EP3239613A1 - Composant de brûleur, brûleur et leurs procédés de fabrication ou de fonctionnement pour un fonctionnement à deux carburants - Google Patents

Composant de brûleur, brûleur et leurs procédés de fabrication ou de fonctionnement pour un fonctionnement à deux carburants Download PDF

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Publication number
EP3239613A1
EP3239613A1 EP16167741.4A EP16167741A EP3239613A1 EP 3239613 A1 EP3239613 A1 EP 3239613A1 EP 16167741 A EP16167741 A EP 16167741A EP 3239613 A1 EP3239613 A1 EP 3239613A1
Authority
EP
European Patent Office
Prior art keywords
burner
fluid
fluid channel
fuel
hole
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16167741.4A
Other languages
German (de)
English (en)
Inventor
Alessio Bonaldo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP16167741.4A priority Critical patent/EP3239613A1/fr
Priority to PCT/EP2017/055256 priority patent/WO2017186386A1/fr
Priority to EP17710688.7A priority patent/EP3417208B1/fr
Publication of EP3239613A1 publication Critical patent/EP3239613A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to a burner component and more particularly to a burner through which dual fluids are provided, particularly dual fuel, for combustion in a turbomachine, particularly a gas turbine engine.
  • ambient air may be compressed by a compressor section and provided to a combustor in which the substantially ambient air will be mixed fuel, the mixture being combusted in a combustion chamber of the combustor, to provide a driving force for a subsequent turbine section - an expansion turbine - in which a hot fluid from the combustor will drive rotor blades of the turbine to drive again one or several shafts.
  • One of the shafts is typically connected to rotor blades of the expansion turbine - turbine rotor blades - and also to rotor blades of the compressor section - compressor rotor blades - so that fluidic forces generated by the combustor and acting upon the turbine rotor blades result directly in revolution of that shaft and the connected compressor rotor blades, which lead to - due to interaction with guide vanes of the compressor and due to reduced cross sectional area of the fluidic path in the compressor - to compression of the ambient air.
  • compressed ambient air and fuel is provided to the combustor.
  • the compressed air is swirled - via a swirler or a swirl generator - and fuel is injected into the swirled air to provide a well mixed fluid.
  • This air/fuel mixture is ignited and burned in a combustion chamber of the combustor.
  • gas turbine engines a continuous combustion takes place in which constantly an air/fuel mixture is provided and burned such that a stable flame is formed in the combustion chamber.
  • pilot fuel may be injected at a different position into the combustion space.
  • the pilot fuel may possibly also be a different fuel type, e.g. liquid fuel, while a so called main fuel is natural gas.
  • pilot fuel may not be needed anymore and can be shut off or at least reduced.
  • the present invention seeks to mitigate the mentioned drawbacks.
  • a burner component particularly a swirler vane or a fuel lance for a burner of a gas turbine engine, comprising a first fluid channel to guide a first fluid, particularly a first fuel, during operation, and a second fluid channel to guide a second fluid, particularly a second fuel, during operation.
  • the second fluid channel is free of passages to the first fluid channel.
  • the burner component comprises at least one first hole to provide a first passage from the first fluid channel through a wall of the burner component for supplying the first fluid into a burner space during operation and at least one second hole to provide a second passage from the second fluid channel through the wall of the burner component for supplying the second fluid into the burner space during operation.
  • the burner component further comprises a helically shaped separating barrier between the first fluid channel and the second fluid channel.
  • burner space not only the main combustion chamber is considered, but also a mixing chamber or swirler passages.
  • first fluid channel and the second fluid channel are arranged in a twisted manner, so that fluid travelling through one of the channels follows a helical path through the burner component.
  • the invention allows guiding of two different fluids in a very compact cross-section. Furthermore it allows to integrate fluid channels into a solid component so that no external pipes need to be attached to an exterior of a burner component.
  • the invention is particularly advantageous with the fluid channels have exit holes - the mentioned first and second holes - through which the delivered fluid can exit the burner component for being injected into a combustion space or into a passage through which air travels.
  • the exit holes can be located very close to another which would not be possible if two standard pipes would be used.
  • the exit holes positions and exit holes sizes can be optimised for different fuel types, e.g. the first fluid channel and its exit holes are designed for supply natural gas of a specific type and the second fluid channel and its exit holes are designed for a different fuel, e.g. hydrogen, a different natural gas, liquid fuel of specific composition, diesel.
  • the same burner component can be used to operate the gas turbine engine with two different fuel types. No hardware adaptions are needed if the operation is switched from one fuel type to another.
