Abstract: An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor.

Abstract: Certain embodiments include a first individual sector having a first outer perimeter configured to fit together with outer perimeters of a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector comprises a first inner perimeter configured to fit about a nozzle outer perimeter of a first fuel nozzle, and the first individual sector is configured to fixedly attach to the first fuel nozzle.

Abstract: A starting injector usable in all flight modes without additional cost or weight. The starting injector includes a dual fuel circuit and an air circuit. An injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit including a starting fuel circuit for ignition and then for all the flight modes, and a main fuel circuit for all the flight modes after starting. The circuits include parallel pipes in a common tube having an axis. The pipe of the starting circuit is substantially in communication with a center of a spherical injector body. At the end, the pipe accommodates an injection manifold coupled to a central channel passing through a central wall of a swirler. The pipe of the main circuit is in communication with an annular channel opposite jet channels. An air circuit is guided between two portions shaped as concentric spheres.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. A plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the flow sleeve and into the distribution manifold provides fluid communication through the flow sleeve to the plurality of fuel injectors.

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 system for supplying fuel to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for a working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube includes a tube wall. A plurality of fuel ports through the tube wall provide fluid communication for fuel to flow through the tube wall and into the tube, and the fuel ports are non-circular.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. Injectors circumferentially arranged around the flow sleeve provide fluid communication through the flow sleeve and into the combustion chamber. A valve upstream from the injectors has a first position that permits working fluid flow to the injectors and a second position that prevents working fluid flow to the injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through injectors circumferentially arranged around the combustion chamber, and operating a valve upstream from the injectors to control the working fluid flow through the injectors.

Abstract: A power plant configured to include a recirculation loop about which a working fluid is recirculated. The recirculation loop may include a plurality of components configured to accept an outflow of working fluid from a neighboring upstream component and provide an inflow of working fluid to a neighboring downstream component. The recirculation loop may include: a recirculation compressor; an upstream combustor; a high-pressure turbine; a downstream combustor; a low-pressure turbine; and a recirculation conduit configured to direct the outflow of working fluid from the low-pressure turbine to the recirculation compressor. The power plant further may include: an oxidant compressor configured to provide compressed oxidant to one of the upstream combustor and the downstream combustor; and means for extracting a portion of the working fluid from an extraction point disposed at a predetermined location on the recirculation loop.

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: The present invention provides a system and method of operating a combined-cycle powerplant at part-load without shutting down an HRSG and steam turbine. The present invention may apply to a powerplant operating in an open-cycle mode. The present invention may also apply to a powerplant operating in a closed-cycle mode.

Abstract: The present invention provides a system and method that yields an exhaust stream that includes a relatively high concentration of a desirable gas and is also substantially oxygen-free. This desirable gas includes, but is not limited to: Carbon Dioxide (CO2), Nitrogen (N2), or Argon. The present invention also provides a way to control the physical property of the exhaust stream.

Abstract: A power plant configured to include a recirculation loop about which a working fluid is recirculated, the recirculation loop comprising a plurality of components configured to accept an outflow of working fluid from a neighboring upstream component and provide an inflow of working fluid to a neighboring downstream component. The recirculation loop may include: a recirculation compressor; an upstream combustor; a high-pressure turbine; a downstream combustor; a low-pressure turbine; and a recirculation conduit configured to direct the outflow of working fluid from the low-pressure turbine to the recirculation compressor. The power plant may include: an oxidant compressor configured to provide compressed oxidant to both the upstream combustor and the downstream combustor; and means for extracting a portion of the working fluid from an extraction point disposed on the recirculation loop.

Abstract: Embodiments of the present invention provide to a cooling and sealing air system for reheat gas turbine powerplant operating in a configuration that includes stoichiometric exhaust gas recirculation configuration. A user may have the flexibility in determining where the cooling and sealing flow derives. This may include and enhanced oil recovery system, a concentrated carbon system, etc.

