A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.

A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.

An apparatus for burning of a gaseous fuel includes a gas manifold comprising a blast tube with an axis of rotation and an outer wall; a center bluff body disposed inside the blast tube; a plurality of aerodynamic blocks circumferentially distributed in the annular space between the blast tube and the center bluff body, creating passage channels for combustion air between the aerodynamic blocks; two injector nozzles located inside the wake zone of each of the aerodynamic block and are fluidically communicating to the gas manifold; an air control mechanism comprising a center hub and a plurality of air control modules. The control modules fit through the passage channels. Each air control module comprises an air deflector located at the outer edge of a passage channel.

An apparatus for burning of a gaseous fuel includes a gas manifold comprising a blast tube with an axis of rotation and an outer wall; a center bluff body disposed inside the blast tube; a plurality of aerodynamic blocks circumferentially distributed in the annular space between the blast tube and the center bluff body, creating passage channels for combustion air between the aerodynamic blocks; two injector nozzles located inside the wake zone of each of the aerodynamic block and are fluidically communicating to the gas manifold; an air control mechanism comprising a center hub and a plurality of air control modules. The control modules fit through the passage channels. Each air control module comprises an air deflector located at the outer edge of a passage channel.

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 control system configured to control flow rates of at least one oxidant and at least one fuel to the turbine combustor in a stoichiometric control mode and a non-stoichiometric control mode, wherein the stoichiometric control mode is configured to change the flow rates and provide a substantially stoichiometric ratio of the at least one fuel with the at least one oxidant, and the non-stoichiometric control mode is configured to change the flow rates and provide a non-stoichiometric ratio of the at least one fuel with the at least one oxidant.

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 control system configured to control flow rates of at least one oxidant and at least one fuel to the turbine combustor in a stoichiometric control mode and a non-stoichiometric control mode, wherein the stoichiometric control mode is configured to change the flow rates and provide a substantially stoichiometric ratio of the at least one fuel with the at least one oxidant, and the non-stoichiometric control mode is configured to change the flow rates and provide a non-stoichiometric ratio of the at least one fuel with the at least one oxidant.

A locally powered intermittent pilot combustion controller may include an igniter, a thermal electric and/or photoelectric device that produces an electrical signal having power when exposed to a flame, and a local power source for providing power when the thermal electric and/or photoelectric device is not exposed to a flame. In some cases, the intermittent pilot combustion controller may include a memory for storing information about an ignition sequence for igniting a pilot flame, and a controller coupled to the memory. The controller may be configured to initiate the ignition sequence of the pilot flame using information stored in the memory, determine whether the ignition was successful by monitoring the electrical signal produced by the thermal electric and/or photoelectric device, and adjust the information stored in the memory based on whether the ignition sequence completed successfully.

A locally powered intermittent pilot combustion controller may include an igniter, a thermal electric and/or photoelectric device that produces an electrical signal having power when exposed to a flame, and a local power source for providing power when the thermal electric and/or photoelectric device is not exposed to a flame. In some cases, the intermittent pilot combustion controller may include a memory for storing information about an ignition sequence for igniting a pilot flame, and a controller coupled to the memory. The controller may be configured to initiate the ignition sequence of the pilot flame using information stored in the memory, determine whether the ignition was successful by monitoring the electrical signal produced by the thermal electric and/or photoelectric device, and adjust the information stored in the memory based on whether the ignition sequence completed successfully.

Method, machine, manufacture, composition of matter, article, and improvements thereto, with particular regard to chemically heated hot emitter electric generators, and support thereof. Illustratively, there can be a machine including: a first computer system including a digital computer operably associated with an input device, a memory, and an output device, the computer programmed to carry out operations including: receiving, as information input at said input device, input representing chemically heated hot emitter electromagnetic emissions; computing, from said input, output that can be used for, or to facilitate, operation of chemically heated hot emitter generators.

Method, machine, manufacture, composition of matter, article, and improvements thereto, with particular regard to chemically heated hot emitter electric generators, and support thereof. Illustratively, there can be a machine including: a first computer system including a digital computer operably associated with an input device, a memory, and an output device, the computer programmed to carry out operations including: receiving, as information input at said input device, input representing chemically heated hot emitter electromagnetic emissions; computing, from said input, output that can be used for, or to facilitate, operation of chemically heated hot emitter generators.