  • This design can even be extended for three or fluid channels, which all are twisted to another. This would allow a wide range of operation in respect of fuel flexibility.
  • the burner component is a part of a combustor of a gas turbine engine, particularly a swirler vane or swirler wing which is also used to inject fuel into a to be swirled further fluid - e.g. compressed air - or a fuel lance for a burner to inject fuel into a burner space.
  • a swirler vane or swirler wing which is also used to inject fuel into a to be swirled further fluid - e.g. compressed air - or a fuel lance for a burner to inject fuel into a burner space.
  • a swirler comprises vanes or wings that have an exterior shape to guide or direct fluids between adjacent vanes or wings, and according to the invention the burner component may be such a swirler vane or wing or may be a part of such component.
  • a fuel lance may be of an elongated form, for example cylindrical, and allows egress of delivered fluids into a burner space or a passage into which the fuel lance extends.
  • the delivery of different fluids through the interior of the fuel lance is reduced in footprint.
  • exit holes dimensioning and positioning can be optimised of the given fluid type that will be passed through the respective fluid channel.
  • DLE dry low emission
  • burners can maintain its high capabilities on natural gas compositions but in parallel allows to expand its operation to other gas compositions without having the geometrical and structural limits imposed by the natural gas injection holes.
  • a customer can easily switch between the fluids depending on the fluid that is operated.
  • This feature therefore allows to expand the accepted fuel flexibility range, meaning for example a larger range of Wobbe index or a larger range of hydrogen concentration, which may be a limiting factor in prior art designs in which only one fuel line with specific exit holes are provided.
  • an operation with two different fuels will not negatively affect NOx emissions in either mode of operation, as the exit holes can be positioned and sized in a substantially optimal way.
  • helically shaped separating barrier may be twisted around a centre line and further walls of the first fluid channel and of the second fluid channel follow together substantially a tubular shape. Particularly both channels may form substantially a circular overall cross section.
  • the centre line may be straight line, e.g. for a cylindrical fuel lance, but alternatively the centre line may follow a more complex path.
  • the centre line is a circle, e.g. if the fluid channels are integrated in a cylindrical burner tip via which fuel is provided into a burner space. Available space in the cylindrical burner tip may be limited and the invention allows to integrate a fuel rail or fuel manifold - generally called "fuel channeled path" - for more than one fluid into the burner tip.
  • the exit holes may be distributed along a circumference of the burner tip.
  • the helicoid structure preferably evolves horizontally instead of vertically, when the burner tip lies in a horizontal plane.
  • the helicoidal separation wall between the two gas passages within the available fuel channeled path may allow the use of additive manufacturing also when developed horizontally.
  • a confining wall for the thread may be preferably not cylindrical, instead the two threaded passages should have preferably a circular section area. Such a vertical helicoid could be useful when the fuel or gas holes for the two different fluids or fuels need to be placed along a vertical line.
  • exit holes size and positioning can be adapted to the specific fuel type which is anticipated to be provided during operation.
  • more than two holes of the at least one first hole of the first fluid channel may be arranged substantially on a straight line. Additionally or alternatively more than two holes of the at least one second hole of the second fluid channel may be arranged also on a straight line.
  • the mentioned two straight lines may be optionally a common straight line. Note that deviations from a perfect straight line obviously are also possible.
  • the geometrical orientation of the at least one first hole and of the at least one second hole may be the same, i.e. the direction of the holes into the burner space is identical. This is particularly advantageous in case that the burner component is part of a swirler vane as the direction of injection into a passing by air flow may be from a preferred angle, for example an injection of fuel into a perpendicular air flow through a swirler passage between two swirler vanes.
  • the plurality of holes of the at least one first hole may define a first surface pattern of outlets on a surface of the burner component
  • the plurality of holes of the at least one second hole may define a second surface pattern of outlets on a surface of the burner component
  • a first layout of the first surface pattern and a second layout of the second surface pattern may be different to another.
  • "Layout" is understood as distribution of holes on a surface, a number of holes, and distances between adjacent holes.
  • the first fuel may have advantageously a specific number of exit holes in a specific distance to another to allow optimal operation - i.e. low NOx emission, stable combustion without flashbacks, etc. - with the first fuel, whereas a different number of exit holes and/or different specific distances will be used for the second fluid channel for operation with a second fluid, so to guarantee also optimal operation for the second fluid.
