Abstract: A combustor includes a combustion chamber that defines a longitudinal axis. A primary reaction zone is inside the combustion chamber, and a secondary reaction zone inside the combustion chamber is downstream from the primary reaction zone. A center fuel nozzle extends axially inside the combustion chamber to the secondary reaction zone, and a plurality of fluid injectors circumferentially are arranged inside the center fuel nozzle downstream from the primary reaction zone. Each fluid injector defines an additional longitudinal axis out of the center fuel nozzle that is substantially perpendicular to the longitudinal axis of the combustion chamber.

Abstract: A combustor nozzle includes an inlet surface and an outlet surface downstream from the inlet surface, wherein the outlet surface has an indented central portion. A plurality of fuel channels are arranged radially outward of the indented central portion, wherein the plurality of fuel channels extend through the outlet surface.

Abstract: A dual-fuel burning gas turbine combustor having a diffusive combustion burner to burn a liquid fuel and a gaseous fuel placed at the axis of the gas turbine combustor and a plurality of pre-mixing combustion burners to burn a liquid fuel and a gaseous fuel placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner having a liquid fuel nozzle, a plurality of gaseous fuel spray holes, a plurality of air holes, and a pre-mixing chamber to mix gaseous fuel and air, wherein each pre-mixing combustion burner has a double pipe sleeve at a connected portion between end cover and the pre-mixing combustion burner, and the double pipe sleeve has an inner sleeve having a gaseous fuel flow path, an outer sleeve positioned on an outer circumferential side of the inner sleeve, and a circular spacing formed between the inner sleeve and the outer sleeve.

Abstract: Methods and systems for low emission power generation in hydrocarbon recovery processes are provided. One system includes integrated pressure maintenance and miscible flood systems with low emission power generation. An alternative system provides for low emission power generation, carbon sequestration, enhanced oil recovery (EOR), or carbon dioxide sales using a hot gas expander and external combustor. Another alternative system provides for low emission power generation using a gas power turbine to compress air in the inlet compressor and generate power using hot carbon dioxide laden gas in the expander. Other efficiencies may be gained by incorporating heat cross-exchange, a desalination plant, co-generation, and other features.

Abstract: A system includes a mixing assembly configured to mix a liquid fuel and a water to generate a fuel mixture. The fuel mixture is configured to combust in a combustor of a gas turbine. The mixing assembly includes a liquid fuel passage disposed in an integrated housing. The liquid fuel passage is configured to flow the liquid fuel and to exclude liquid traps. The mixing assembly also includes a water passage disposed in the integrated housing. The water passage is configured to flow the water and to exclude liquid traps. The mixing assembly also includes a mixer disposed in the integrated housing and coupled to the liquid fuel passage and the water passage. The mixer is configured to mix the liquid fuel and the water to form the fuel mixture.

Abstract: The invention relates to a burner arrangement for using in a single combustion chamber or in a can-combustor comprising a center body burner located upstream of a combustion zone, an annular duct with a cross section area, intermediate lobes which are arranged in circumferential direction and in longitudinal direction of the center body. The lobes being actively connected to the cross section area of the annular duct, wherein a cooling air is guided through a number of pipes within the lobes to the center body and cools beforehand at least the front section of the center body based on impingement cooling. Subsequently, the impingement cooling air cools the middle and back face of the center body based on convective and/or effusion cooling. At least the back face of the center body includes on the inside at least one damper.

Abstract: Provided is a power plant including a gas turbine that uses a fuel gas as a fuel; a fuel gas cooler that cools the fuel gas, which is to be pressurized in a fuel gas compressor and re-circulated, using cooling water; and a dust collection device that separates/removes impurities from the fuel gas that is to be guided to the fuel gas compressor; wherein the power plant further includes heating means that heats the fuel gas that is to be guided to the dust collection device using the fuel gas that has been used to generate an anti-thrust force acting on a rotor of the fuel gas compressor.

Abstract: A turbomachine combustor assembly includes a combustor body, a combustion chamber defined within the combustor body, one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber, and a fuel start-up system fluidly connected to the combustion chamber. The fuel start-up system is configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel. A pilot nozzle is fluidly connected to the fuel start-up system. The pilot nozzle is configured and disposed to deliver an atomized cloud of the ignition fuel toward the combustion chamber.

Abstract: Fuel is oxidized with air in a pressurized reaction chamber containing water. Water, fuel, or both may be communicated into the reaction chamber in a gaseous state, a liquid state, or both. For example, a liquid mixture that includes the water and/or the fuel can be evaporated to form a gas mixture, and the gas mixture can be communicated into the reaction chamber. Additionally or alternatively, the liquid mixture that includes the water and/or the fuel can be communicated into the reaction chamber and evaporated in the reaction chamber. The water and the fuel may be communicated into the reaction chamber separately or in combination.

