Systems and methods for control of combustion dynamics in combustion system

Patent metadata

Field	Value
Publication number	US-2016273449-A1
Application number	US-201514659399-A
Country	US
Kind code	A1
Filing date	Mar 16, 2015
Priority date	Mar 16, 2015
Publication date	Sep 22, 2016
Grant date	—

Abstract

A system includes a gas turbine engine having a first combustor and a second combustor. Each combustor has at least one fuel nozzle that receives a mixture of liquid fuel and water, via main and pilot fuel supplies, and that injects the mixture and an oxidant into a combustion chamber. A biasing system is disposed in a fuel path upstream of the fuel nozzles in the second combustor to vary the ratios of water/main fuel or water/pilot fuel or the flow rates of such mixtures. The biasing system is configured to help reduce a combustion dynamics amplitude or modal coupling between the first combustor and the second combustor.

First claim

1 . A system, comprising:
a gas turbine engine comprising:
a first combustor comprising a first fuel nozzle disposed in a first head end chamber of the first combustor, wherein the first fuel nozzle is configured to inject a first fuel mixture and an oxidant into a first combustion chamber of the first combustor, the first fuel mixture comprising a first ratio of liquid fuel and water;
a second combustor comprising a second fuel nozzle disposed in a second head end chamber of the second combustor, wherein the second fuel nozzle is configured to inject a second fuel mixture into a second combustion chamber of the second combustor, the second fuel mixture comprising a second ratio of the liquid fuel and the water; and
a biasing system disposed along a fuel path upstream of the first and the second fuel nozzles, wherein the biasing system is configured to help reduce a combustion dynamics amplitude or modal coupling between the first combustor and the second combustor.

2 . The system of claim 1 , wherein the biasing system comprises a first orifice plate along the fuel path configured to regulate a first fuel flow rate of the first fuel mixture.

3 . The system of claim 2 , wherein the biasing system comprises a second orifice plate along the fuel path configured to regulate a second fuel flow rate of the second fuel mixture, and wherein the first fuel flow rate is different from the second fuel flow rate.

4 . The system of claim 3 , wherein the first orifice plate has at least one difference relative to the second orifice plate; and wherein the at least one difference comprises at least one of different orifice diameters, different orifice shapes, different numbers of orifices, different geometrical arrangements of orifices, different distances between adjacent orifices, different valve types, different valve shapes, different number of valves, different valve sizes, or any combination thereof.

5 . The system of claim 1 , wherein the biasing system comprises, along the fuel path, a first mixing system configured to control the first ratio of the liquid fuel to the water of the first fuel mixture, and wherein the first fuel nozzle is a primary fuel nozzle having a main fuel portion through which the first fuel mixture and oxidant are injected.

6 . The system of claim 5 , wherein the biasing system comprises, along the fuel path, a second mixing system configured to control the second ratio of the liquid fuel to the water of the second fuel mixture, wherein the first ratio is different from the second ratio, and wherein the second fuel nozzle is a primary fuel nozzle having a main fuel portion through which the second fuel mixture and oxidant are injected.

7 . The system of claim 6 , wherein the second mixing system is configured to cause the first ratio to be different from the second ratio.

8 . The system of claim 1 , wherein the biasing system comprises, along the fuel path, a first mixing system configured to control a third ratio of the liquid fuel to the water of the first fuel mixture, and wherein the first fuel nozzle is a primary fuel nozzle having a pilot fuel portion through which the third fuel mixture and oxidant are injected.

9 . The system of claim 8 , wherein the biasing system comprises, along the fuel path, a second mixing system configured to control a fourth ratio of the liquid fuel to the water of the second fuel mixture, wherein the third ratio is different from the fourth ratio, and wherein the second fuel nozzle is a primary fuel nozzle having a pilot fuel portion through which the fourth fuel mixture and oxidant are injected.