  • the at least one first hole may have identical size this would mean that possibly different amount of fuel is ejected due to different local pressure of the first fluid within the first channel.
  • several of the at least one first hole may have different first hole diameters.
  • the passage cross section of the first channel can be reduced in size along a length of the first channel.
  • the second hole diameter may be different to the first hole diameter, possibly optimised for the selected first and second fluid. For example, considering the holes are arranged in an order in direction of a fluid flow through the respective fluid channels, an initial hole of the at least one first hole may have a different diameter than an initial hole of the at least one second hole, a consecutive hole of the at least one first hole may have a different diameter than a consecutive hole of the at least one second hole, and so forth.
  • the separating barrier may be integrally formed within the burner component and produced via additive manufacturing, somestimes called 3D printing.
  • a powder based system may be considered, like selective laser melting (SLM) or selective laser sintering, wherein successive layers are selectively fused to build a body of the burner component.
  • SLM selective laser melting
  • Particularly walls of the first fluid channel, wall of the second fluid channel, and the helically shaped separating barrier are physically fused together, while void spaces forming conduits for the first fluid channel, the second fluid channel, the at least one first hole, and the at least one second hole will only be filled temporarily with loose powder which will be removed again during the manufacturing process.
  • the invention is directed to at least two channels that are twisted about another.
  • the channels may be arranged in form of a double helix. If a terminology is used that is common in the field of threads, e.g. for screws and bolts, this twisted design defines a double-start or a multiple-start thread.
  • the "start" can be considered the inlets to the fluid channels at a supply end.
  • Double-start thread means that exactly two channels are part of the twisted design. In other words, two barriers are turned around a central line of symmetry and define the separating barrier. A “double-start thread” may also be called “double thread screw”.
  • Multiple-start means that multiple channels are part of the twisted design. In consequence also multiple barriers are turned around a central line of symmetry and define the separating barrier.
  • Lead defines the distance taken in direction of the central line until when a specific fluid has performed one complete 360° rotation about the central line.
  • Pitch defines substantially the distance taken in direction of the central line between the two barriers.
  • Pitch is the distance from a crest of one thread of the separating barrier to the next crest.
  • the separating barrier is twisted about a central line.
  • the shape is quite equal to a helicoid as defined in Geometry as mathematical science.
  • the separating barrier may comprise at least two helicoid walls twisted around a common centre line, the two helicoid walls being displaced to another along the common centre line. This may also be called “closed right ruled generalized helicoid”.
  • the separating barrier is wrapped around a central cylinder.
  • the shape is similar to a cylinder with an external thread applied on its lateral surface.
  • the invention is not only directed to a burner component, but also to a burner as such, particularly a burner of a gas turbine engine.
  • a burner may have multiple swirler vanes which are arranged according to the previously explained design.
  • the swirler vanes may be arranged about a burner axis and define swirler passages for air into which the first fluid is provided via the first fluid channel and a second fluid is provided via the second fluid channel, both fluids being injected into the swirler passages during operation.
  • the swirler vanes may be arranged about a burner axis.
  • the swirler may be an axial or a radial swirler. Alternatively the swirlers may be angled such that to the burner axis.
  • such a burner may have a fuel lance that is equipped with the inventive fluid channel design.
  • inventive features can also be used in a fuel rail embedded in a body of the burner.
  • the helically shaped separating barrier may be additively manufactured. Particularly it will be generated as helicoid about a centre line.
  • the helicoid shape is especially suitable for additive manufacturing because it develops upward in a way that there is always a lower layer of material available to add the new layer.
  • undercuts can be problematic for powder based additive manufacturing, but as for the helicoid adds each new layer has an underneath layer and is only slightly overhanging the underneath layer, the helicoids can be produced with additive manufacturing, particularly if the expanse of the helicoids is oriented vertically to a base plate upon which the burner component is generated.