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 system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.

Abstract: Systems and methods for controlling fuel mixing are provided. One or more parameters associated with the operation of a machine configured to receive a combined fuel may be identified. A fuel flow of the combined fuel that is provided to the machine may be determined. Based at least in part on the identified parameters, a ratio of a first fuel type included in the combined fuel to the determined fuel flow may be determined. The first fuel type may have a heating value that is greater than a second fuel type included in the combined fuel. A flow of the first fuel type may be set based at least in part on the ratio. Subsequent to setting the flow of the first fuel type, an energy content of the fuel flow of the combined fuel may be determined, and the flow of the first fuel type may be adjusted based at least in part on the determined energy content.

Abstract: A gas turbine combustor includes a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame. The burner is provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction. A first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole. A swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole.

Abstract: A system for a gas turbine engine includes a combustor assembly coupled to a plurality of first nozzles having outlet passageways coupled to a first fuel source and first passageways coupled to a second fuel source. The system also includes the combustor assembly coupled to a second nozzle that has second passageways coupled to the second fuel source. An associated control system, coupled to the combustor assembly, is configured to channel a first fuel from the first fuel source through the outlet passageways, and channel a second fuel from the second fuel source through the second passageways when the engine attains a predetermined load. The control system is further configured to channel the second fuel from the second fuel source through the first passageways and to reduce a flow of the first fuel entering the first nozzles when the engine is at a load greater than a first predetermined load.

Abstract: A burner for a gas turbine engine is provided. The burner includes a radial swirler for creating a swirling fuel/air mix, a combustion chamber where combustion of the swirling fuel/air mix occurs, and a pre-chamber located between the radial swirler and the combustion chamber. The radial swirler includes a plurality of vanes arranged in a circle, generally radially inwardly extending flow slots are defined between adjacent vanes in the circle, each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, and a base and top. A flow slot includes a first gas fuel injection hole in its base and a flow slot includes a second gas fuel injection hole in its first side wherein the amounts of gas fuel injected via the first and second gas fuel injection holes are independently variable.

Abstract: When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end of a pilot injector barrel. Additional air is drawn into the first end of the pilot injector barrel from an enclosure containing both the first end of the pilot injector barrel and the tube outlet. Liquid pilot fuel is supplied at a second end of the pilot injector barrel, and this fuel is atomized by the flow of the air assist and additional air.

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 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 fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, 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 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: 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: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, 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: A plant (100) for the gasification of biomass comprises a gasifier (10) and an apparatus (23) for the filtration of the gas. The apparatus comprises a scrubber (31), a tank (41), and a wet electrostatic precipitator (51). The scrubber is in fluid communication with the gasifier and with the tank, and is adapted for the injection of a washing liquid in the gas flow. The tank comprises a bottom area for collecting the liquid and a top area for holding the gas. The wet electrostatic precipitator is in fluid communication with the top area of the tank. In some examples, a gasifier comprises a gasification reactor (12), a grate (125) for the support of the biomass in the reactor (12) and a plug (126). The plug is vertically movable so as to close and/or open the middle part of the grate.

Abstract: A gas turbine engine is provided and includes a 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, 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, and a control system coupled to the fuel circuit and configured to control relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.

Abstract: A system, including a turbine fluid supply system, including a fuel supply assembly, including a first fuel supply configured to supply a first fuel to a gas turbine engine; and a second fuel supply configured to supply a second fuel to the gas turbine engine, wherein the first fuel has a greater carbon content than the second fuel, and a diluent supply assembly comprising at least one diluent supply configured to supply at least one diluent to the gas turbine engine; and a controller having instructions to control the first fuel supply, the second fuel supply, or the at least one diluent supply to adjust a percentage of carbon in a combustor of the gas turbine engine to maintain a ratio of carbonaceous emissions in an exhaust gas per unit of energy produced by the gas turbine engine at or below a threshold ratio.

Abstract: A gas turbine combustor includes a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction. A first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole. A swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole.

