Abstract: A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube.

Abstract: An annular fluid distribution device (20) for distributing fluid into a gaseous flow (14), that includes: a first fluid distribution manifold (30) having a first fluid inlet and first fluid outlets (24), wherein the first fluid outlets inject a first fluid into the gaseous flow; and a second fluid distribution manifold (32), having a second fluid inlet and second fluid outlets (26), wherein the second fluid outlets inject a second fluid into the gaseous flow. The second fluid manifold is isolated from the first fluid distribution manifold, and the first fluid outlets and the second fluid outlets are disposed on a common fluid outlet plane (43).

Abstract: A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).

Abstract: The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel. The enhanced mixing feature may include a turbulated mixing zone.

Abstract: A bundled tube fuel injector includes an outer band that circumferentially surrounds a fuel plenum defined within the bundled tube fuel injector. The outer band includes a forward end portion that is axially separated from an aft end portion. A plurality of pre-mix tubes extends through the fuel plenum substantially parallel to one another. A first segment of the plurality of pre-mix tubes is circumferentially surrounded by the outer band. An outer shroud extends circumferentially around a second segment of the pre-mix tubes. The outer shroud includes a forward portion and an aft portion. The aft end portion of the outer band is coupled to the forward portion of the outer shroud via a plurality of fasteners for enhanced assembly and reparability.

Abstract: A combustor cap for a combustor chamber of a combustion system is provided. The combustor cap includes a plate member including: a plurality of openings for accommodating a plurality of fuel nozzles of the combustion system; a cooling passage extending through a plane of the plate member; an entrance opening to the cooling passage; and an exit opening from the cooling passage to a side of the plate member opposite to the combustion chamber.

Abstract: A bundled tube fuel nozzle includes a fuel distribution body. The fuel distribution body includes a substantially flat aft wall having an inner surface axially spaced from an outer surface, a fuel stem collar axially spaced from the inner surface of the aft wall and a contoured forward wall that extends between the fuel stem collar and the aft wall. The contoured forward wall and the aft wall define a fuel plenum within the fuel distribution body. The bundled tube fuel nozzle further includes a plurality of injector tubes that are in fluid communication with the fuel plenum. Each injector tube extends from the contoured forward wall to the aft wall within the fuel distribution body and defines a premix passage through the contoured forward, the fuel plenum and the aft wall.

Abstract: A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system. The oxidation of the fuel is initiated by raising the temperature of the mixture to or above an auto-ignition temperature of the fuel. In some cases, the reaction chamber may be provided without a fuel oxidation catalyst material.

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

Abstract: A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine.

Abstract: A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow, a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector and is individually removable from the combustor cap assembly, an air distributor disposed within the interior volume and configured to distribute the air flow received by the interior volume to each of the plurality of mixing tubes, and a combustor cap removably coupled to the support structure.

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 includes a multi-tube fuel nozzle with a fuel nozzle body and a plurality of tubes. The fuel nozzle body includes a nozzle wall surrounding a chamber. The plurality of tubes extend through the chamber, wherein each tube of the plurality of tubes includes an air intake portion, a fuel intake portion, and an air-fuel mixture outlet portion. The multi-tube fuel nozzle also includes a differential configuration of the air intake portions among the plurality of tubes.

Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.

Abstract: A premixer assembly for mixing air and fuel for combustion includes a plurality of tubes disposed at a head end of a combustor assembly. Also included is a tube of the plurality of tubes, the tube including an inlet end and an outlet end.

Abstract: A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.

Abstract: A method for use in a gas turbine engine. The method includes the steps of: configuring a downstream injection system within the interior flowpath that includes two injection stages, a first stage and a second stage, wherein the first stage and the second stage are each axially spaced from the other; and circumferentially positioning the injectors of the first stage and the second stage based on: a) a characteristic of an anticipated combustion flow occurring just upstream of the first stage during a mode of operation; and b) the characteristic of an anticipated combustion flow just downstream of the second stage given an anticipated effect of the air and fuel injection from the first stage and the second stage.

Abstract: A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough. A fuel injector is coupled to the fuel/air mixer assembly. The fuel injector has a tip portion with a plurality of fuel outlets arranged to direct fuel into the air flow passages of the air/fuel mixer elements. Each of the fuel/air mixer elements has at least one outlet arranged to supply fuel to the element.