10 . The system of claim 1 , wherein the biasing system comprises, along the fuel path, a first mixing system configured to control a first ratio of the liquid fuel to the water of the first fuel mixture and a second ratio of the liquid fuel to the water of the second fuel mixture, wherein the liquid fuel is a main fuel, and wherein the first fuel nozzle and the second fuel nozzle are primary fuel nozzles having a main fuel portion through which respective portions the first fuel mixture and the second fuel mixture are injected with an oxidant.

11 . The system of claim 10 , wherein the biasing system comprises, along the fuel path, a second mixing system configured to control a third ratio of the liquid fuel to the water of a third fuel mixture and a fourth ratio of the liquid fuel to the water of a fourth fuel mixture, wherein the liquid fuel is a pilot fuel; wherein the first and second fuel nozzles are primary fuel nozzles having a pilot fuel portion through which respective portions the third fuel mixture and the fourth fuel mixture are injected with an oxidant.

12 . The system of claim 11 , wherein the first mixing system and the second mixing system are configured to cause at least one of the first ratio being different from the second ratio and the third ratio being different from the fourth ratio.

13 . The system of claim 1 , comprising:
a first plurality of first combustors; and a second plurality of second combustors, wherein the first and second combustors are arranged in a pattern to help reduce the combustion dynamics amplitude or modal coupling between the first plurality of first combustors and the second plurality of second combustors.

14 . A system, comprising:
a gas turbine engine comprising:
a combustor comprising a first fuel nozzle and a second fuel nozzle disposed in a head end chamber of the combustor, wherein the fuel nozzles are primary fuel nozzles having a main fuel portion and a primary fuel portion, the fuel nozzles being configured to inject a fuel mixture and an oxidant into a combustion chamber of the combustor, the fuel mixture comprising a liquid fuel and water; and

a biasing system disposed in a fuel path upstream of the combustor, wherein the biasing system is configured to at least partially control a combustion dynamics amplitude in the combustor.

15 . The system of claim 14 , wherein the biasing system comprises at least one orifice plate disposed along the fuel path, the biasing system being configured to at least partially control a flow rate of the fuel mixture along the fuel path to at least the first fuel nozzle, such that the flow rate of the fuel mixture to the first fuel nozzle is different from a flow rate of the fuel mixture to the second fuel nozzle.

16 . The system of claim 15 , wherein the fuel mixture and oxidant are injected through the main fuel portion of the first fuel nozzle and the second fuel nozzle.

17 . The system of claim 15 , wherein the fuel mixture and oxidant are injected through the pilot fuel portion of the first fuel nozzle and the second fuel nozzle.

18 . The system of claim 14 , wherein the biasing system comprises a mixing system configured to control a ratio of the liquid fuel to the water of the fuel mixture to at least the first fuel nozzle, such that the ratio of the fuel mixture to the first fuel nozzle is different from the ratio of the fuel mixture to the second fuel nozzle.

19 . A method, comprising:
injecting a first fuel mixture and an oxidant into a first combustion chamber of a first combustor using a first fuel nozzle disposed in a first head end chamber of the first combustor, the first fuel mixture comprising a first ratio of liquid fuel and water and the first fuel nozzle comprising a primary fuel nozzle having a main fuel portion through which the first fuel mixture and oxidant are injected; injecting a second fuel mixture and the oxidant into a second combustion chamber of a second

Assignees

• Gen Electric

Inventors

• Dicintio Richard Martin
• Crothers Sarah Lori

Classifications

• F23R2900/00013

  Reducing thermo-acoustic vibrations by active means · CPC title

• F23M20/005

  Noise absorbing means · CPC title

• F02C3/30 Primary

  Adding water, steam or other fluids {for influencing combustion, e.g. to obtain cleaner exhaust gases (F02C7/141, F02C7/30, F01D21/00, F01K21/04, F23D11/10 take precedence)} · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F05D2270/14

  to control thermoacoustic behaviour in the combustion chambers · CPC title