Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle is configured to produce a diffusion flame. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.

Abstract: In an embodiment, a system includes a gas turbine controller. The gas turbine controller is configured to receive a plurality of sensor signals from a fuel composition sensor, a pressure sensor, a temperature sensor, a flow sensor, or a combination thereof, included in a gas turbine engine system. The controller is further configured to execute a gas turbine model by applying the plurality of sensor signals as input to derive a plurality of estimated gas turbine engine parameters. The controller is also configured to execute a flame holding model by applying the plurality of sensor signals and the plurality of estimated gas turbine engine parameters as input to derive a steam flow to fuel flow ratio that minimizes or eliminates flame holding in a fuel nozzle of the gas turbine engine system.

Abstract: A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.

Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.

Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle is configured to produce a diffusion flame. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.

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.

Abstract: A gas turbine system includes a turbine combustor, a turbine, an exhaust gas compressor, an exhaust gas recirculation (EGR) system, a carbon black recovery system, and a carbon black production controller. The carbon black production controller monitors data corresponding to a parameter of the carbon black. The carbon black production controller is also configured to adjust, based on the data, the fuel provided to the turbine combustor while maintaining a ratio of the fuel to the oxidant within a predetermined range to adjust the parameter of the carbon black.

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 and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.

Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle is configured to produce a diffusion flame. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.

Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle has first and second passages that separately inject respective first and second flows into a chamber of the turbine combustor to produce a diffusion flame. The first flow includes a first fuel and a first diluent, and the second flow includes a first oxidant. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.

Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle is configured to produce a diffusion flame. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path. In addition, the system includes a first catalyst unit disposed along the exhaust recirculation path.

Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle has first and second passages that separately inject respective first and second flows into a chamber of the turbine combustor to produce a diffusion flame. The first flow includes a first fuel, and the second flow includes a first oxidant and a first diluent. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.

Abstract: A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.

Abstract: A system includes a fuel control system configured to control a fuel flow to one or more combustors and an oxidant control system configured to control an oxidant flow to each combustor of the one or more combustors, wherein the oxidant flow is configured to at least partially react with the fuel flow within the one or more combustors to form an exhaust gas flow. The system also includes an exhaust gas system configured to direct a recirculation flow of the exhaust gas flow to each combustor of the one or more combustors; and a controller coupled to the fuel control system, the oxidant control system, and the exhaust gas system. The controller is configured to independently control a fuel-to-oxidant ratio and an exhaust gas-to-oxidant ratio. The FOR is the fuel flow divided by the oxidant flow, and the EGOR is the recirculation flow divided by the oxidant flow.

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.

Abstract: 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.

Abstract: In an embodiment, a system includes a gas turbine controller. The gas turbine controller is configured to receive a plurality of sensor signals from a fuel composition sensor, a pressure sensor, a temperature sensor, a flow sensor, or a combination thereof, included in a gas turbine engine system. The controller is further configured to execute a gas turbine model by applying the plurality of sensor signals as input to derive a plurality of estimated gas turbine engine parameters. The controller is also configured to execute a flame holding model by applying the plurality of sensor signals and the plurality of estimated gas turbine engine parameters as input to derive a steam flow to fuel flow ratio that minimizes or eliminates flame holding in a fuel nozzle of the gas turbine engine system.

Abstract: A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including a first oxidant conduit configured to inject a first oxidant through a plurality of first oxidant openings configured to impart swirling motion to the first oxidant in a first rotational direction, a first fuel conduit configured to inject a first fuel through a plurality of first fuel openings configured to impart swirling motion to the first fuel in a second rotational direction, and a second oxidant conduit configured to inject a second oxidant through a plurality of second oxidant openings configured to impart swirling motion to the second oxidant in a third rotational direction. The first fuel conduit surrounds the first oxidant conduit and the second oxidant conduit surrounds the first fuel conduit.

Abstract: A method includes combusting a fuel and an oxidant in a combustor of an exhaust gas recirculation (EGR) gas turbine system that produces electrical power and provides a portion of the electrical power to an electrical grid. The method further includes controlling, via one or more processors, one or more parameters of the EGR gas turbine system to decrease the portion of the electrical power provided to the electrical grid in response to an over-frequency event associated with the electrical grid, wherein controlling the one or more parameters comprises decreasing a flow rate of fuel to the combustor in response to the over-frequency event.

Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.