US20130104554A1 - Burner assembly - Google Patents

Burner assembly Download PDF

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Publication number
US20130104554A1
US20130104554A1 US13/806,895 US201113806895A US2013104554A1 US 20130104554 A1 US20130104554 A1 US 20130104554A1 US 201113806895 A US201113806895 A US 201113806895A US 2013104554 A1 US2013104554 A1 US 2013104554A1
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United States
Prior art keywords
full jet
jet nozzles
attachment
peripheral line
fuel
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.)
Abandoned
Application number
US13/806,895
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English (en)
Inventor
Siegfried Bode
Timothy A. Fox
Thomas Grieb
Matthias Hase
Jürgen Meisl
Sebastian Pfadler
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Siemens AG
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Siemens AG
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Assigned to SIEMENS CANADA LIMITED reassignment SIEMENS CANADA LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FOX, TIMOTHY A.
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS CANADA LIMITED
Publication of US20130104554A1 publication Critical patent/US20130104554A1/en
Abandoned legal-status Critical Current

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    • 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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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

Definitions

  • the present invention relates to a burner assembly for a gas turbine having at least one combustor, wherein the burner assembly comprises a centrally arranged pilot burner and a number of main burners surrounding the pilot burner, wherein each of the main burners comprises a cylindrical housing having a lance which is centrally arranged therein and has a fuel channel for liquid fuel, wherein the lance is supported on the housing by means of swirl blades and an attachment is arranged on the lance in the direction of the combustor, wherein at least one liquid fuel nozzle is arranged in the attachment preferably downstream of the swirl blades and connected to the fuel channel.
  • compressed air from the compressor is supplied to the combustor.
  • the compressed air is mixed with a fuel, for example oil or gas, and the mixture is combusted in the combustor.
  • the hot combustion gases are finally supplied by way of a combustor output as a working medium to the turbine, where they expand and cool to transmit pulses to the blades, thereby performing work.
  • the vanes here serve to optimize pulse transmission.
  • the oil fuel is injected in for example by way of swirl generators, in which the oil is mixed with air.
  • the oil is made to swirl within the nozzles used for injection.
  • Such an oil nozzle is also referred to as a pressure swirl nozzle.
  • the object of the present invention is therefore to specify a burner assembly of the type mentioned in the introduction, which resolves the above problem.
  • the object is achieved with a burner assembly of the type mentioned in the introduction in that the at least one liquid fuel nozzle is embodied as a full jet nozzle and the at least one full jet nozzle has a length and diameter, the ratio of the length to the diameter being at least 1.5.
  • full jet nozzles allow the setting of the fuel profile, in particular of the radial fuel distribution, to be changed very effectively.
  • Full jet nozzles produce a full jet without interfering turbulence.
  • the full jet nozzle has the advantage that a higher preliminary fuel pressure can be converted to a greater penetration depth.
  • pressure swirl nozzles a higher preliminary pressure causes smaller drops to form, which in turn penetrate less effectively. This means that for greater penetration depth with pressure swirl nozzles a much higher pressure is required than with full jet nozzles.
  • the full jet nozzle can be embodied as a hole running in the attachment.
  • the liquid fuel nozzles configured as full jet nozzles inventively have a length to diameter ratio of at least 1.5. According to the invention this provides a liquid fuel jet exiting from the nozzle which mixes optimally with the air swirled by the swirl blades.
  • the length to diameter ratio of at least 1.5 ensures that for example steam bubble formation in the liquid fuel jet is reliably prevented and a sufficiently low turbulence level is maintained in the jet. It also ensures an adequate penetration depth of the fuel jet and good mixing behavior of the jet with the air flowing past.
  • the length to diameter ratio is advantageously selected in a range from 6 to 14. A liquid fuel jet produced by a full jet nozzle with such a length to diameter ratio behaves particularly optimally in respect of penetration depth and mixing properties.
  • At least one such full jet nozzle can be arranged in the attachment both in the main burners (which can also be referred to as main swirl generators) and also in the pilot burner respectively.
  • the attachment arranged on the lance can be a different component from the lance.
  • the attachment could also be configured from a number of pieces or as a single piece with the lance.
  • the penetration depth of the fuel can be varied specifically by adjusting the nozzle diameter, to achieve an advantageous radial fuel profile.
  • Interaction with the central pilot burner also requires optimization of the fuel and drop size distribution, primarily as a function of the relative alignment of the injection position to the pilot cone, in order thus to set the ignition of the fuel/air mixture with an advantageous time delay. This time delay between injection position and fuel combustion is largely responsible for the formation of thermoacoustic feedback, from which combustor pulsations can result.
  • the local drop size distributions and air/fuel ratios and also the axial injection position are the main influencing parameters here, which have to be adjusted as a function of local flow conditions of the combustion air.