Abstract: A combustion device includes: a combustion liner in which a combustion chamber is formed; a main burner provided at a top portion of the combustion liner and including a premix passage configured to annularly inject a pre-mixed gas of a fuel and air into the combustion chamber and a radial swirler configured to introduce the fuel and the air to the premix passage in a radially inward direction; and a fuel injection pipe configured to inject the fuel to the radial swirler from an entrance side of the radial swirler, and the radial swirler is divided into a plurality of swirler stages by dividing plates in an axial direction.

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 system for supporting fuel nozzles inside a combustor includes a ring that circumferentially surrounds the fuel nozzles inside the combustor, a support plate that extends radially inside at least a portion of the ring, and a first connection between the support plate and at least one of the fuel nozzles inside the combustor. A second connection is between the support plate and the ring. A method for supporting fuel nozzles in a combustor includes surrounding the fuel nozzles with a ring, connecting a support plate to the ring, and connecting the support plate to at least one fuel nozzle.

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 fuel/air mixing tube for use in a fuel/air mixing tube bundle is provided. The fuel/air mixing tube includes an outer tube wall extending axially along a tube axis between an inlet end and an exit end, the outer tube wall having a thickness extending between an inner tube surface having a inner diameter and an outer tube surface having an outer tube diameter. The tube further includes at least one fuel injection hole having a fuel injection hole diameter extending through the outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back.

Abstract: A nozzle includes a center body that defines an axial centerline. A shroud circumferentially surrounds at least a portion of the center body to define an annular passage between the center body and the shroud. A plenum is inside the center body and substantially parallel to the axial centerline, and an igniter is inside the center body and generally adjacent to the plenum. A method for igniting a combustor includes flowing a fuel through a center body axially aligned in a nozzle and flowing a working fluid through an annular passage, wherein the annular passage is substantially parallel to and radially outward of the center body. The method further includes projecting at least one of a beam, spark, or flame from an igniter located inside the center body.

Abstract: A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.

Abstract: An injection system for fuel and air that includes a number of lobes positioned adjacent to each other. Each of the lobes has a trailing end. A number of jets may be positioned adjacent to the trailing end.

Abstract: A fuel nozzle for use with a turbine engine is provided. The fuel nozzle includes a housing coupled to a combustor liner defining a combustion chamber. The housing is at least partially positioned within an air plenum and comprises an endwall that at least partially defines the air plenum. The fuel nozzle includes a plurality of mixing tubes extending through the housing for channeling a fuel to the combustion chamber, a cooling fluid plenum at least partially defined within the housing by the housing endwall, and a plurality of apertures defined within the housing endwall for channeling a cooling fluid from the cooling fluid plenum to the air plenum.

Abstract: A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.

Abstract: A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times the nozzle is in operation. There is no need for a supply of compressed purge air.

Abstract: Disclosed is a combustion system for a gas turbine engine, which includes a combustor and a plurality of fuel injector nozzles within the combustor. The plurality of fuel injector nozzles include at least one start nozzle and at least of run nozzle, wherein each of the plurality of fuel injector nozzles is a single-circuit fuel injector nozzle. The combustion system further includes a fuel flow directing system to selectively deliver fuel flow to each of the at least one start nozzle and at least one run nozzle, wherein the fuel flow directing system is configured to deliver preferential flow of fuel to the at least one start nozzle during an engine start-up procedure and is further configured to deliver an equalized flow both of the at least one start nozzle and the at least one run nozzle as a total engine fuel flow is near or above an idle setting.

Abstract: It is described a combustion device control unit and a combustion device, e.g. a gas turbine, which determine on the basis of at least one operating parameter whether the combustion device is in a predefined operating stage. In response hereto, there is generated a control signal configured for setting a ratio of at least two different input fuel flows to a predetermined value (psc1, psc3) for a predetermined time (dt) in case the combustion device is in the predefined operating stage.

Abstract: A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes.