  • swirlers and/or a fuel lance may be generated on one common additive manufacturing generation process. If the swirlers are angled in respect of a burner axis - and the burner axis being a vertical to the base plate - the helicoids may not be generated vertically to the base plate but with a slight angle. A 25° deviation from the vertical may be possible so that the gentle overhung structures can be generated, as each layer of the layer by layer generation shows only a slight overhang.
  • the invention is also directed to a method of operation of a burner.
  • the first fluid channel and the second fluid channel can be individually controlled.
  • the method comprises the steps of: supplying a first fluid, particularly a first fuel or purging air, to the first fluid channel; supplying a second fluid, particularly a second fuel or purging air, to the second fluid channel; exhausting the first fluid from the first fluid channel via the at least one first hole into the burner space; and exhausting the second fluid from the second fluid channel via the at least one second hole into the burner space.
  • Fuel can be provided only via a single one of the fluid channels at a given time, the other channel being purged with air or non-reactive fluid.
  • both fluid channels may be used to supply a main fuel via the first fluid channel and a pilot fuel via the second fluid channel.
  • both fluid channels may be used to supply a gaseous fuel - e.g. natural gas - via the first fluid channel and a another type of fuel - e.g. liquid fuel - via the second fluid channel.
  • both fluid channels may be used to supply the same type of fuel via both fluid channels, but the amount of supply being separately controllable.
  • one of the fluid channels can also be used to inject water into a burner space.
  • the method of operation may comprise the further steps of: throttling or increasing supply of the first fluid to the first fluid channel; and/or switching over the first fluid between the first fuel and the purging air; and/or throttling or increasing supply of the second fluid to the second fluid channel; and/or switching over the second fluid between the second fuel and the purging air.
  • urging air is used to indicate that the respective channel shall be evacuated from a previously used fuel and that no fluid enters the respective channel via its exit holes in an opposite direction. Nevertheless the fluid channels can be used to specifically to inject air into the burner space to modify the swirl in the burner or to change intentionally a local fuel concentration in the burner space.
  • FIG. 1 a burner component 10 is depicted in a simplified embodiment in a magnified drawing.
  • the further figures then show more realistic embodiments.
  • Particularly an exterior shape of the burner component 10 is shown in FIG. 1 merely as a cylinder. This may be true for some real life embodiments, e.g. if the burner component 10 is a fuel lance, but in other embodiments the exterior shape may be more complex, e.g. when the burner component 10 is a swirler vane of a passage through a burner body.
  • the burner component 10 shows a helically shaped separating barrier 40 which separates two fluid channels that are twisted around each other along a centre line 41, which could be considered to be a central axis.
  • the two fluid channels are the first fluid channel 21 and the second fluid channel 22. Each of these channels define a corkscrew-like channels to guide fluids, likes gases, liquids, or mixtures of both.
  • the first fluid channel 21 is arranged to guide a first fluid 23 - indicated by an arrow.
  • the first fluid 23 is particularly a first fuel, e.g. a gaseous fuel with a specific Wobbe Index and/or further parameters.
  • the first fluid 23 could also be air, water, or a liquid fuel.
  • the first fluid 23 could be specific kind of natural gas.
  • the second fluid channel 22 is arranged to guide a second fluid 24 - indicated again by an arrow.
  • the second fluid 24 is particularly a second fuel, e.g. a gaseous fuel with a different specific Wobbe Index and/or different further parameters.
  • the second fluid 24 could also be air, water, or a liquid fuel.
  • the second fluid 24 could be specific kind of natural gas.
  • the first fluid 23 and the second fluid 24 are particularly different to another.
  • the second fluid channel 22 is free of passages to the first fluid channel 21.
  • the channels are distinct or separate to another. No mixing of the fuels occurs within the mentioned channels. This allows providing different types of fluids and/or different amount of fluids through the channels.
  • the footprint of the channels, as they are arranged helically, is small so that these channels can be incorporated in small components.
  • the first fluid channel 21 and the second fluid channel 22 are provided to deliver a fluid to specific locations at a combustor surface so that the delivered fluids can be ejected into a combustion chamber or any other location - e.g. a passage, like a swirler passage - within the combustor.
  • the burner component 10 comprises at least one first hole 25 - in FIG. 1 only one hole 25 is depicted but more could be present - to provide a first passage from the first fluid channel 21 through a wall 30 of the burner component 10 for supplying the first fluid 23 into a burner space 31 during operation.
  • the burner component 10 comprises at least one second hole 26 - in FIG. 1 two holes 26 are depicted but a different number could be present - to provide a second passage from the second fluid channel 22 through the wall 30 of the burner component 10 for supplying the second fluid 24 into the burner space 31 during operation.
