Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor is provided. The fuel injector has an annular flow passage which conveys fuel to a prefilming lip at an end of the flow passage. The fuel injector also has plurality of fuel distributor slots which are circumferentially spaced around and in fluid communication with the other end of the flow passage to deliver respective fuel streams into the flow passage. The slots are configured so that the fuel streams enter the flow passage at a swirl angle of at least 80° relative to the axis of the flow passage.

Abstract: A fuel nozzle for a turbine engine is disclosed. The fuel nozzle has a common axis, a body portion disposed about the common axis, a barrel portion located radially outward from the body portion. The fuel nozzle also has at least one swirler vane disposed between the body portion and the barrel portion and a liquid fuel jet disposed within the at least one swirler vane. The at least one swirler vane is configured to radially redirect an axial flow of air. The liquid fuel jet is configured to inject liquid fuel in a radial direction relative to the common axis.

Abstract: A fuel injector for a gas turbine engine is disclosed which includes an inlet fitting for receiving fuel, a nozzle for issuing fuel into the gas turbine engine, an injector body extending between the inlet fitting and the nozzle and having and interior bore extending therethrough, and an elongated fuel tube disposed within the interior bore of the injector body for delivering fuel from the inlet fitting to the nozzle. The fuel tube has an inlet end portion dynamically associated with the inlet fitting and an outlet end portion rigidly connected to the nozzle. An adapter is operatively associated with either the inlet end section of the fuel tube or a reception bore formed with the inlet fitting of the injector for accommodating a seal member in a manner that permits thermal growth of the injector body relative to the fuel tube.

Abstract: A mounting system for an annular internal fuel manifold disposed within a gas turbine engine includes a fuel inlet assembly having a heat shield extending about at least a portion of an inner fuel inlet tube. The heat shield has a distal end engaged with the fuel manifold and has a radially outwardly projecting shoulder proximate an opposed proximal end thereof. The proximal end of the heat shield is received within a bushing disposed within a corresponding opening of a supporting casing. The shoulder of the heat shield retains the bushing in place.

Abstract: A gas turbine engine fuel nozzle assemblage (10) comprises a nozzle outer body (25) comprising a premixing section (23) and an interiorly disposed first fuel passageway (22) to supply fuel to the premixing section (23), and more interiorly a central channel (33) comprising an inlet (30) from an air supply, an aperture (19) at an upstream end to receive a lance (18), and a downstream-disposed annular bearing surface (21) adapted to slidingly engage the lance, the fuel nozzle assemblage adapted so that the lance may be alternatably selected as any interchangeable one of a gas lance, an oil lance, and a non-fueling dummy lance. Between the lance and the central channel (33) is formed a cooling fluid passageway (24) that is in fluid communication with the inlet (30) and one or more cooling fluid passageway exits (60). The interchangeability of the lances (18) is effective to provide a desired flexible functionality to said fuel nozzle assemblage.

Abstract: A fuel injector (36) for alternate fuels (26A, 26B) with energy densities that differ by at least about a factor of two. 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) between the respective radial passages and the surface (49) of the vane. 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 backpressure. 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 about twice first fuel flow rate at the given backpressure.

Abstract: A secondary fuel nozzle is formed by brazing and welding a central core, a cylindrical body, and a unitary secondary fuel nozzle portion. The central core has a central bore for receiving a liquid fuel cartridge, and at least two passages concentric with the central bore. The secondary fuel nozzle portion includes a base flange and a main shaft having a central bore for aligning with the central bore of the core and for receiving the liquid fuel cartridge, and a plurality of peripheral bores disposed at spaced locations about the central bore for flow communication with the concentric passages of the core. The core is brazed to the base flange and the cylindrical body is disposed around the core and welded to the base flange to define a one-piece secondary fuel nozzle assembly.

Abstract: Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface.

Abstract: A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.

Abstract: The invention relates to a burner having an annular premixing channel in which fuel can be discharged in a radially distributed manner. The radial distribution of the fuel can be regulated during operation of the burner in that fuel can be supplied, independently of one another, into a first and a second part of admission devices having admission holes varying radially in opposite direction by means of fuel supply lines. The invention also relates to a method for operating a gas turbine in which radial distribution of the fuel is regulated in a premixing channel of a burner.

