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The present techniques are directed to a combustor for a gas turbine. For example, an embodiment provides a spool piece for the combustor. The spool piece includes an oxidant injection port configured for injection of an oxidant proximate to a flame in the combustor and a recycle-gas extraction port

The present techniques are directed to a combustor for a gas turbine. For example, an embodiment provides a spool piece for the combustor. The spool piece includes an oxidant injection port configured for injection of an oxidant proximate to a flame in the combustor and a recycle-gas extraction port configured for an extraction of a recycle gas from the combustor, wherein the recycle gas is isolated from the oxidant prior to the use of the oxidant in a flame.

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1. A gas turbine combustor, comprising: a combustor comprising a partially perforated combustion liner;an oxidant injection port configured for injection of an oxidant through the partially perforated combustion liner such that the oxidant is injected proximate to a flame in the combustor;a recycle-

1. A gas turbine combustor, comprising: a combustor comprising a partially perforated combustion liner;an oxidant injection port configured for injection of an oxidant through the partially perforated combustion liner such that the oxidant is injected proximate to a flame in the combustor;a recycle-gas extraction port configured for an extraction of a recycle gas from the combustor, wherein the partially perforated combustion liner allows a portion of the recycle gas to mix with at least a portion of an exhaust gas; anda barrier to prevent mixing of the recycle gas and the oxidant prior to introduction of the oxidant through the partially perforated combustion liner. 2. The gas turbine combustor of claim 1, comprising an injection lance configured to inject the oxidant directly into the flame. 3. The gas turbine combustor of claim 1, wherein the oxidant comprises a mixture of oxygen and a diluent gas. 4. The gas turbine combustor of claim 1, further comprising a swirler configured to create a spiral flow in the oxidant to enhance mixing with a fuel. 5. The gas turbine combustor of claim 1, wherein the combustor comprising a partially perforated combustion liner is configured to replace a preexiting combustor. 6. A method for operating a gas turbine engine, comprising: injecting an oxidant into an oxidant injection port on a combustor, wherein the combustor is configured to convey the oxidant to a flame in the combustor to form an exhaust gas;cooling a portion of the exhaust gas from the gas turbine engine to form a cooled exhaust gas;compressing the cooled exhaust gas to form a recycle gas;flowing the recycle gas around a perforated combustion can disposed around the flame to cool the perforated combustion can and form a hot recycle gas, wherein the oxidant and the recycle gas are prevented from mixing by a barrier prior to introduction of the oxidant through the perforated combustion can;flowing at least a portion of the recycle gas through the perforated combustion can to mix with the exhaust gas; andremoving a portion of the hot recycle gas through a recycle-gas extraction port on the combustor. 7. The method of claim 6, further comprising compressing the recycle gas in the compressor section of the gas turbine engine prior to injecting the recycle gas into the combustor. 8. The method of claim 6, further comprising compressing the oxidant in a compressor external to the gas turbine engine. 9. The method of claim 6, further comprising cooling the recycle gas in a direct contact cooler. 10. The method of claim 6, further comprising transferring heat energy from the hot recycle gas to the oxidant, or to a fuel, or to both, prior to their injection into the combustor. 11. The method of claim 6, further comprising controlling an injection of the oxidant, a fuel, or both, to all combustors to adjust a composition of the exhaust gas. 12. The method of claim 6, further comprising individually controlling an injection of the oxidant, a fuel, or both, to each of a plurality of combustors to adjust a composition of the exhaust gas. 13. The method of claim 6, further comprising: cooling the hot recycle gas to form a cooled recycle gas; andseparating carbon dioxide from the cooled recycle gas. 14. A gas turbine system, comprising: a combustor, comprising:a recycle gas port configured for an injection of a recycle gas for cooling the combustor;an oxidant injection port configured for an injection of an oxidant proximate to a flame in the combustor;a partially perforated combustion liner for allowing at least a portion of the recycle gas to mix with at least a portion of an exhaust gas; anda recycle-gas extraction port configured for an extraction of the recycle gas from the combustor, wherein a barrier prevents mixing of the recycle gas and the oxidant prior to introduction of the oxidant through the partially perforated combustion liner. 15. The gas turbine system of claim 14, further comprising: a compressor; anda turbine expander, wherein the compressor and turbine expander are mechanically coupled so that mechanical energy is transferred from the turbine expander to the compressor. 16. The gas turbine system of claim 14, further comprising a carbon dioxide removal system. 17. The gas turbine system of claim 14, further comprising a heat recovery unit configured to harvest energy from the exhaust gas from the gas turbine system. 18. The gas turbine system of claim 17, wherein the heat recovery unit comprises a heat recovery steam generator. 19. The gas turbine system of claim 17, comprising a turbine driven by energy recovered from the heat recovery unit. 20. The gas turbine system of claim 14, further comprising a heat exchanger configured to heat the oxidant with heat recovered from the recycle gas extracted from the combustor. 21. The gas turbine system of claim 14, further comprising a heat exchanger configured to heat a fuel with heat recovered from the recycle gas extracted from the combustor.