Turbine system with exhaust gas recirculation, separation and extraction

Patent metadata

Field	Value
Publication number	US-10316746-B2
Application number	US-201615014981-A
Country	US
Kind code	B2
Filing date	Feb 3, 2016
Priority date	Feb 4, 2015
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.

First claim

The invention claimed is:

1. A system, comprising:
a turbine combustor, comprising:
a liner defining a combustion chamber;
a flow sleeve disposed radially outward of the liner comprising a forward portion and an aft portion;
a first volume configured to receive a combustion fluid and to direct the combustion fluid into the combustion chamber, wherein at least a portion of the first volume is disposed radially outward of the forward portion of the flow sleeve, wherein the first volume is disposed within a head end of the turbine combustor;
a cap positioned proximate to the head end of the turbine combustor and coupled to a forward end of the flow sleeve to form a seal;
a second volume disposed at least partially between the flow sleeve and the liner, wherein the second volume is configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber, wherein the seal is configured to block the first flow of the exhaust gas from flowing into the head end of the turbine combustor; and
a third volume disposed axially downstream from the first volume and circumferentially about at least a portion of the second volume, wherein the third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction conduit, the third volume is isolated from each of the first volume and from the second volume, and the aft portion of the flow sleeve isolates the second volume from the third volume;
wherein the forward portion of the flow sleeve comprises one or more first openings configured to enable the combustion fluid to flow radially inward through the flow sleeve, the liner comprises one or more second openings into the combustion chamber, and the first volume is configured to direct the combustion fluid through the one or more first openings of the flow sleeve, through the one or more second openings of the liner, and into the combustion chamber.

2. The system of claim 1 , comprising:
a housing, wherein the flow sleeve is disposed within the housing, and the third volume is defined between the aft portion of the flow sleeve and the housing; and
a flange extending radially outward from the forward portion of the flow sleeve to the housing, wherein the flange isolates the third volume from the first volume.

3. The system of claim 1 , wherein the extraction conduit is positioned between a transition piece and a head end of the turbine combustor.

4. The system of claim 1 , comprising:
a housing, wherein the liner is disposed within the housing and the flow sleeve is disposed within the housing, wherein the second volume is defined between the liner and the flow sleeve, and the third volume is defined between the flow sleeve and the housing.

5. The system of claim 1 , comprising an exhaust gas compressor configured to compress and to route the exhaust gas to the turbine combustor.

6. The system of claim 1 , comprising a gas turbine engine having the turbine combustor, wherein the gas turbine engine is a stoichiometric exhaust gas recirculation gas turbine engine.

7. The system of claim 1 , comprising an exhaust gas extraction system coupled to the extraction conduit, and a hydrocarbon production system coupled to the exhaust gas extraction system.

8. The system of claim 1 , wherein a first cross-sectional flow area of the second volume is less than a second cross-sectional flow area of the third volume.

9. A system, comprising:
a turbine combustor, comprising:
a housing;
a liner defining a combustion chamber;
a flow sleeve disposed about the liner;
a first volume disposed in a head end of the combustion chamber, wherein the first volume is configured to receive a combustion fluid and to provide the combustion fluid to the combustion chamber;
a third volume disposed downstream of the first volume and defined between the flow sleeve and the housing, wherein the third volume is configured to receive a second flow of recirculated combustion products and to direct the second flow of recirculated combustion products out of the turbine combustor via an extraction conduit; and
a flange extending between the flow sleeve and the housing, wherein the flange is configured to block flow of the combustion fluid into the third volume and to block flow of the second flow of recirculated combustion products into the first volume.

10. The system of claim 9 , comprising a second volume defined between the liner and the flow sleeve, wherein the second volume is configured to receive a first flow of recirculated combustion products and to direct the first flow of recirculated combustion products into the combustion chamber, and the flow sleeve isolates the second volume from the third volume.

11. The system of claim 10 , comprising a transition piece having an impingement sleeve, wherein the impingement sleeve enables the first flow of recirculated combustion products to flow into the second volume.

12. The system of claim 9 , wherein the extraction conduit is positioned between a transition piece and the head end of the turbine combustor.

13. The system of claim 9 , comprising an exhaust gas compressor configured to compress and to route the second flow of recirculated combustion products to the turbine combustor.

14. The system of claim 9 , comprising an exhaust gas extraction system coupled to the extraction conduit, and a hydrocarbon production system coupled to the exhaust gas extraction system.

15. The system of claim 9 , comprising a gas turbine engine having the turbine combustor, wherein the gas turbine engine is a stoichiometric exhaust gas recirculation gas turbine engine.

16. A method, comprising:
combusting an oxidant and a fuel in a combustion chamber of a turbine combustor to generate combustion products;
compressing, via a recirculating fluid compressor, at least some of the combustion products generated by the turbine combustor to generate compressed combustion products;
cooling a liner of the turbine combustor using a first flow of the compressed combustion products through a second volume disposed at least partially around the combustion chamber;
separating a second flow of the compressed combustion products within the turbine combustor from the oxidant, the fuel, and the first flow of the compressed combustion products, wherein the second flow of the compressed combustion products are separated from the first flow of the compressed combustion products by a flow sleeve that extends circumferentially about the liner, wherein the second volume is at least partially disposed between the flow sleeve and the liner;
separating the second flow of the compressed combustion products from a first volume via a flange, wherein the first volume is configured to receive the oxidant, the fuel, or both; and
routing at least some of the oxidant, the fuel, or both, into the combustion chamber in a radial direction from the first volume upstream of the turbine combustor and across the second volume via one or more first combustion fluid openings in the flow sleeve and one or more second combustion fluid openings in the liner, wherein the one or more first combustion fluid openings and the one or more second combustion fluid openings are disposed upstream of the flange.

17. The method of claim 16 , wherein combusting the oxidant and the fuel comprises operating the turbine combustor in a stoichiometric combustion mode of operation.

18. The method of claim 16 , comprising directing the first flow of the compressed combustion

Assignees

• Gen Electric
• Exxonmobil Upstream Res Co

Inventors

• Allen Jonathan Kay
• Borchert Bradford David
• Trout Jesse Edwin
• Slobodyanskiy Ilya Aleksandrovich
• Valeev Almaz
• Sidko Igor Petrovich
• Roberts Matthew Eugene
• Ginesin Leonid Yul'Evich

Classifications

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F23C9/08

  for reducing temperature in combustion chamber, e.g. for protecting walls of combustion chamber · CPC title

• F23R3/28

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

• F23C2202/50

  Control of recirculation rate · CPC title