Abstract: The present invention relates to a burner for a combustion chamber of a gas turbine plant, with an injection device for introducing gaseous fuel into the burner. The injection device has a body which is arranged in the burner and which has at least one nozzle for introducing gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction transversely with respect to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at an trailing edge of the streamlined body.

Abstract: The present invention relates to a burner for a combustion chamber of a gas turbine plant. The burner includes a lance for introducing gaseous fuel into the burner. A shaft of the lance has at least one nozzle for introducing gaseous fuel into the burner. A main injection direction of the respective nozzle is oriented onto a portion of a burner wall. An introduction device for a diverting fluid is provided, which is designed for introducing a diverting fluid counteracting an impingement of the fuel flow on the burner wall.

Abstract: A fuel nozzle for a gas turbine engine is disclosed, the fuel nozzle comprising at least one unitary component made using a rapid manufacturing process. In one aspect, the rapid manufacturing process is a laser sintering process. Unitary components disclosed include a conduit, swirler, distributor, venturi and a centerbody.

Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.

Abstract: A method of fabricating a fuel nozzle is provided. The method includes providing a unitary portion of material including a first end face, a second end face, and a body extending therebetween. A passageway is fabricated to extend from the first end face to the second end face along a centerline of the portion of material. The method further includes fabricating a plurality of concentrically-aligned channels within the first end face, and fabricating a plurality of inlets that extend through at least one of the second end face and an outer surface of the body to at least one of the passageway and one of the plurality of channels.

Abstract: A fuel injector for an aero-mechanical injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the injector comprising a main tubular structure of axis XX? opening out at a downstream end for delivering the air/fuel mixture, a tubular fuel duct that is disposed inside the main structure and that opens out into the main structure via a fuel atomizer plug so as to introduce fuel into the main structure at a pressure PC into the main structure, at least one air feed channel that opens out into the main structure so as to introduce air at a pressure PA therein, and means for injecting into the fuel duct a gas at a pressure PG that is greater than PA and greater than or equal to PC so as to create effervescence in the fuel on being introduced into the main structure.

Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.

Abstract: A burner for a gas-turbine engine has a frustoconical burner shell, at least two swirler arrangements, which are connected to the shell and are spaced apart around the circumference of the shell between its two ends, and a combustion chamber disposed downstream of a wider end of the shell. Each of the swirler arrangements includes an air swirler and a pre-combustion chamber disposed downstream of the air swirler, and a longitudinal axis of each swirler arrangement intersects a line parallel to, and spaced apart from, the longitudinal axis of the shell. The swirler arrangements are preferably connected to the shell at the same axial point.

Abstract: This invention aims to suppress the occurrence of smoke, for example, during a light load operation of a gas turbine, by adopting an air blast method for a pilot nozzle in a dual fuel combustion low NOx combustor. A gas turbine combustor of the present invention is that in a gas turbine furnished with a dual fuel combustion low NOx combustor having a pilot nozzle capable of injecting a gaseous fuel and a liquid fuel simultaneously or selectively, and a plurality of main nozzles disposed around the pilot nozzle and being capable of injecting a gaseous fuel and a liquid fuel simultaneously or selectively, wherein the pilot nozzle has a gas nozzle portion for injecting the gaseous fuel, and a liquid nozzle portion for injecting the liquid fuel, adopts an air blast method for the liquid nozzle portion, uses combustion air as air for an air blast, and throws the combustion air at a liquid film formed in the liquid nozzle portion to atomize the liquid fuel by use of a velocity difference.

Abstract: A gas turbine engine fuel nozzle includes an axis of symmetry extending therethrough, the nozzle body including a first passage extending coaxially therethrough, a second passage, and a third passage, the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip coupled to the nozzle body, the nozzle tip including at least one primary discharge opening in flow communication with the first passage, at least one secondary discharge opening in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet. The fuel injector also includes a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis. The premix barrel is fluidly coupled to the fuel galleries and the compressed air inlet at the proximal end and is configured to couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel having a first end and a second end. The second end is coupled to the injector housing and the first end is located proximate the distal end of the premix barrel.