Abstract: A fuel injector (36) for alternate fuels (26A, 26B) with different energy densities. Vanes (47B) extend radially from a fuel delivery tube structure (20B) with first and second fuel supply channels (19A, 19B). Each vane has first and second radial passages (21A, 21B) communicating with the respective fuel supply channels, and first and second sets of apertures (23A, 23B). The first fuel supply channel, first radial passage, and first apertures form a first fuel delivery pathway providing a first fuel flow rate at a given fuel delivery pathway backpressure that is essentially common to both sets of fuel delivery pathway apertures. The second fuel supply channel, second radial passage, and second apertures form a second fuel delivery pathway providing a second fuel flow rate that may be at least 1 about twice the first fuel flow rate at the given fuel delivery pathway backpressure.

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: According to various embodiments, a system includes a fuel controller configured to control a fuel transition between a first flow of a first fuel and a second flow of a second fuel into a fuel nozzle of a combustion system. The fuel controller is configured to adjust a third flow of a diluent in combination with the second flow of the second fuel to maintain a pressure ratio across the fuel nozzle above a predetermined operating pressure ratio.

Abstract: Methods and systems are provided for premixing combustion fuel and air within gas turbines. In one embodiment, a combustor includes an upstream mixing panel configured to direct compressed air and combustion fuel through a premixing zone to form a fuel-air mixture. The combustor also includes a downstream mixing panel configured to mix additional combustion fuel with the fuel-air mixture to form a combustion mixture.

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.

Abstract: An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen.

Abstract: The present application provides a combustor for combusting a number of flows of air and a number of flows of fuel. The combustor may include a central swirler for producing a high swirl quench air flow, a number of trapped vortex cavities surrounding the central swirler for producing a flow of combustion gases, a brief severe quench zone downstream of the trapped vortex cavities to quench the flow of combustion gases between an outer quench air flow and the high swirl quench air flow, and an expansion zone downstream of the brief severe quench zone.

Abstract: A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.

Abstract: A fuel injector includes a flow path for fuel air mixture to a combustor extending longitudinally through the fuel injector. The fuel injector may also include a liquid fuel gallery at least partially encircling the flow path. The gallery may include a plurality of fuel spokes configured to deliver liquid fuel from the gallery to the flow path. The fuel injector may also include an annular outer housing circumferentially positioned about the gallery to form an insulating air cavity at least partially around the gallery. The outer housing may include at least one purge hole to provide communication between the insulating air cavity and outside the outer housing of the injector.

Abstract: A combustor includes a combustion chamber that defines a longitudinal axis. A primary reaction zone is inside the combustion chamber, and a secondary reaction zone inside the combustion chamber is downstream from the primary reaction zone. A center fuel nozzle extends axially inside the combustion chamber to the secondary reaction zone, and a plurality of fluid injectors circumferentially are arranged inside the center fuel nozzle downstream from the primary reaction zone. Each fluid injector defines an additional longitudinal axis out of the center fuel nozzle that is substantially perpendicular to the longitudinal axis of the combustion chamber.

Abstract: An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base (11), and the main nozzles each have an oil fuel path for supplying oil fuel and a gas fuel path for supplying gas fuel. A plurality of the oil fuel paths are provided to penetrate the nozzle pipe base (11), and a plurality of lengths of upright piping (21) are provided to be connected to the oil fuel paths, respectively, and be erected on the nozzle pipe base (11). A plurality of lengths of connection piping (22) for interconnecting the lengths of the upright piping (21) in a polygonal shape at a minimum distance are provided outside the nozzle pipe base (11). An oil fuel supply section (14) is connected to one of the lengths of the connection piping (22) to distribute oil fuel to each of the oil fuel paths.

Abstract: A chemical reactor comprises a flow channel, a source, and a destination. The flow channel is configured to house at least one catalytic reaction converting at least a portion of a first nanofluid entering the channel into a second nanofluid exiting the channel. The flow channel includes at least one turbulating flow channel element disposed axially along at least a portion of the flow channel. A plurality of catalytic nanoparticles is dispersed in the first nanofluid and configured to catalytically react the at least one first chemical reactant into the at least one second chemical reaction product in the flow channel.

Abstract: A gas turbine engine configured to operate using a liquid fuel and a gaseous fuel may include a combustor system fluidly coupled to a compressor system and a turbine system. The gas turbine engine may also include a control system configured to selectively direct the gaseous fuel and the liquid fuel to the combustor system based on a concentration of a constituent in the gaseous fuel.

Abstract: Embodiments of the present application include a combustor assembly. The combustor assembly may include a combustion chamber, a first plenum, a second plenum, and one or more elongate air/fuel premixing injection tubes. Each of the elongate air/fuel premixing injection tubes may include a first length at least partially disposed within the first plenum and configured to receive a first fluid from the first plenum. Moreover, each of the elongate air/fuel premixing injection tubes may include a second length disposed downstream of the first length and at least partially disposed within the second plenum. The second length may be formed of a porous wall configured to allow a second fluid from the second plenum to enter the second length and create a boundary layer about the porous wall.

