Systems and methods for addition of fuel additives to control turbine corrosion

Patent metadata

Field	Value
Publication number	US-11859533-B2
Application number	US-202117338014-A
Country	US
Kind code	B2
Filing date	Jun 3, 2021
Priority date	Jun 3, 2021
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

A gas turbine engine system includes a gas turbine engine including a compressor, combustor including a plurality of late lean fuel injectors supplied with secondary fuel; gas turbine, and wash system configured to be attached and in fluid communication with the late lean fuel injectors. The wash system includes a water source including water; first fluid source including a first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal gas turbine components; a mixing chamber in communication with the water source and first fluid source; a water pump to pump the water to the mixing chamber; a first fluid pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at the late lean fuel injectors while the gas turbine engine is on-line.

First claim

What is claimed is:

1. A gas turbine engine system, comprising:
a gas turbine engine, the gas turbine engine including a compressor, a combustor, and a gas turbine, the combustor including a plurality of late lean fuel injectors supplied with a secondary fuel to an interior of the combustor, the plurality of late lean fuel injectors distal to a head end of the combustor, adjacent to an upstream side of the gas turbine, and configured to supply the secondary fuel in a direction substantially transverse to a longitudinal direction of the combustor; and
a wash system configured to be attached to and in fluid communication with the plurality of late lean fuel injectors of the combustor, the wash system including:
a water source supplying water;
a first fluid source supplying a first fluid, the first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal components of the gas turbine;
a mixing chamber in communication with the water source and the first fluid source;
a water pump configured to pump the water to the mixing chamber;
a first fluid pump configured to pump the first fluid to the mixing chamber;
a fluid line configured to be in fluid communication with the mixing chamber and at least one of the plurality of late lean fuel injectors such that a fluid from the mixing chamber including the water, the first fluid, or a mixture thereof is injected into the combustor at at least one of the plurality of late lean fuel injectors,

wherein the mixture is injected while the gas turbine engine is on-line.

2. The gas turbine engine system of claim 1 , wherein the first fluid source includes a mixture of demineralized/deionized water and at least one of magnesium (Mg), yttrium (Y), or detergent as vanadium ash formation mitigant, the mixture of demineralized/deionized water and at least one of magnesium (Mg), yttrium (Y), or detergent as vanadium ash formation mitigant is configured to be injected into the combustor at at least one of the plurality of late lean fuel injectors; and the mixture of demineralized/deionized water and at least one of magnesium (Mg), yttrium (Y), or detergent as vanadium ash formation mitigant is delivered to the at least one of the plurality of late lean fuel injectors and then conveyed to internal components of gas turbine with a flow of combustion gases from the combustor to the gas turbine.

3. The gas turbine engine system of claim 2 , wherein the mixture of demineralized/deionized water and magnesium (Mg), yttrium (Y), or detergent as vanadium ash formation mitigant is configured to remove vanadium from internal components of the gas turbine engine.

4. The gas turbine engine system of claim 2 , wherein the mixture of demineralized/deionized water and magnesium (Mg), yttrium (Y), or detergent as vanadium ash formation mitigant is provided as a solution or as a foam.

5. The gas turbine engine system of claim 1 , wherein the mixing chamber includes one or more angled counter flow nozzles therein, the one or more angled counter flow nozzles extending into the mixing chamber at an angle with respect to a central axis of the mixing chamber and configured to inject the first fluid at the angle in a direction counter to a flow of the water in the mixing chamber.

6. The gas turbine engine system of claim 1 , wherein the water source is in communication with the mixing chamber via a water source line and the water pump.

7. The gas turbine engine system of claim 1 , wherein the first fluid source is in communication with the mixing chamber via a first fluid source line and the first fluid pump.

8. The gas turbine engine system of claim 1 , further including a controller, the controller being in operative communication with the water pump and the first fluid pump, wherein the controller is configured to regulate flow of the water and the first fluid through the fluid line to at least one of the plurality of late lean fuel injectors.

9. The gas turbine engine system of claim 8 , wherein the controller further includes at least one flow control valve positioned in the fluid line, the at least one flow control valve in communication with the controller for enabling actuation of the at least one flow control valve between at least open and closed positions, the actuation caused by the controller.

10. The gas turbine engine system of claim 8 , wherein the controller further includes at least one flow sensor positioned in the fluid line, the at least one flow sensor in communication with the controller for sensing flow in the fluid line.

11. A method of washing an on-line gas turbine engine, the gas turbine engine including a compressor, a combustor, a gas turbine, the combustor including a plurality of late lean fuel injectors distal to a head end of the combustor, adjacent to an upstream side of the gas turbine, and supplied with a secondary fuel to an interior of the combustor, the method comprising:
supplying water from a water source to a mixing chamber of a wash system;
supplying a first fluid from a first fluid source to a mixing chamber of the wash system, the first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal components of the gas turbine;
supplying the water and first fluid to the mixing chamber including pumping water from the water source and pumping the first fluid from the first fluid source; and
injecting fluid from the mixing chamber to at least one of the plurality of late lean fuel injectors while the gas turbine engine is on-line, wherein each late lean fuel injector in the plurality of late lean fuel injectors are configured to inject the fluid from the mixing chamber in a direction substantially transverse to a longitudinal direction of the combustor.

12. The method of claim 11 , wherein the first fluid source includes a mixture of demineralized/deionized water and at least one of magnesium (Mg), yttrium (Y), or detergent.

13. The method of claim 12 , the method includes removing vanadium from internal components of the gas turbine engine by the mixture of demineralized/deionized water and magnesium (Mg), yttrium (Y), or detergent.

14. The method of claim 12 , the method including providing the mixture of demineralized/deionized water and magnesium (Mg), yttrium (Y), or detergent as a solution or as a foam.

15. The method of claim 11 , wherein the mixing chamber includes one or more angled counter flow nozzles therein, the one or more angled counter flow nozzles extending into the mixing chamber at an angle with respect to a central axis of the mixing chamber and to inject the first fluid at the angle in a direction counter to a flow of the water in the mixing chamber.

16. The method of claim 11 , the gas turbine engine further including a controller, the controller in operative communication with the water pump, the first fluid pump, and the fluid line, wherein the method includes the controller regulating a flow of the water and the first fluid through the fluid line to at least one of the plurality of late lean fuel injectors.

17. The method of claim 11 , the method further includes forming a vanadium based ash component magnesium orthovanadate [3MgO·V 2 O 5 ] by treating deposited vanadium at an appropriate Mg/V ratio, wherein magnesium orthovanadate does not melt and remains in a solid state on the internal components of the gas turbine.

18. The method of claim 11 , the method further includes forming an additional ash component, the additional ash component includes water soluble magnesium sulfate (MgSO 4 ), wherein MgSO 4 can be removed through water

Assignees

• Gen Electric

Inventors

• Scipio Alston Ilford
• Ekanayake Sanji

Classifications

• F02C3/22 Primary

  the fuel or oxidant being gaseous at standard temperature and pressure (F02C3/28 takes precedence) · CPC title

• B08B3/003

  Cleaning involving contact with foam · CPC title

• B08B3/02

  Cleaning by the force of jets or sprays · CPC title

• B08B3/08

  the liquid having chemical or dissolving effect · CPC title

• B08B9/0325

  Control mechanisms therefor · CPC title