Abstract: A fuel nozzle for a gas turbine includes a first radial swirler and a second radial swirler that introduce radial swirl to a flow of pressurized air; a chevron splitter between the two swirlers that directs the swirled flow of pressurized air to a main mixer passage to form a fuel-air mixture with fuel injected into the fuel nozzle; and a main mixer passage that receives the fuel-air mixture from the premixing chamber, and includes a converging throat that accelerates the fuel-air mixture. A method of mixing fuel and air for combustion in a gas turbine includes introducing a radial swirl to first and second flows of pressurized air; directing the swirled, pressurized air to a premixing chamber via a chevron splitter; mixing the swirled, pressurized air with a fuel jet injected into the premixing chamber to form a fuel-air mixture; and accelerating the fuel-air mixture in the main mixer passage having a converging throat.

Abstract: In one embodiment, a system for reducing pressure oscillations within a gas turbine engine includes at least one fuel injector configured to inject fuel into a combustor. The system also includes a valve fluidly coupled to the at least one fuel injector. The system further includes a controller communicatively coupled to the valve. The controller is configured to cycle the valve between an open position and a closed position at a first frequency and a first duty cycle while a magnitude of pressure oscillations within the combustor is less than a threshold value, to cycle the valve between the open position and the closed position at a second frequency and a second duty cycle while the magnitude of the pressure oscillations within the combustor is greater than or equal to the threshold value, and to adjust the second frequency based on a measured frequency of the pressure oscillations.

Abstract: A combustor and a method for reducing a temperature gradient of a combustor component are provided. The combustor includes a coating applied to at least a portion thereof with the coating serving to alter the emissivity of the at least a portion to which it is applied. The method includes applying a coating on at least one of a combustor liner and a flow sleeve, wherein the coating alters the emissivity exhibited where applied.

Abstract: A corrugated cyclone mixer for use in a fuel injection assembly of a turbine engine. The corrugated cyclone mixer generally includes an annular housing including a flange portion and a lip portion configured downstream of the flange portion. The mixer further including a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer. The swirler is configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow. The lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end. The plurality of corrugations are configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer. Additionally disclosed is a fuel injection assembly and a turbine assembly including the corrugated cyclone mixer.

Abstract: A fuel injector to reduce NOx emissions in a combustor system. The fuel injector including a housing, at least one oxidizer flow path, extending axially through the fuel injector housing and defining therein one or more oxidizer flow paths for an oxidizer stream and a fuel manifold, extending axially through the fuel injector housing and defining therein one or more fuel flow path. The fuel manifold includes a forward portion and an aft portion including an aft face. A plurality of fuel injector outlets are defined in the aft portion, wherein the plurality of fuel injector outlets are configured to inject a fuel flow along a mid-plane of the fuel injector and away from a downstream wall. The fuel flow exiting the fuel manifold undergoes circumferential and radial mixing upon interaction with the oxidizer stream. Additionally disclosed is a combustor system including the fuel injector.

Abstract: A system for processing a gas stream includes a gathering subsystem configured to collect the gas stream from a well-head and a gas conditioning subsystem for receiving the gas stream from the gathering subsystem and providing physical conditioning of the gas stream. The system includes one or more gas turbines configured to receive and combust a first flow of the conditioned gas stream from the gas conditioning subsystem and coupled with an electrical generator. The system includes one supplemental combustor configured to receive heated exhaust gases from the one or more gas turbines and a second flow of the conditioned gas stream from the gas conditioning subsystem, wherein the at least one supplemental combustor is configured to combust the second flow of the conditioned gas stream and the heated exhaust gases such that an exhaust gas stream flow from the at least one supplemental combustor meets emission regulation requirements.

Abstract: A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOx exhaust gas stream, a heat recovery system configured to receive the low-NOx exhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and H2O deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.

Abstract: A system for controlling combustion dynamics is provided. The system includes a combustor having a combustion chamber and an inlet for feeding a fuel-air mixture into the combustion chamber. The system also includes a dome plate at an upstream end of the combustion chamber. The system further includes a liner along a length of the combustion chamber. The system also includes an actuator configured to control one or more recirculating zones in the combustion chamber.