Abstract: A method of operating a gas turbine engine is provided. The method includes discharging pilot fuel into a combustion chamber from a nozzle through at least one pilot fuel outlet defined in a tip of the nozzle, discharging steam from the nozzle through a plurality of steam outlets that are spaced circumferentially about the plurality of pilot fuel outlets, and discharging primary fuel from the nozzle through a plurality of primary fuel outlets that are circumferentially aligned with the plurality of steam outlets. To facilitate mixing the primary fuel with the steam, the primary fuel is discharged from the nozzle tip at an oblique angle with respect to a centerline extending through the nozzle tip.

Abstract: A method and a pre-shaped workpiece for making at least a portion of a gas turbine fuel nozzle are disclosed having opposed gripping tabs which can be secured to machine tool holders during manufacturing by a machine tool.

Abstract: A fuel lance for a gas turbine installation with sequential combustion, in which hot gas is produced in a first combustion chamber and expanded in a subsequent turbine, and then flows through a subsequent second combustion chamber in which the fuel lance for injecting fuel into the hot gas is arranged. The fuel lance has a lance section which extends in the flow direction of the hot gas and includes at least an outer tube which is arranged concentrically to a lance axis, and a center tube which is concentrically arranged in the outer tube and in which the fuel is guided to the lance tip and is injected through first injection openings in the region of the lance tip into the hot gas. The fuel lance is modified for operation with syngas by the first injection openings being arranged directly on the lance tip, and by the first injection openings being oriented so that the fuel jets which emerge from them include an acute angle with the lance axis.

Abstract: A fuel nozzle sheath has a lateral opening for admitting air about a nozzle stem. The stress distribution along the perimeter of the window is smoothed out by increasing the corner radius of the window corner presenting higher stress concentration.

Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.

Abstract: A fuel nozzle assembly for a gas turbine includes a plurality of circumferentially spaced vanes with holes for flowing fuel from plenums within the vanes through holes in the vane walls for premixing with air. To tune the nozzle assembly, the holes are resized by reforming the existing holes to a predetermined hole size, securing plugs into the holes, and forming holes through at least certain of the plugs to diameters less than the diameter of the existing holes.

Abstract: A method of operating a gas turbine engine is provided. The method includes discharging pilot fuel into a combustion chamber from a nozzle through at least one pilot fuel outlet defined in a tip of the nozzle, discharging steam from the nozzle through a plurality of steam outlets that are spaced circumferentially about the plurality of pilot fuel outlets, and discharging primary fuel from the nozzle through a plurality of primary fuel outlets that are circumferentially aligned with the plurality of steam outlets. To facilitate mixing the primary fuel with the steam, the primary fuel is discharged from the nozzle tip at an oblique angle with respect to a centerline extending through the nozzle tip.

Abstract: Disclosed is a ring-shaped fuel injector having an inner diameter, an outer diameter and a height, a fuel groove arranged in a face side of the ring, and at least one fuel injection opening arranged on the ring and connected to the fuel groove.

Abstract: A fuel injector system provides an air assist fuel nozzle which includes a fuel shroud and an air portion. Air passes around the fuel shroud to air jets in the air portion to provide a focused application of air directly onto a fuel spray from each of a multiple of main fuel jets to impart additional velocity to the fuel as it is flowing out of the fuel nozzle. The air jets increase the resulting fuel spray velocity to a level high enough to reach a prefilmer wall of a swirler even during snap deceleration conditions.

Abstract: To improve the burning efficiency of fuel supplied to a turbine engine by electronic fuel injectors under control of a fuel injection control system, a nebulizer of unique design is employed with the fuel injectors to further reduce the individual fuel cell size from that provided by the pulsing of fuel from the fuel injector. At least one nebulizer is used with at least one fuel injector, having means for injecting fuel in pulses into the nebulizer and thence into the combustion chamber of a turbine engine, and an electronic control unit to receive and interpret input sensor signals from selected operating functions of the engine and to generate and direct fuel injection signals to modify the pulse duration and/or frequency of fuel injection in response to a deviation from a selected operating function, such as the desired operating speed, caused by variable operating loads encountered by the turbine engine.

Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. When in gas operation, the fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber.

