System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation

Patent metadata

Field	Value
Publication number	US-9903588-B2
Application number	US-201414444601-A
Country	US
Kind code	B2
Filing date	Jul 28, 2014
Priority date	Jul 30, 2013
Publication date	Feb 27, 2018
Grant date	Feb 27, 2018

Abstract

In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.

First claim

The invention claimed is:

1. A system comprising:
a turbine combustor comprising:
a combustor liner disposed about a combustion chamber;
a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, wherein the head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber;
a flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor, wherein the gas flow comprises a substantially inert gas;
a barrier section within the passage, wherein the barrier section is configured to substantially block the portion of the oxidant flow toward the turbine end and to substantially block the gas flow toward the head end within the passage, wherein the barrier section is configured to provide a dynamic barrier configured to separate the passage into an oxidant section and a cooling section, wherein the dynamic barrier comprises a fluid interface between the portion of the oxidant flow and the gas flow where the oxidant flow and the gas flow interact, and a position of the dynamic barrier is movable along a length of the passage; and
a controller configured to control the portion of the oxidant flow into the oxidant section and the gas flow into the cooling section, wherein the controller is configured to move the dynamic barrier along the length of the passage based at least in part on controlling the portion of the oxidant flow, the gas flow, or any combination thereof.

2. The system of claim 1 , wherein the gas flow comprises an exhaust gas, wherein the exhaust gas comprises less than approximately 5 percent by volume of the oxidant or the first fuel.

3. The system of claim 1 , wherein the barrier section comprises a physical barrier configured to extend at least partially between the combustor liner and the flow sleeve across the passage, wherein the physical barrier is configured to separate the passage into the oxidant section and the cooling section.

4. The system of claim 1 , wherein the barrier section comprises a plurality of flow guides configured to restrict the passage at the dynamic barrier.

5. The system of claim 1 , wherein the combustor liner comprises a plurality of mixing holes and a plurality of dilution holes, wherein the plurality of mixing holes is configured to direct at least one of the oxidant flow and the gas flow into the combustion chamber, and the plurality of dilution holes is configured to direct the gas flow into the combustion chamber.

6. The system of claim 1 , comprising a gas turbine engine having the turbine combustor, a turbine driven by the combustion gases from the turbine combustor and that outputs an exhaust gas, and an exhaust gas compressor driven by the turbine, wherein the exhaust gas compressor is configured to compress and to route the exhaust gas to the turbine combustor.

7. The system of claim 6 , wherein the gas turbine engine is a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine.

8. The system of claim 6 , comprising an exhaust gas extraction system coupled to the gas turbine engine, and a hydrocarbon production system coupled to the exhaust gas extraction system.

9. The system of claim 1 , wherein the head end comprises a first fuel nozzle configured to direct the first fuel flow into the combustion chamber, and a second fuel nozzle configured to direct a second fuel flow into the combustion chamber, wherein the first fuel nozzle is controlled separately from the second fuel nozzle.

10. A system comprising:
a turbine combustor comprising:
a combustor liner disposed about a combustion chamber; and
a flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage comprises:
an oxidant section configured to direct an oxidant in a first direction, wherein the oxidant is configured to react with a first fuel in the combustion chamber to produce combustion gases;
a cooling section configured to direct an inert gas in a second direction substantially opposite to the first direction, wherein the inert gas is configured to cool the combustor liner and the combustion gases in the combustion chamber; and
a barrier section between the oxidant section and the cooling section, wherein the barrier section is configured to substantially separate the oxidant in the oxidant section from the inert gas in the cooling section, wherein the barrier section is configured to provide a dynamic barrier comprising a fluid interface between the oxidant and the inert gas where the oxidant and the inert gas interact directly, and a position of the dynamic barrier is movable along a length of the passage; and
a controller configured to control a first flow of the oxidant into the oxidant section and a second flow of the inert gas into the cooling section, wherein the controller is configured to move the dynamic barrier within the passage based at least in part on controlling the first flow, the second flow, or any combination thereof.

11. The system of claim 10 , wherein the controller is further configured to control a ratio between the oxidant and the first fuel in the combustion chamber.

12. The system of claim 11 , comprising a first fuel nozzle configured to inject the first fuel into the combustion chamber, wherein the controller is configured to control one or more flows through the first fuel nozzle to adjust a first ratio between the oxidant and the first fuel in the combustion chamber.

13. The system of claim 12 , comprising a second fuel nozzle configured to inject a second fuel into the combustion chamber, wherein the controller is configured to control one or more flows through the second fuel nozzle to adjust a second ratio between the oxidant and the second fuel in the combustion chamber.

14. The system of claim 10 , wherein the inert gas comprises an exhaust gas, wherein the exhaust gas comprises less than approximately 5 percent by volume of the oxidant or the first fuel.

15. The system of claim 10 , wherein the passage comprises a physical barrier that at least partially extends between the combustor liner and the flow sleeve.

16. The system of claim 10 , wherein the oxidant section comprises a plurality of mixing holes configured to direct the oxidant into the combustion chamber to mix with the first fuel, to increase a concentration of oxidant in the combustion chamber, or to raise a temperature of a reaction with the first fuel, or any combination thereof.

17. The system of claim 10 , wherein the coolant section comprises a plurality of dilution holes configured to direct a first portion of the inert gas into the combustion chamber to cool the combustor liner, to cool the combustion gases in the combustion chamber, or to reduce emissions of the combustion gases, or any combination thereof.

18. A method comprising:
injecting an oxidant and a fuel into a combustion chamber from a head end of a turbine combustor;
combusting the oxidant and the fuel in the combustion chamber to provide substantially stoichiometric combustion;
cooling the combustion chamber with an exhaust gas flow, wherein the exhaust gas flow is directed upstream from a turbine end of the turbine combustor toward the head end along a passage disposed about the combustion chamber;
substantially blocking the exhaust gas flow within the passage with a barrier, wherein the barrier comprises a dynamic barrier c

Assignees

• Gen Electric
• Exxonmobil Upstream Res Co

Inventors

• Slobodyanskiy Ilya Aleksandrovich
• Davis Jr Lewis Berkley
• Minto Karl Dean

Classifications

• F02C3/34

  with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle · CPC title

• F23C2202/30

  Premixing fluegas with combustion air · CPC title

• F23C2202/20

  Premixing fluegas with fuel · CPC title

• F23N2221/12

  Recycling exhaust gases · CPC title

• F23R3/002

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