Abstract: The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.

Abstract: A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.

Abstract: A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes.

Abstract: A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow.

Abstract: An endcover for a turbine combustor adapted to support one or more combustor nozzles, includes a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel cavity is formed in the plate; and a fuel restrictor insert is formed with at least one flow orifice located within the fuel cavity for supplying fuel to at least one combustor nozzle. The fuel restrictor insert is adjustable along a length dimension of the fuel cavity.

Abstract: A control system for use with a turbine engine that is configured to operate at a rated power output is provided. The control system includes a computing device that includes a processor that is programmed to calculate an amount of fluid to be supplied for combustion in the turbine engine. The processor is also programmed to designate at least one nozzle of a plurality of nozzles to receive the fluid. Moreover, the control system includes at least one control valve coupled to the computing device. The control valve is configured to receive at least one control parameter from the computing device for use in modulating the amount of the fluid to be channeled to the nozzle such that the rated power output is generated while emission levels are maintained below a predefined emissions threshold level.

Abstract: A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.

Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

Abstract: A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events.

Abstract: A reformer for use in a gas turbine engine specially configured to treat a supplemental fuel feed to the combustor that includes a reformer core containing a catalyst composition and an inlet flow channel for transporting the reformer fuel mixture, air and steam (either saturated or superheated) into a reformer core. An outlet flow channel transports the resulting reformate stream containing reformed and thermally cracked hydrocarbons and substantial amounts of hydrogen out of the reformer core for later combination with the main combustor feed. Because the catalytic partial oxidation reaction in the reformer is highly exothermic, the additional heat is transferred (and thermally integrated) using one or more heat exchange units for a first and/or second auxiliary gas turbine fuel stream that undergo thermal cracking and vaporization before combining with the reformate. The combined, hydrogen-enriched feed significantly improves combustor performance.

Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure.

Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.

Abstract: The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.

Abstract: A turbomachine system includes a compressor portion having a compressor inlet and a compressor outlet, a turbine portion operatively connected to the compressor portion, a combustor having a combustor inlet fluidly connected to the compressor outlet and a combustor outlet fluidly connected to the turbine portion; and a reformer having a reformer inlet fluidly connected to the compressor outlet and a reformer outlet fluidly connected to the combustor inlet. The reformer partially combusts air from the compressor portion and a fuel to form a hydrogen-rich syngas.

Abstract: The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.

Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.

Abstract: A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes.

Abstract: Disclosed is a method of operating a secondary fuel nozzle for a turbomachine combustor including delivering a flow of pilot fuel through a pilot fuel channel toward a combustion zone and delivering a flow of air through a plurality of transfer passages arranged around the pilot fuel channel toward the combustion zone. The flow of pilot fuel and the flow of air are combusted in the combustion zone, and a flow of transfer fuel is delivered through the plurality of transfer passages for combustion. A secondary fuel nozzle includes a pilot fuel channel extending along the fuel nozzle to deliver a flow of pilot fuel to a combustion zone. A plurality of transfer passages are arranged around the pilot fuel channel and are configured to deliver a flow of air for combustion with the flow of pilot fuel and to deliver a flow of transfer fuel to the combustion zone.

Abstract: Systems and methods for controlling fuel flow within a machine are provided. A plurality of fuel types provided to the machine and a plurality of fuel circuits associated with the machine may be identified, each of the plurality of fuel circuits adapted to be provided with one or more of the plurality of fuel types. A fuel flow parameter for calculating fuel flow may be identified, and a respective fuel flow for each of the one or more fuel types provided to each of the plurality of fuel circuits may be calculated based at least in part on the identified fuel flow parameter. Based at least in part on the calculation of the respective fuel flows, operation of one or more fuel flow control devices providing fuel to the plurality of fuel circuits may be controlled.

Abstract: A combustor may include a number of nozzles, a first fuel source with a low reactivity fuel therein, a second fuel source with a high reactivity fuel therein, and a primary valve for varying the flow of the low reactivity fuel and the high reactivity fuel delivered to the nozzles.