Abstract: In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements including liquid fuel jets are arranged to such that through high angle incidents by the airflow appropriate vaporization and droplet formation is achieved for a fuel/air mixture combustible in a combustor of a turbine engine. At low liquid fuel flow rates below a pre-determined level the liquid fuel is atomized and entrained by the airflow. At high liquid fuel flow rates the fuel splash impinges upon a wash surface to develop a wash film which is again vaporized and atomized about an edge for a fuel/air mixture capable of combustion.

Abstract: A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixing burner and the premix gas feed is carried out via side wall shells of the premixing burner. The premix gas feed and the pilot gas feed are carried out in combination, in such a way that a continuous mixture ratio between premix gas and pilot gas can be set within the premixing burner.

Abstract: A method enables a gas turbine engine to be assembled. The method comprises coupling a fuel nozzle within the engine to inject fuel into the engine, wherein the fuel nozzle includes three independent injection circuits arranged such that the second injection circuit is between the first and third injection circuits, coupling a liquid fuel source to a first injection circuit defined within the nozzle and including an annular discharge opening, and coupling a water source to one of the second injection circuit and the third injection circuits such that the water source is coupled in flow communication to an annular discharge opening.

Abstract: A multi-staged gas turbine engine fuel supply system includes a plurality of fuel injectors and at least first and second staged fuel injection circuits in each of the fuel injectors. Each of the first and second staged fuel injection circuits includes first and second fuel injection points and at least first and second fuel nozzle valves operable to open at different first and second crack open pressures and controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector may have a valve housing with one of the first fuel nozzle valves and one of the second fuel nozzle valves contained therein.

Abstract: A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel is formed in a surface of a gas turbine engine component, and the channel is adapted for conveying a fluid flow from an inlet to an outlet. At least a first sealing member is disposed within the channel and divides the channel into at least a first discrete conduit and a second discrete conduit. A second sealing member encloses the channel to define the second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.

Abstract: The present invention relates to a fuel nozzle for use in an engine such as a gas turbine engine. The fuel nozzle includes a fuel injector for injecting fuel into a combustion chamber of the engine and a plurality of rows of holes surrounding the fuel injector for eliminating recirculation of hot gas products onto a face of the fuel nozzle. The holes eject air primarily in an axial direction.

Abstract: A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.

Abstract: A fuel injector includes an annular main fuel nozzle received within an annular nozzle housing, a main nozzle fuel circuit having at least one annular leg, and a pilot nozzle fuel circuit. Spray orifices of the leg extend through the fuel nozzle and spray wells through the housing are aligned with the orifices. The nozzle is designed to generate sufficient static pressure differentials between at least two different ones of the spray wells to purge the main nozzle fuel circuit. Spray well portions may be asymmetrically flared out with respect to a spray well centerline in different local streamwise directions. Some of the spray well portions may be asymmetrically flared out in a local upstream direction and others in a local downstream direction. The local streamwise direction may have an axial component parallel to a nozzle axis about which the annular nozzle housing is circumscribed and a circumferential component around the nozzle housing.

Abstract: A multi-staged gas turbine engine fuel supply fuel injector includes at least first and second staged fuel injection circuits having first and second fuel injection points. At least first and second fuel nozzle valves operable to open at different first and second crack open pressures are controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector includes a valve housing containing the fuel nozzle valves.

Abstract: A diffusion flame combustor for a gas turbine comprising a flame tube that delimits a combustion chamber, the flame tube having a fuel injector unit mounted at one end, the other end of the tube being connected to a duct that conveys combustion gases to the turbine. The flame tube is mounted coaxially inside a generally tubular container that communicates with the discharge casing of an air compressor and, together with the tube, defines a space for combustion air. The injector unit comprises an injector head facing generally into the combustion chamber and provided with at least one fuel gas injection nozzle. The nozzle includes an air-gas premixing duct into which fuel gas is introduced. The premixing duct has an inlet section that communicates with the air space and is provided with a radial-fin air swirler generally upstream of a point at which the fuel gas enters the premixing duct. This partial premixing of combustion gas with combustion air reduces NOx emissions and production of un-combusted material.

Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.