Abstract: A bundled tube fuel injector includes a fuel distribution module, a tube bundle having a plurality of pre-mix tubes that extend in parallel downstream from the fuel distribution module and a support plate disposed substantially adjacent to the fuel distribution manifold. The plurality of pre-mix tubes extends through the support plate. A retention sleeve is coupled to the support plate at a first end. A second end of the retention sleeve includes a plurality of radially extending retention features that are circumferentially arranged around the second end. The bundled tube fuel injector also includes an aft plate having a retention collar. The retention collar is configured to engage with the retention features. The retention sleeve and the retention collar partially define a cartridge passage that extends through the bundled tube fuel injector.

Abstract: A gas turbine engine fuel injector is disclosed having a plurality of fuel injection circuits that are structured to deliver fuel to air passageways. In one non-limiting embodiment, one of the fuel injection circuits includes a plain jet airblast injector that delivers fuel to an air passageway. In some applications the plain jet can extend across the air passageway and deliver a fuel to an opposite surface to form a fuel film. The fuel film can then be sheared between an air in the air passageway and an air in a nearby air passageway. Another of the fuel injection circuits includes a fuel filmer structured to deliver fuel to an air passageway that can then be sheared by an air in the air passageway and an air in the air passageway that included the plain jet airblast injector.

Abstract: A device for injecting a mixture of air and fuel into a turbine engine combustion chamber, the device including a mechanism for centering a fuel injector, which mechanism is movable radially in a support mechanism fastened to a wall of the chamber, the support mechanism carrying a retaining mechanism for axially retaining the centering mechanism on a side opposite from the chamber wall, the retaining mechanism being fastened in releasable manner to the support mechanism.

Abstract: A late lean injection combustor assembly may include a first interior in which a first fuel supplied thereto is combustible, a flow sleeve annulus including a second interior in which a second fuel supplied thereto is combustible, at least one fuel injector disposed about the second interior, and at least one elongate premixing conduit disposed about the flow sleeve annulus and in fluid communication with the at least one fuel injector. The at least one elongate premixing conduit may be in fluid communication with a compressor discharge air and the second fuel such that the compressor discharge air and the second fuel are premixed within the elongate premixing conduit before entering the second interior by way of the at least one fuel injector.

Abstract: A gas turbine combustor cap assembly (24) including a pre-mix tube (42, 44) with an upstream flange (60, 62) that aligns and seats the tube against a primary feed plate (66) attached to an upstream end of a support ring (48). The pre-mix tube may have an intermediate flange (64) at an intermediate position on the length of the tube that aligns and seats the tube against an intermediate structural frame (68) attached to the support ring at an intermediate position on the length of the support ring. The combustor cap assembly (24) may have multiple pre-mix tubes, including a central pre-mix tube (44) with upstream (62) and intermediate (64) flanges and a circular array of outer pre-mix tubes (44) with at least an upstream flange (64).

Abstract: A combustor includes an end cover having an outer side and an inner side, an outer barrel having a forward end that is adjacent to the inner side of the end cover and an aft end that is axially spaced from the forward end. An inner barrel is at least partially disposed concentrically within the outer barrel and is fixedly connected to the outer barrel. A fluid conduit extends downstream from the end cover. A first bundled tube fuel injector segment is disposed concentrically within the inner barrel. The bundled tube fuel injector segment includes a fuel plenum that is in fluid communication with the fluid conduit and a plurality of parallel tubes that extend axially through the fuel plenum. The bundled tube fuel injector segment is fixedly connected to the inner barrel.

Abstract: A combustor includes a combustor external cylinder, a tubular combustor basket installed in the combustor external cylinder, a compressed air channel defined between the combustor external cylinder and the combustor basket, and a plurality of fuel nozzles installed in the combustor basket. Compressed air flowing along the compressed air channel is approximately reversed in the flow direction at an end of the combustor basket, and is introduced into the plurality of fuel nozzles. Fuel injection pegs made up of an upstream side fuel injection peg injecting upstream side fuel and a downstream side fuel injection peg injecting downstream side fuel, are installed in the compressed air channel. Concentration fluctuation of the upstream side fuel caused by pressure fluctuation in the combustor is configured so as to reduce a peak of concentration fluctuation of the downstream side fuel at a combustion start position of the combustor.

Abstract: A system includes a turbomachine including a first chamber configured to contain a first fluid and a second chamber configured to contain a second fluid. The turbomachine also includes a barrier disposed between the first and second chambers. The barrier is configured to separate the first fluid and the second fluid. Additionally, the barrier includes a first surface facing the first chamber and a second surface facing the second chamber. The turbomachine also includes an orifice extending from the first chamber to the second chamber. The orifice defines a fluid passageway. Additionally, the turbomachine includes a tube including a first end and a second end. The first end is coupled to the first surface and is disposed about a perimeter of the orifice. The tube is configured to at least partially contain the second fluid.