  • the first fluid channel 21 and the second fluid channel 22 are delimited in the shown example by the wall 30 that follows substantially a tubular shape in which the helically shaped separating barrier 40 is located.
  • the wall 30 may also have a different form.
  • the distribution of the at least one first hole 25 and the at least one second hole 26 may be such that the injection of the guided fluids happens at different locations into the burner space 31.
  • the locations of these holes may be predefined such that the burner can adapt to different types of fuels, assuming that a stable combustion is preferred.
  • the size of these holes can be predefined such that the burner is adapted to different types of fuels. For example a low calorific fuel as a first type of fluid may be supplied via the first fluid channel 21 while the second fluid channel 22 is only purged by air. If switchover to a high calorific fuel as a second type of fluid is wanted, then the first fluid channel 21 may be purged with air and the second fluid channel 22 can deliver this high calorific fuel.
  • the locations and size of the holes are different for both channels, the combustion can be optimised for both types of fuels.
  • the at least one first hole 25 has a first hole diameter 42 and the at least one second hole 26 has a second hole diameter 43 different to the first hole diameter 42.
  • the holes sizes (42 versus 43) may be different by 5% to 40%.
  • the appropriate size may be calculated or determined by experiments.
  • the two helically formed fluid channels (21 and 22) extend along the centre line 41.
  • the distribution of a plurality of the first holes 25 and a plurality of the second holes 26 is different to another.
  • a first one of the second holes 26 may be in between two consecutive ones of the first holes 25, as shown in FIG. 1 .
  • the orientation of the holes according to FIG. 1 is in the same direction. That means that all holes are arranged on a straight line. It may be advantageous though if the holes may be injecting the fluids into the burner space 31 in a different angle. In that case at a plurality of the first holes 25 are arranged on a first line, while the plurality of the second holes 26 are arranged on a second line, wherein these two lines are not identical.
  • the separating barrier 40 comprises at least two helicoid walls 50 and 51 that are twisted around the common centre line 41.
  • the two helicoid walls 50, 51 are displaced to another along the common centre line 41. If this structure is compared to the technology of threads this configuration would be called a double-start thread. Possibly - but not shown - more than two fluid channels can be twisted about the centre line 41. This configuration would be called a multiple-start thread.
  • the separating barrier 40 is integrally formed within the burner component 10, particularly produced via additive manufacturing.
  • One advantageous technique is called selective laser melting (SLM).
  • SLM selective laser melting
  • the helicoids shape would be especially suitable for additive manufacturing because it develops upward in a way that there is always a lower layer of material available to add the new layer during manufacturing.
  • a powder based additive manufacturing process may be performed such that the wall 30 and the helically shaped separating barrier 40 are generated layer by layer such that powder is distributed and a laser fuses a layer of powder with an underlying solidified structure. This will be performed repetitively layer by layer.
  • the laser for fusing of a layer of powder is slightly repositioned after every layer so that layer by layer a helicoids structure is generated.
  • the helically shaped separating barrier 40 will be formed as one solid component together with the wall 30.
  • Further parts of the burner component 10 may also be generated by additive manufacturing in the same manufacturing process. For example a complete swirler wing may be generated as one single component. Possibly even the complete swirler comprised of several swirler wings could be generated in an additive manufacturing process. Finally, even a complete burner including one or several of these inventive structures can be generated in an additive manufacturing process so that the complete burner is one single solid component.
  • FIG. 2 a burner is shown in a sectional view which is attached to a combustion chamber 309.
  • FIG. 5 shows the same burner in a three dimensional view.
  • the burner comprises a fuel lance 304 and a swirler with swirler wings 303.
  • a central gaseous fuel may be provided via holes 301 located at the fuel lance 304.
  • the swirler wings 303 - also called as swirler vanes - define passages for air between the swirler wings 303.
  • So called main gaseous fuel may be provided via holes 300 on the swirler wings 303.
  • Both, the fuel lance 304 and the swirler wings 303, or each element individually, can be equipped with a helicoid fuel supply as explained in accordance with FIG. 1 .
  • the exemplary burner of FIG.2 and FIG. 5 shows further downstream a mixer 305 in which the air and fuel can continue to mix.
  • Holes 306 for air may be located at a surrounding wall of the mixer 305. These holes 306 allow to generate a film cooling effect, as expressed by arrows for film cooling air 307.
  • a burner tip 308 follows the mixer 305.