Abstract: There is provided a combustor comprising a fuel nozzle which is comprised of a rodlike body which has a fuel passage and which is located in an air passage; a plurality of hollow members which are connected to the fuel passage and which extend in radial directions from the rodlike body into the air passage; at least one injection port formed in each hollow member to inject a fuel from the fuel passage into the air passage; and a projection which extends from a farmost inner wall of each hollow member that is most distant from an axis of the rodlike body to the injection port that is most distant from the axis. A hole for leaking fuel that is connected to an air passage may be formed in a farmost inner wall of the hollow member that is more distant from an axis of a rodlike body than the injection port that is most distant from the axis, or may be formed to be adjacent to all the injection ports on an upstream or downstream side in the direction of the airflow.

Abstract: A fuel injector includes a main fuel nozzle with a main nozzle fuel circuit and a pilot nozzle fuel circuit in fuel supply communication with a pilot nozzle. The injector further includes a purge means for purging the main nozzle fuel circuit while the pilot nozzle fuel circuit supplies fuel to the pilot nozzle and a purge air cooling means for supplying a cooled portion of purge air to the main nozzle fuel circuit during purging. The cooled portion is cooled with fuel that flows through the pilot nozzle fuel circuit. The purge air cooling means may include a purge air cooling path in thermal conductive communication with the pilot nozzle fuel circuit and operable to flow the cooled portion therethrough to the main nozzle fuel circuit during purging. The purge air cooling path may be in thermal conductive communication with at least one annular pilot leg of the pilot nozzle fuel circuit.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly.

Abstract: A fuel injector for a gas turbine engine has an inlet fitting, a fuel nozzle, and a housing stem with a pair of fuel conduits fluidly interconnecting the nozzle and fitting. The fuel nozzle includes an annular secondary fuel passageway directing fuel from one fuel conduit to an annular discharge orifice at a discharge end of the nozzle. The secondary fuel passageway is defined between an outer, annular fuel conduit portion and a primary adapter. The primary adapter has an outer surface with a distinct, radially-outwardly-projecting annular shoulder to restrict flow through the secondary passageway and provide substantially uniform distribution of flow through the passageway downstream of the shoulder, for improved combustion and flame stability.

Abstract: A flame-holding nozzle for a combustion turbine engine is disclosed. The nozzle includes several elongated sleeves in a substantially concentric arrangement. The sleeves cooperatively provide distinct passageways for fluids to move through the nozzle. The nozzle includes conduits that advantageously direct fluids to designated regions of the nozzle, allowing fuel and cooling fluid to move within the nozzle without becoming commingled. Portions of the nozzle sleeves are also strategically arranged to transmit fluids in a manner that provides substantially-uniform thermal expansion, thereby reducing the need for sliding joints or bellows arrangements.

Abstract: An injector of a two-headed combustion chamber of a turbomachine has a first feed tube which is connected to an annular injection piece for discharging primary fuel into the combustion chamber. It also has a second feed tube surrounding the first feed tube and connected to a cylindrical endpiece for discharging secondary fuel into said combustion chamber. This endpiece has an annular channel of diameter that is greater than the diameter of the second feed tube and that extends over its entire length. A third tube is provided that surrounds the second tube and that is connected to a tubular separation element which is inserted in the annular channel of the cylindrical endpiece so as to form two annular spaces in which a cooling fluid can flow over 360° all the way to the end of the injector.

Abstract: An injector includes a plurality of flat, circular plates which provide fuel delivery and cooling of the injector. Fuel delivery passages in the plates have swirl chambers and spray orifices which are formed by chemical etching. A pair of fuel delivery plates define a fuel cavity therebetween, and include a plurality of radially-outwardly extending spokes, with the spokes from one fuel plate in adjacent, surface-to-surface relation with opposing spokes from the adjacent fuel plate. A fuel passage is defined between each of the opposing spokes, leading from the fuel cavity to a fuel outlet opening at the distal end of each spoke. A fuel tube delivers fuel to the fuel cavity between the plates, from where the fuel is then directed through the outlet openings. Downstream plates shape the fuel into appropriate sprays for ignition. An upstream cooling plate assembly directs air against the upstream fuel plate, and radially outwardly along the spokes of the upstream plate.