• F05D2270/08

  to produce clean exhaust gases · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F23R2900/00013

  Reducing thermo-acoustic vibrations by active means · CPC title

• F23R2900/00002

  Gas turbine combustors adapted for fuels having low heating value [LHV] · CPC title