System and method for a multi-wall turbine combustor
A system includes a turbine combustor, which includes a first wall disposed about a combustion chamber, a second wall disposed about the first wall, and a third wall disposed about the second wall. The third wall is configured to combine an exhaust gas with an oxidant and the combustion chamber is configured to combust a mixture of a fuel, the oxidant, and the exhaust gas.
1. A system, comprising:
a turbine combustor, comprising:
a first wall disposed circumferentially about a combustion chamber, wherein the first wall comprises a combustion liner, a transition piece, or any combination thereof, and wherein the combustion chamber is configured to combust a mixture of a fuel, an oxidant, and an exhaust gas;
a second wall disposed circumferentially about the first wall and the combustion chamber, wherein the second wall defines an opening and comprises a flow sleeve, an impingement sleeve, or any combination thereof; and
a third wall disposed circumferentially about the second wall, the first wall, and the combustion chamber, wherein the third wall defines at least one exhaust gas port configured to receive the exhaust gas, and wherein the third wall comprises an outer sleeve;
wherein the second wall and the third wall define a first passage configured to receive the oxidant from at least one oxidant port and to receive the exhaust gas from the at least one exhaust gas port, to combine the exhaust gas with the oxidant to form an oxidant-exhaust gas mixture, and to direct the oxidant-exhaust gas mixture through the first passage in a direction away from a head end portion of the turbine combustor; and
wherein the first wall and the second wall define a second passage configured to receive the oxidant-exhaust gas mixture from the first passage via the opening of the second wall, and to direct the oxidant-exhaust gas mixture through the second passage in a second direction toward the head end portion of the turbine combustor, opposite the first direction.
2. The system of claim 1 , wherein the third wall comprises the at least one oxidant port.
3. The system of claim 2 , wherein the at least one oxidant port is disposed upstream from the at least one exhaust gas port.
4. The system of claim 2 , wherein the at least one oxidant port is disposed downstream from the at least one exhaust gas port.
5. The system of claim 2 , comprising at least one oxidant conduit extending through a casing of the turbine combustor to the at least one oxidant port, wherein the at least one oxidant conduit is configured to segregate the oxidant from the exhaust gas outside of the third wall.
6. The system of claim 2 , wherein the at least one exhaust gas port comprises a plurality of exhaust gas ports, a bell mouth, or any combination thereof.
7. The system of claim 1 , wherein the combustor comprises a plurality of turbulators disposed along the flow path.
8. The system of claim 1 , wherein the second wall comprises a plurality of openings.
9. The system of claim 1 , comprising a bypass tube passing through the first, second, and third walls, wherein the bypass tube is configured to transfer the exhaust gas directly to the combustion chamber.
10. The system of claim 1 , comprising a gas turbine engine having the turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine, wherein the exhaust gas compressor is configured to compress and route the exhaust gas to the turbine combustor.
11. The system of claim 10 , comprising an exhaust gas extraction system coupled to the gas turbine engine, and a hydrocarbon production system coupled to the exhaust gas extraction system.
12. The system of claim 10 , wherein the gas turbine engine is a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine.
13. A method, comprising:
flowing an exhaust gas and an oxidant along a flow path through a multi-wall turbine combustor, wherein the multi-wall turbine combustor comprises a first wall surrounding a combustion chamber, wherein the first wall comprises a combustion liner, a transition piece, or any combination thereof, a second wall surrounding the first wall, wherein the second wall comprises a flow sleeve, an impingement sleeve, or any combination thereof, and a third wall surrounding the second wall, wherein the third wall comprises at least one exhaust gas port configured to receive the exhaust gas and an outer sleeve, wherein the flow path extends through:
a first passage defined by the second wall and the third wall, wherein the first passage is configured to receive the oxidant from at least one oxidant port and to receive the exhaust gas from the at least one exhaust gas port, to combine the exhaust gas with the oxidant to form an oxidant-exhaust gas mixture, and to direct the oxidant-exhaust gas mixture through the first passage in a first direction away from a head end portion of the multi-wall turbine combustor; and
a second passage defined by the first wall and the second wall, wherein the first passage is configured to receive the oxidant-exhaust gas mixture from the first passage via an opening of the second wall, and to direct the oxidant-exhaust gas mixture through the second passage in a second direction toward the head end portion of the multi-wall turbine combustor, opposite the first direction; and
combusting a mixture of a fuel, the oxidant, and the exhaust gas within the combustion chamber.
14. The method of claim 13 , comprising supplying the oxidant and the exhaust gas independently to the first passage of the multi-wall turbine combustor.