Abstract: A fuel injector assembly for a combustor including an axially staged fuel injector includes an injector body having an inner wall and a boss that is rigidly connected to the injector body the boss includes an inner wall. The inner wall of the boss and the inner wall of the injector body together define a flow passage of the fuel injector assembly. The injector body defines an inlet to the flow passage and the boss defines an outlet of the flow passage.

Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.

Abstract: A fuel injector assembly for a combustor including an axially staged fuel injector includes an injector body having an inner wall and a boss that is rigidly connected to the injector body the boss includes an inner wall. The inner wall of the boss and the inner wall of the injector body together define a flow passage of the fuel injector assembly. The injector body defines an inlet to the flow passage and the boss defines an outlet of the flow passage.

Abstract: A fuel injector assembly includes a shroud defining a fuel manifold therein. The fuel manifold is fluidly coupled to a fuel line to receive a fuel therefrom. The fuel injector assembly further includes a center body and a plurality of vanes operatively coupling the center body to the shroud. Each vane of the plurality of vanes is circumferentially spaced from circumferentially adjacent vanes to define at least one passage therebetween for routing of air therethrough. Each of the plurality of vanes has at least one outlet hole in fluid communication with the fuel manifold and at least one passage of the at least one passage for expulsion of the fuel into the at least one passage for mixing with the air. A fuel injector outlet is defined by an inner wall of the fuel injector assembly and positioned to direct a fuel-air mixture out of the fuel injector assembly.

Abstract: A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes and the second radial passage has a second plurality of swirler vanes. The first radial passage is in fluid communication with the outer flow passage and the second radial passage is in fluid communication with the inner flow passage.

Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.

Abstract: An exhaust gas recirculation system that includes an exhaust gas recirculation regulator operatively connectable to a turbomachine system, and regulating a predetermined amount of exhaust gas to be recirculated. The exhaust gas recirculation system further includes a measuring unit that measures fuel composition of incoming fuel, and a control unit connected to the EGR regulator and the measuring unit, and determining a Wobbe Index and/or reactivity of the incoming fuel based on the measured fuel composition and determining the predetermined amount of exhaust gas to be recirculated based on the determined Wobbe Index and/or reactivity.

Abstract: A gas turbine engine having a combustor that includes: an inner radial wall defining axially stacked first and second interior chambers, wherein the first interior chamber extends axially from an end cover to a fuel nozzle, and the second interior chamber extends axially from the fuel nozzle to an inlet of the turbine; and an outer radial wall formed about the inner radial wall so to form a flow annulus therebetween. The flow annulus may include a flow conditioning section that has: conditioning passages defined therethrough for directing a flow from inlets formed at an upstream end to outlets formed at a downstream end of the flow conditioning section; and structure rigidly attaching the inner radial wall to the outer radial wall.

Abstract: A combustor includes a plurality of tubes arranged in a tube bundle and supported by at least one plate that extends radially within the combustor, wherein each tube includes an upstream end axially separated from a downstream end and provides fluid communication through the tube bundle. A flow conditioner extends upstream from the upstream end of one or more of the plurality of tubes, and a radial passage extends through the flow conditioner. A method for distributing fuel in a combustor including flowing a working fluid through a flow conditioner that extends from a tube that is configured in a tube bundle comprising a plurality of tubes and that is supported by at least one plate. The flow conditioner includes at least one radial passage to impart radial swirl to the working fluid. Flowing a fuel through an annular insert that is at least partially surrounded by the flow conditioner.

Abstract: A method for operating a catalytic reforming assembly. The method includes injecting a quantity of oxidizer gas and a quantity of combustion gas into a reformer to form a mixture. The mixture is channeled across a catalyst bed to form a reformate gas stream. A temperature of the catalyst bed is measured using at least one temperature sensor. A level of the oxidizer gas in the reformate stream is measured using at least one oxidizer gas sensor. A health of the catalyst bed is determined based on at least one of a catalyst bed temperature measurement and an oxidizer gas level.

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 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: A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes and the second radial passage has a second plurality of swirler vanes. The first radial passage is in fluid communication with the outer flow passage and the second radial passage is in fluid communication with the inner flow passage.

Abstract: A system for supplying fuel to a combustor includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber. A plurality of fuel nozzles are radially arranged across the combustor upstream from the combustion chamber to supply a swirling flow of fuel into the combustion chamber. A first fuel injector downstream from the plurality of fuel nozzles provides fluid communication for fuel to flow through the liner and into the combustion chamber. The first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber.

Abstract: In one aspect, a combustion system is configured to facilitate preventing the formation of vanadium pentoxide (V2O5) and decrease a concentration of at least one of vanadium trioxide (V2O3) and vanadium tetroxide (V2O4) particles in an exhaust. The combustion system includes a vanadium-containing fuel supply and a combustor. The combustor is configured to generate a combustor exhaust gas including vanadium trioxide (V2O3) and/or vanadium tetroxide (V2O4) particles and to combust a reduced-oxygen mixture including the vanadium-containing fuel, ambient air, and a portion of the combustor exhaust gas. The combustion system also includes a particle separator configured to remove substantially all of the V2O3 and/or V2O4 particles from the combustor exhaust gas. A method for combusting fuel and a power generation system are also provided.

Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

Abstract: A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

Abstract: In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.

Abstract: A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.

Abstract: A combustor including a combustion nozzle. The combustion nozzle includes a mixing section and an exit section. The mixing section includes an air inlet, and a fuel inlet. The exit section includes a plurality of jets on an exit surface. The combustor further includes a combustion zone, including a combustion liner, disposed downstream and in fluidic communication with the combustion nozzle. The combustor is configured wherein a, NOx emission of the combustor is related to 1/R, where R is a Reynolds number ratio of a jet of the plurality of jets to the combustion liner. A method for achieving NOx reduction in a combustion nozzle.