Abstract: A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.

Abstract: A method of using a counterflow injection mechanism disposed in a combustion liner. The combustion liner including an outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets, an inner casing having a closed rear end and a combustion outlet, and an air circulation path extending between and along the inner and outer casings. The counterflow injection mechanism includes a fuel-air injection mechanism having fuel and air passages extending through the air circulation path and leading to fuel and air injection openings disposed at an off-center position. The method includes injecting fuel and air from the injection mechanism toward the closed rear end of the inner casing in a direction counterflow to a generally lengthwise downstream flow of combustion products in a gas turbine combustor.

Abstract: In one embodiment, a system for reducing pressure oscillations within a gas turbine engine includes at least one fuel injector configured to inject fuel into a combustor. The system also includes a valve fluidly coupled to the at least one fuel injector. The system further includes a controller communicatively coupled to the valve. The controller is configured to cycle the valve between an open position and a closed position at a first frequency and a first duty cycle while a magnitude of pressure oscillations within the combustor is less than a threshold value, to cycle the valve between the open position and the closed position at a second frequency and a second duty cycle while the magnitude of the pressure oscillations within the combustor is greater than or equal to the threshold value, and to adjust the second frequency based on a measured frequency of the pressure oscillations.

Abstract: The present application provides a secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine. The secondary combustion system may include a manifold ring and a number of injectors extending from the manifold ring. Each of the injectors may include a number of jets in communication with the manifold ring. One or more of the jets may include an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle.

Abstract: A combustor and a method for reducing a temperature gradient of a combustor component are provided. The combustor includes a coating applied to at least a portion thereof with the coating serving to alter the emissivity of the at least a portion to which it is applied. The method includes applying a coating on at least one of a combustor liner and a flow sleeve, wherein the coating alters the emissivity exhibited where applied.

Abstract: In accordance with certain embodiments, a system includes a counterflow injection mechanism. The counterflow injection mechanism includes a fuel-air injection mechanism having fuel and air passages leading to fuel and air injection openings, wherein the fuel and air injection openings are disposed at an off-center position and a generally counterflow direction relative to a generally lengthwise flow axis of a gas turbine combustor.

Abstract: The present application and the resultant patent provide a combustor for a turbine engine. The combustor may include a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly. The swirler assembly may include a number of stages with a number of fueled structures and a number of unfueled structures.

Abstract: A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range.

Abstract: A combustor nozzle is provided. The combustor nozzle includes a first fuel system configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fuel system configured to introduce the syngas fuel, or a hydrocarbon fuel, or diluents, or combinations thereof into the combustion chamber to enable diffusion combustion within the combustion chamber.

Abstract: A tunable fluid flow control system includes a fluidic oscillator having a movable boundary wall. A pressurized gas source is coupled to the movable boundary wall and configured to supply a stream of pressurized gas to the movable boundary wall to actuate the boundary wall. The boundary wall is actuatable to vary a cavity volume in the fluidic oscillator so as to control frequency of flow of a pulsating fluid generated by the fluidic oscillator. A portion of a fluid is bypassed the fluidic oscillator so as to control amplitude of flow of a pulsating fluid generated by the fluidic oscillator.

Abstract: A method for controlling combustion dynamics is provided. The method includes providing a flow of partially premixed, premixed, or lean premixed fuel-air into a combustion chamber. The method also includes monitoring the combustion system for combustion dynamics. The method further includes actuating a system to control and abate combustion dynamics.

Abstract: A gas turbine system includes a fuel reformer system comprising a fuel inlet configured to receive a fuel slipstream; an oxygen inlet configured to introduce an oxygen slipstream; a preconditioning zone configured to pretreat the fuel slipstream; a mixing zone comprising a premixing device configured to facilitate mixing of the fuel slipstream and the oxygen slipstream to form a gaseous premix; a reaction zone configured to generate a syngas from the gaseous premix; a quench zone configured to mix a fuel stream into the syngas to form a hydrogen-enriched fuel mixture; and a gas turbine configured to receive the fuel mixture.