  • a wall of the burner tip 308 may optionally also be equipped with a helicoid fuel supply for pilot fuel as explained in accordance with FIG. 1 . Therefore pilot fuel could be guided via inner channels or inner manifolds embedded in a body of the burner tip 308.
  • Pilot fuel injectors 302, provided with fuel via the embedded helicoids fuel supply (which is not shown in FIG.2 but later indicated in FIG. 5 ) are also indicated in FIG. 2 .
  • FIG. 3 shows an enlarged cross section of the swirler.
  • the swirler wings are referenced by numeral 100.
  • Each swirler wing 100 is burner component 10, as previously introduced.
  • One swirler wing 100 at the top of the figure shows a cross section of the two twisted fluid channels 21 and 22, as introduced in accordance with FIG. 1 .
  • a second cross section is shown for a further swirler wing 100 which is position at a downward position in FIG. 3 .
  • the latter swirler wing 100 also shows several first holes 25 and several second holes 26. In the example, and depicted from left to right, two holes 25 follow another, and afterwards the holes 25 and 26 are arranged alternatingly. This is just an example how the holes could be positioned differently to another.
  • a third swirler wing 100 is shown substantially in the middle of the FIG.3 .
  • swirler wing 100 which is not shown in a sectional view as its position is behind the drawing plane, only the holes 25 and 26 are shown on a surface of the swirler wing 100. In the example all holes are arranged on a common line on the surface of the swirler wing 100.
  • FIG. 5 should be consulted.
  • FIG. 4 a further magnified view of two swirler wings 100 are shown, including the supply of fuel.
  • Two different fuel supplies are indicated by arrows, leading into the first fluid channel 21 and the second fluid channel 22.
  • the helicoids structure inside the swirler wing 100 is indicated in a cross sectional view for one of the swirler wings 100.
  • the helicoid internal structure for the first fluid channel 21 and the second fluid channel 22 is only indicated by dashed lines.
  • the plurality of holes 25 and 26 are indicated.
  • FIG. 5 now shows such a burner 105 in a three dimensional view.
  • swirler wings 100 are shown.
  • a burner space 31 may be represented by passages between the swirler wings 100 and/or by a central void between the swirler wings 100.
  • the swirler wings 100 again define the burner component 10.
  • Outlet holes 25 and 26 are indicated in one of the swirler wings 100.
  • the internal helicoid first and second fluid channels (21 and 22) are indicated by dashed lines.
  • a inwardly facing surface of the burner tip section 103 may be equipped with first holes 25' and second holes 26'.
  • different types of pilot fuel may be provided via the holes 25' and 26'.
  • air may be injected via these holes to enhance the turbulence.
  • water or another fluid may be injected via the holes 25' and 26'. This configuration allows injection of a specific fluid via the holes 25' while another fluid may be injected via holes 26'.
  • An internal helicoid structure is indicated by a first fluid channel 21' and a second fluid channel 21' via dashed lines.
  • FIG.3 three different locations are shown in which the inventive helicoids structure could be incorporated.
  • FIG. 6 shows a different type of burner 105.
  • a swirler vane 100' may be present, which incorporates a burner component 10, that defines two internal fluid passages as defined in accordance with FIG. 1 .
  • the helicoids fluid channels are indicated by a fuel supply line with reference numerals 21 and 22 identifying the first fluid channel 21 and the second fluid channel 22.
  • the inventive helicoid multi fuel supply can be used for different kinds of burner designs.
  • the additive manufacturing allows new opportunities in the possible shapes to be used for the main gas channels and this invention take advantage of this.
  • the current space allowed for the main gas channel is therefore divided between the first fluid and the second fluid without interfering with the injection holes diameter and/or positioning by using a helicoidally shaped wall between the first and second fluid channel.
  • the helicoids shape is especially suitable for additive manufacturing because it develops upward in a way that there is always a lower layer of material available to add the new layer.
  • the division of two main gas channels by the use of a helicoid allows to maintain untouched the predesigned natural gas injection holes while adding extra possible locations for having further injection holes for a second fluid.
  • Advanced DLE burners will maintain higher capabilities on natural gas compositions but at the same time operation can be expanded to other gas compositions without having limits imposed by the natural gas injection holes.
  • fuel supply can easily be switched between a first and a second fuel depending on the fuel that is to be used.
  • the presented features allow expanding an designed fuel flexibility range, i.e. a larger range of Wobbe index or a larger range of hydrogen concentration, that would otherwise (if only one single channel is provided in a burner with only one set of injection holes) be limited by having only one set of fuel injection holes.
  • a combustor can meet continuously very low NOx emission even when operating on different fuels, for which different fuel injection holes positions and/or dimensions are needed.
  • the two fluid channels with different fluid injection holes can be used for several modes of operation:

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP16167741.4A 2016-04-29 2016-04-29 Composant de brûleur, brûleur et leurs procédés de fabrication ou de fonctionnement pour un fonctionnement à deux carburants Withdrawn EP3239613A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP16167741.4A EP3239613A1 (fr) 2016-04-29 2016-04-29 Composant de brûleur, brûleur et leurs procédés de fabrication ou de fonctionnement pour un fonctionnement à deux carburants
PCT/EP2017/055256 WO2017186386A1 (fr) 2016-04-29 2017-03-07 Composant de brûleur, brûleur, et procédés de fabrication ou de mise en oeuvre de ceux-ci pour un fonctionnement dual-fuel
EP17710688.7A EP3417208B1 (fr) 2016-04-29 2017-03-07 Composant de brûleur et brûleur

Applications Claiming Priority (1)

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EP16167741.4A EP3239613A1 (fr) 2016-04-29 2016-04-29 Composant de brûleur, brûleur et leurs procédés de fabrication ou de fonctionnement pour un fonctionnement à deux carburants

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EP17710688.7A Active EP3417208B1 (fr) 2016-04-29 2017-03-07 Composant de brûleur et brûleur

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WO2020259918A1 (fr) * 2019-06-25 2020-12-30 Siemens Aktiengesellschaft Dispositif de combustion pour turbine à gaz
CN116467817A (zh) * 2023-06-01 2023-07-21 广东合胜厨电科技有限公司 一种基于上进风燃烧器的风道设计方法

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Publication number Priority date Publication date Assignee Title
CN116136308A (zh) 2021-11-16 2023-05-19 通用电气公司 具有压降吹扫通道的旋流器套圈板
US11994295B2 (en) 2022-02-18 2024-05-28 General Electric Company Multi pressure drop swirler ferrule plate
US12038176B2 (en) 2022-02-18 2024-07-16 General Electric Company Coupling a fuel nozzle purge flow directly to a swirler

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US2978870A (en) * 1957-12-26 1961-04-11 Gen Electric Fuel injector for a combustion chamber
EP2107300A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Ensemble de tourbillonnement avec injecteur à gaz
EP2489939A1 (fr) * 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Chambre de combustion dotée d'une section de paroi et d'un élément de bord
EP2604919A1 (fr) * 2011-12-12 2013-06-19 Siemens Aktiengesellschaft Buse à combustible pour deux carburants
US20140202163A1 (en) * 2013-01-23 2014-07-24 General Electric Company Effusion plate using additive manufacturing methods
US20150135716A1 (en) * 2012-11-21 2015-05-21 General Electric Company Anti-coking liquid cartridge

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EP3029379A1 (fr) * 2014-12-03 2016-06-08 Siemens Aktiengesellschaft Lance de carburant liquide pilote, système de carburant liquide pilote et procédé d'utilisation

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US2978870A (en) * 1957-12-26 1961-04-11 Gen Electric Fuel injector for a combustion chamber
EP2107300A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Ensemble de tourbillonnement avec injecteur à gaz
EP2489939A1 (fr) * 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Chambre de combustion dotée d'une section de paroi et d'un élément de bord
EP2604919A1 (fr) * 2011-12-12 2013-06-19 Siemens Aktiengesellschaft Buse à combustible pour deux carburants
US20150135716A1 (en) * 2012-11-21 2015-05-21 General Electric Company Anti-coking liquid cartridge
US20140202163A1 (en) * 2013-01-23 2014-07-24 General Electric Company Effusion plate using additive manufacturing methods

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Publication number Priority date Publication date Assignee Title
WO2020259918A1 (fr) * 2019-06-25 2020-12-30 Siemens Aktiengesellschaft Dispositif de combustion pour turbine à gaz
CN116467817A (zh) * 2023-06-01 2023-07-21 广东合胜厨电科技有限公司 一种基于上进风燃烧器的风道设计方法
CN116467817B (zh) * 2023-06-01 2023-11-17 广东合胜厨电科技有限公司 一种基于上进风燃烧器的风道设计方法

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EP3417208B1 (fr) 2020-08-19
EP3417208A1 (fr) 2018-12-26

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