Abstract: A wake manipulating structure for a turbine system includes a combustor liner defining a combustor chamber. Also included is an airflow path located along an outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is a venturi structure or section disposed in the airflow path configured to reduce the wake region.

Abstract: A system including a multi-tube fuel nozzle, including a first plate having a first plurality of openings, a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, and a resilient metallic seal disposed along the first plate about the plurality of tubes.

Abstract: A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold.

Abstract: An assembly for use in a fuel injection system within a combustor of a combustion turbine engine is described. The assembly may include: a first port formed through an outer radial wall of the combustor and a second port formed through an inner radial wall. A plenum may be formed about the first port. A tube may be formed that has a first end positioned within the first port and a second end positioned within the second port. At the first end, the tube may be sized smaller than the first port such that two passages are defined therethrough: a first passage defined about an exterior of the tube; and a second passage defined through an interior of the tube.

Abstract: Disclosed herein are screw shaft turbine compressors having (i) a compressor section, (ii) a turbine section, (iii) a combustion section coupling to the compressor section and the turbine section, and (iv) a grooved shaft. The grooved shaft can include one or more grooves for providing fuel from the compressor section to the combustion section and for allowing exhaust to leave the combustion section and exit the turbine section. A method for generating different speed to torque ratios on the shaft and a system for generating torque on the shaft are further disclosed.

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 combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.

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: A system includes a multi-tube fuel nozzle including a fuel nozzle head that includes an outer wall surrounding a chamber. The outer wall includes a downstream wall portion configured to face a combustion region. The multi-tube fuel nozzle also includes multiple tubes extending through the chamber to the downstream wall portion. Each tube of the multiple tubes includes an upstream portion, a downstream portion, and at least one fuel inlet disposed at the upstream portion, and is configured to receive air and mix the air with fuel from the at least one fuel inlet. The multi-tube fuel nozzle includes a fuel conduit extending through the chamber crosswise to and around the multiple tubes. The fuel conduit includes multiple impingement cooling orifices. A fuel flow path extends through the fuel conduit, through the impingement cooling orifices, through the chamber, and into the at least one fuel inlet of each tube.

Abstract: There is provided a heating device, in particular an austenitization device, for a plant for hot forming blanks, wherein the heating device is for locally heating, in particular austenitization, regions of the blanks and has at least one burner. Also included is means for moving the burner and/or the flame of the burner to the regions of the blank which are to be subjected to local heating.

Abstract: A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes an end cover, an endcap assembly, a fluid supply chamber, and a plurality of tube assemblies positioned at the endcap assembly. Each of the tube assemblies includes housing having a fuel plenum and a cooling fluid plenum. The cooling fluid plenum is positioned downstream from the fuel plenum and separated from the fuel plenum by an intermediate wall. The plurality of tube assemblies also include a plurality of tubes that extends through the housing. Each of the plurality of tubes is coupled in flow communication with the fluid supply chamber and a combustion chamber positioned downstream from the tube assembly. The plurality of tube assemblies further includes an aft plate at a downstream end of the cooling fluid plenum. The plate includes at least one aperture.

Abstract: A gas turbine engine case has a metallic composite boss mounted thereto. The boss may have a main metal injection molded (MIM) part, and a separately formed flange part integrated to the main MIM part and projecting laterally outwardly therefrom. The MIM part and the flange part may be made of different materials. The material of the flange part is selected to provide a suitable mounting interface with the gas turbine engine case.

Abstract: A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes arranged on a reference circle diameter which, together with a first longitudinal end face of the vanes disposed on a first wall and a second wall disposed on an opposing second longitudinal end face of the vanes, form a flow channel. In this arrangement at least one injection orifice in the first wall and at least one further injection orifice in the second wall open into a flow channel. The arrangement of the at least two mutually opposing injection orifices in the wall of the swirler makes for a homogeneous distribution of the fuel in the flow channel and ensures a uniform mixing of the air with the fuel. This results in uniform and low-NOx combustion of the fuel/air mixture in a burner.

Abstract: A fuel distributor is disclosed comprising a body having a unitary construction, a fuel conduit located within the body, a fuel flow path located within the body that is oriented in a circumferential direction around an axis and in flow communication with the fuel conduit, and at least one orifice located in the body in flow communication with the fuel flow path such that a fuel entering the fuel conduit exits through the orifice.

Abstract: A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud.