Abstract: A dual fuel engine control system comprising a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine, and a second fuel control system configured to control the flow of a second fuel to the aircraft gas turbine engine.

Abstract: A fuel delivery system for a gas turbine designed to efficiently transfer from one type of fuel to a separate fuel, comprising different and cooperating fuel modules, namely high hydrogen fuel gas, distillate fuel and naphtha fuel modules, each of which feeds a different liquid or gas fuel to the combustors, an atomized air delivery system for either the naphtha or distillate (or combinations thereof), an air extraction system, a plurality of distribution control valves for the high hydrogen fuel gas, distillate fuel and naphtha fuel modules, and a nitrogen purge system to purge the high hydrogen fuel gas lines to the combustors and/or flushing the naphtha lines with distillate.

Abstract: A method and apparatus to determine a first heating value of a low BTU fuel, determine a target fuel quality level based on a state of a turbine system, control a second heating value of a high BTU fuel, and inject the high BTU fuel into the low BTU fuel to achieve the target fuel quality level.

Abstract: A system includes a multi-fuel gas turbine configured to operate on both a liquid fuel system and a gas fuel system, wherein the multi-fuel gas turbine comprises a compressor, a combustor, and a turbine. The system also includes a gas fuel purge system configured to purge a gas fuel circuit of the gas fuel system during liquid fuel operation of the gas turbine, wherein the gas fuel purge system is configured to sequentially purge the gas fuel circuit with air and steam.

Abstract: The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The dual gas fuel delivery system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, and wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold.

Abstract: A turbomachine is provided and includes a compressor to compress inlet gas to produce compressed gas, a combustor coupled to the compressor in which the compressed gas is combusted along with a first fuel and/or a second fuel to produce a fluid flow, a turbine coupled to the combustor through which the fluid flow is directed for power and/or electricity generation and first and second supply circuits to supply the first fuel and the second fuel to the combustor, respectively. The first and second supply circuits are operable to enable transfers between operations associated with the first fuel and the second fuel being respectively supplied to the combustor at a high load.

Abstract: The invention provides a gas-turbine fuel nozzle (1) that includes a plurality of fuel supply channels (3a) to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels (3b) to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes (7a, 7b) that are provided at downstream ends of the fuel supply channels (3a) or the fuel/scavenging-fluid supply channels (3b) and that inject the fuel guided from the fuel supply channels (3a) or the fuel/scavenging-fluid supply channels (3b); a scavenging-fluid supply channel (21) that is connected to the fuel/scavenging-fluid supply channels (3b) to guide the scavenging fluid; and scavenging-fluid cooling means (23) for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel.

Abstract: In method for operating a gas turbine (11), the compressed air is fed to a combustor (18, 19) for the combustion of a coal syngas, and the resulting hot gases are expanded in a subsequent turbine (16, 17). Some of the compressed air is separated into oxygen and nitrogen, and the oxygen is used for producing the syngas. In a first combustor, (18) syngas is combusted and the resulting hot gases are expanded in a first turbine (16), and in a second combustor syngas is combusted, using the gases which issue from the first turbine (16), and the resulting hot gases are expanded in the second turbine (17). The two combustors (18, 19) are operated with undiluted syngas, and the first combustor flame temperature (TF) is lowered compared with the operation with natural gas (TNG), while the second combustor (19) is operated in the normal operation (TNG) for natural gas.

Abstract: The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold, and wherein the low energy gas delivery system further comprises a primary low energy gas stop and pressure control valve between the gas split and the low energy gas primary manifold outlet.

Abstract: A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit. Also in first phase steam is also supplied to the first conduit in addition to the first type of fuel and steam is supplied to the second conduit after the ignition. In the second phase a second type of fuel is supplied to the combustor basket through the second conduit after ignition of the first fuel through the first conduit, while stopping the supply of the first fuel, and continuing to supply steam through both the first and second conduits.

Abstract: A dual fuel combustor nozzle includes a body member including a first end portion that extends to a second end portion through an intermediate portion. The intermediate portion includes an outer wall portion and an inner wall portion with the inner wall portion defining a first fuel plenum. The dual fuel nozzle also includes an inner nozzle member arranged within the first fuel plenum. The inner nozzle member includes a first end section that extends to a second end section through an intermediate section. The intermediate section defines a second fuel plenum. The second end section being spaced from the second end portion of the body member so as to define a pre-emergence zone.