Abstract: A combustion apparatus (10) incorporating a dry low NOx (DLN) combustor (20) that uses two different fuels (30, 40) simultaneously. One fuel (30) is premixed with air (22) for a primary combustion zone (25), and a second fuel (40) supplies a diffusion pilot flame (29). Each fuel may be selected for its specialized role, maximizing overall combustion efficiency while lowering emissions. A primary fuel (30) such as natural gas (NG) may be chosen for its economy and combustion characteristics in a lean premix. A pilot fuel (40) may be chosen for having a low diffusion flame temperature and a clean burn. An oxygenated pilot fuel such as dimethyl ether (DME) has a lower flame temperature than natural gas, thereby reducing NOx from the pilot flame. The pilot fuel (40) may be produced from the primary fuel (30) by a reformer (50) associated with the combustion apparatus.

Abstract: The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes.

Abstract: Provided is a nozzle tip assembly having at least one tube member housed within a tubular shell, the tube member having a first passage connecting the first outlet port to the first inlet port and a second passage connecting the second outlet port to the second inlet port. The configuration of the tube member allows the tubular shell to be sized such that separation of fluid flowing around the tubular shell is reduced, thereby reducing the amount of aerodynamic wake that occurs in an injector.

Abstract: A flow balancing valve for a multistage combustor includes a first pressure feedback line, a first burn line, and a first metering port fluidly connected to the first fuel injector. The flow balancing valve further includes a second pressure feedback line, a second burn line, and a second metering port fluidly connected to the second fuel injector. A metering land is located between and defines sizes of the first metering port and the second metering port. An increase in pressure differential between the first pressure feedback line and the second pressure feedback line causes a compensatory movement in the metering land to balance fuel flow for the first fuel injector and the second fuel injector.

Abstract: A gas turbine combustor has a chamber supplied with fuel and air and a multi-burner having a plurality of burners provided with an air hole plate having a plurality of air holes, and fuel nozzles for supplying fuel to the air holes in the air hole plate; the multi-burner is made up of a center burner disposed in the center and a plurality of outer burners around the center burner, the outer burners are divided into inner fuel nozzles and outer fuel nozzles to separately supply fuel through fuel systems, and the fuel is supplied to the fuel nozzles in the center burner or to the fuel nozzles in the center burner and the inner fuel nozzles in the outer burners disposed around the center burner in a partial load condition in which the load is lower than that of when all the fuel systems are used to supply fuel.

Abstract: A fuel injector system for a turbine engine may include a center body disposed about a longitudinal axis and a barrel housing positioned radially outwardly from the center body to define an annular passageway therebetween. The fuel injector may also include one or more fuel discharge outlets positioned in the annular passageway. The one or more fuel discharge outlets may be configured to discharge pulses of a fuel into the annular passageway. The fuel injector may further include one or more fluidic oscillators fluidly coupled to the one or more fuel discharge outlets. The one or more fluidic oscillators may be configured to induce pulsations in the fuel discharged by the one or more fuel discharge outlets.

Abstract: A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle receptacles. Moreover, each segment of the plurality of segments does not completely surrounding any one fuel nozzle receptacle.

Abstract: A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.

Abstract: The disclosure relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, wherein the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area.

Abstract: An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection system. Heat protection deflectors are fastened to the chamber end wall. Holes are formed through the chamber end wall to pass cooling air onto an upstream face of each deflector. The inner or outer edge of a deflector presents a sealing rim engaging the respective inner or outer wall of the chamber.

Abstract: A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct.

Abstract: A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and a plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the distribution manifold provides fluid communication through the distribution manifold to the plurality of fuel injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber and diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds a plurality of fuel injectors circumferentially arranged around the combustion chamber.

Abstract: A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.

Abstract: A fuel nozzle for a turbine engine includes a primary fuel passageway for supplying fuel to a plurality of radially extending fuel injectors arranged around the exterior of the fuel nozzle. A secondary fuel passageway couples an upstream end of the primary fuel passageway to a downstream end of the primary fuel passageway. The secondary fuel passageway acts as a resonator tube to help reduce oscillations in the fuel flowing through the primary fuel passageway.