Abstract: An object of the invention is to provide a reliable gas turbine combustor that can provide lowered NOx and combustion stability. The gas turbine combustor includes a combustion chamber to which fuel and air are supplied; a first burner located on the upstream side of the combustion chamber, the first burner jetting fuel into the combustion chamber and jetting air into the combustion chamber in a swirling manner; a plurality of second burners arranged around the first burner and supplying a premixed gas of air and fuel to the combustion chamber; an annular bulkhead disposed between the first burner and the second burners and having an inclined surface formed to broaden toward the downstream side of the combustion chamber; and a plurality of air jet ports formed in the inclined surface of the annular bulkhead and adapted to jet air into the combustion chamber.

Abstract: A micromixer of a turbine system is provided and the micromixer includes a plurality of pipes each having an inlet and an outlet for receiving flow and dispersing the flow to a combustor. Also provided is a non-uniform inlet arrangement defined by the inlets of the plurality of pipes, wherein at least one of the inlets extends to an axial location distinct from at least one other inlet.

Abstract: A fuel supply device of a gas turbine engine is provided. The fuel supply device includes a fuel divider which divides fuel supplied from a collecting fuel passage to feed the fuel to a pilot fuel passage and to a main fuel passage. The fuel divider includes a movable member which is movable according to fuel pressure at the fuel entrance and opens and closes pilot ports and main ports according to a distance of the movement of the movable member. When the fuel pressure at the fuel entrance is not higher than a predetermined value, the fuel is supplied only to the pilot fuel passage, while when the fuel pressure at the fuel entrance is higher than the predetermined value, the fuel is supplied to the pilot fuel passage and to the main fuel passage.

Abstract: A combustor of a turbomachine is provided and includes an assembly defining an interior and being configured to direct air to flow along an annulus in a first direction about the interior and in a second direction toward the interior, the first and second directions being substantially opposed, a manifold configured to be supplied with fuel and a tubular body defining a pathway along which the air is transmittable in a third direction from the annulus to the interior, the third direction being transverse to the first and second directions. The tubular body includes a sidewall extendible through the manifold. The sidewall defines an injection hole within the manifold by which transmitted air is mixable with the fuel.

Abstract: A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend from the upstream surface through the downstream surface. A divider inside a tube bundle defines a diluent passage that extends axially through the downstream surface, and a diluent supply in fluid communication with the divider provides diluent flow to the diluent passage. A method for reducing combustion dynamics in a combustor includes flowing a fuel through tube bundles, flowing a diluent through a diluent passage inside a tube bundle, wherein the diluent passage extends axially through at least a portion of the end cap into a combustion chamber, and forming a diluent barrier in the combustion chamber between the tube bundle and at least one other adjacent tube bundle.

Abstract: A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.

Abstract: A fuel-air mixer for use with a combustor is provided. The fuel-air mixer includes an outer ring, an intermediate hub disposed coaxially within the outer ring such that a first plenum is formed therebetween, and an inner hub disposed coaxially within the intermediate hub such that a second plenum is formed therebetween. A first swirler including a plurality of first swirler vanes is positioned between the outer ring and the intermediate hub, wherein the first swirler is configured to rotate fluid flowing therethrough in a first direction. A second swirler including a plurality of second swirler vanes is positioned between the intermediate hub and the inner hub, wherein the second swirler is configured to rotate fluid flowing therethrough in a second direction. A plurality of fuel injection conduits are also defined within the fuel-air mixer for channeling fuel to the first and second plenums.

Abstract: A seal assembly for use between an injector and a combustion chamber in a gas turbine. A liner at least partially defines the combustion chamber, and the liner has at least one tubular liner collar, through which an injector is inserted. In one embodiment, the liner collar has a partially convex outer diameter and a floating collar is positioned at least partially around the liner collar. The floating collar has a retention member having a first end fixed to the floating collar and a second end configured to abut the convex outer diameter of liner collar, wherein the retention member maintains the floating collar at a radial distance from the injector less than a radial distance between the liner collar and the injector.

Abstract: A lance is presented for introducing fuel into a second burner of a combustion chamber of a gas turbine installation with sequential combustion, having a first and a second combustion chamber. The lance includes a foot and a shank which projects from it. In an installed state of the lance the foot extends perpendicularly or at an angle to a main flow direction of the burner. The shank extends centrally in the burner and generally parallel to the main flow direction. At least one projecting arm, having at least one nozzle for introducing fuel, is arranged such that it extends from the shank. A respective end of the at least one arm is oriented in the main flow direction and extends generally parallel to the main flow direction.