Abstract: An object of this invention is to suppress adhesion of a flame to periphery of air hole outlets arranged on an air hole plate. A combustor includes a fuel nozzle for jetting out a fuel into a combustion chamber formed at a downstream side; an air hole plate of a flat-plate shape disposed between the fuel nozzle and the chamber, the air hole plate facing an upstream side of the chamber; and a plurality of air holes provided in the air hole plate, in a circumferential direction relative to a central axis of the air hole plate, such that a fuel flow and an air flow formed at an outer circumferential side of the fuel flow are blown out into the chamber from the respective air holes; wherein a clearance defined between any two circumferentially adjacent air hole inlets provided on a face of the air hole plate that is nearer to the fuel nozzle is wider than a clearance defined between any two circumferentially adjacent air hole outlets formed on a face of the air hole plate that is nearer to the chamber.

Abstract: A nozzle assembly (10) comprising a first inlet tube (14), a second inlet tube (15), and a nozzle (16). The nozzle (16) is formed from a stack of plates (20-38) which are joined together in face-to-face contact. The plates (20-38) collectively have openings which define a nozzle outlet, a first inlet, a second inlet, a first circuit from the first inlet to the nozzle outlet, a second circuit from the second inlet to the nozzle outlet, and a fluid-outlet chamber through which both the first circuit and the second circuit pass. The nozzle assembly (10) can be used as a fuel injector for a gas turbine engine, with jet fuel being supplied to the first circuit during start-up and low power conditions and jet fuel being supplied to both the first circuit and the second circuit during high power conditions.

Abstract: A trapped vortex combustor includes a trapped vortex cavity having a first surface and a second surface. A plurality of fluidic mixers are disposed circumferentially along the first surface and the second surface of the trapped vortex cavity. At least one fluidic mixer includes a first open end receiving a first fluid stream, a coanda profile in the proximity of the first open end, a fuel plenum to discharge a fuel stream over the coanda profile, and a second open end for receiving the mixture of the first fluid stream and the fuel stream and discharging the mixture of the first fluid stream and the fuel stream in the trapped vortex cavity. The coanda profile is configured to enable attachment of the fuel stream to the coanda profile to form a boundary layer of the fuel stream and, to entrain the incoming first fluid stream to the boundary layer of the fuel stream to form a mixture of the first fluid stream and the fuel stream.

Abstract: A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage having a plurality of fuel injection bores distributed in a liner wall defining the respective stage. Valves at the fuel injection bores of one of the combustion stages, the valves each defining an air passage from an exterior to an interior of the combustion stage, the valves each having an actuatable member for adjusting a size of a respective air passage for air staging the combustor.

Abstract: A premixer is provided and includes a peripheral wall defining a mixing chamber therein through which a flow path for a fluid is defined, a nozzle including an annular splitter plate disposed in the flow path within the mixing chamber, the splitter plate including a trailing edge defined in relation to a predominant direction of fluid flow along the flow path and being formed to define a fuel line therein, which is receptive of oil fuel and an annular array of fuel injectors disposed at the trailing edge, which are each fluidly communicative with the fuel line and configured to inject at least the oil fuel into the flow path with the oil fuel being substantially atomized upon injection or substantially immediately after the injection by interaction with the fluid flowing along the flow path.

Abstract: A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.

Abstract: A turbomachine combustor assembly includes a combustor housing, a first combustion zone arranged in the combustor housing, a second combustion zone arranged downstream from the first combustion zone, and one or more injector assemblies positioned downstream from the first combustion zone and upstream from the second combustion zone. The one or more injector assemblies includes a first injector member having a first centerline axis and a second injector member having a second centerline axis. The second injector member extends though the first injector member with the second centerline axis being off-set from the first centerline axis.

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.