  • the fuel and drop size distribution in the peripheral direction are optimized by means of the appropriately embodied full jet nozzles, to achieve ignition of the fuel/air mixture with an advantageous time delay.
  • the attachment to comprise a central attachment axis and the at least one full jet nozzle to comprise a central axis and the at least one full jet nozzle to be arranged in the attachment in such a manner that the central axis of the at least one full jet nozzle is at an angle of 90 degrees to the central attachment axis of the attachment.
  • the central axis of the full jet nozzle runs in the longitudinal direction of the full jet nozzle.
  • the fuel is injected essentially perpendicular to the flow direction of the air, thereby achieving a particularly large penetration depth. This allows favorable mixing with the air flowing past.
  • the attachment to comprise a central attachment axis
  • the at least one full jet nozzle to comprise a central axis
  • the at least one full jet nozzle to be arranged in the attachment in such a manner that the central axis of the at least one full jet nozzle is at an angle of between 90+/ ⁇ 30 degrees to the central attachment axis of the attachment.
  • the angle details relate to the inclination of the central axis in the direction of the central attachment axis.
  • the angle range is selected so that by inclining the central axis of the at least one full jet nozzle it is possible to set a variation of the penetration depth with essentially the same droplet size distribution and fuel injection quantity. This allows the radial fuel profile to be matched in respect of the overall burner assembly, in particular the radial fuel profile of a main burner in respect of the pilot burner.
  • the attachment can also be considered advantageous for the attachment to have an attachment surface and the at least one full jet nozzle to comprise a central axis, and the at least one full jet nozzle to be arranged in the attachment in such a manner that the central axis of the at least one full jet nozzle is perpendicular to said attachment surface.
  • the advantageous embodiment of the invention allows injection of the liquid fuel jet perpendicular to the flow direction for a region of the attachment tapering conically to an attachment tip, thereby allowing the greatest possible penetration depth for the fuel for full jet nozzles arranged in this region of the attachment.
  • the attachment can also be considered advantageous for the attachment to have an attachment surface and the at least one full jet nozzle to comprise a central axis and the at least one full jet nozzle to be arranged in the attachment in such a manner that the central axis of the at least one full jet nozzle forms an angle of ⁇ 10 degrees to +10 degrees with the surface normal of the attachment surface.
  • the surface normal runs perpendicular to the attachment surface and is to be considered in each instance in the region of the intersection of central axis and attachment surface.
  • the central axis can run in an inclined manner for this purpose both in the direction of the central attachment axis and in the peripheral direction (azimuthal angle).
  • the specified angle range of ⁇ 10 degrees to +10 degrees for the inclination of the central axis ensures a large penetration depth for the fuel jet without changing the droplet size distribution or the injected fuel quantity.
  • This allows the fuel profile to be produced around the lance to be set both in the radial and peripheral direction of the lance.
  • the number from eight to twelve full jet nozzles is preferred. A number from 6 to 16 full jet nozzles per main burner can also be seen as advantageous. A number from 8 to 20 full jet nozzles can also be considered advantageous.
  • the peripheral line here does not require a material manifestation but simply serves to describe the arrangement of the full jet nozzles.
  • the at least one peripheral line can run for example in a flat and closed manner around the lance.
  • the peripheral line can for example run in a ring shape and perpendicular to the central attachment axis.
  • Optimum conditions should be set in particular for the two special instances—injection position in the direction of the pilot flow (which can also be referred to as pilot cone flow) and in the counter direction toward the combustor outer wall.
  • injection position in the direction of the pilot flow which can also be referred to as pilot cone flow
  • pilot cone flow pilot cone flow
  • the mixture formation and atomization mechanism produced by powerful shear flows are different from in the second instance, this should be taken into account when setting the fuel profile.
  • the inventive embodiment can be realized with one or a number of the main burners, for example with every second of the main burners arranged around the pilot burner.
  • the peripheral line can run in a ring shape and perpendicular to the central attachment axis, with the full jet nozzles arranged along the peripheral line all having the same diameter.
  • the number density of the full jet nozzles increases along the peripheral line in the direction of the pilot burner. This allows a higher fuel concentration to be produced in the direction of the pilot burner with the same radial fuel profile.
  • full jet nozzles can also be considered advantageous for full jet nozzles to be arranged along at least one peripheral line in such a manner that an inclination of the central axes of the full jet nozzles in the direction of the central attachment axis varies in the peripheral direction.
  • the angle of inclination in the direction of the central attachment axis can be selected for example between 90+/ ⁇ 20 degrees, with the angle details relating to the angle between the central axis inclined in the direction of the central attachment axis and the central attachment axis. Obtuse setting angles are therefore possible.
  • a periphery-based variation of the penetration depth can be achieved in the cited angle range, regardless of the drop size distribution and the injection quantity.
  • the central axis of every second full jet nozzle runs on the peripheral line perpendicular to the central attachment axis and the central axis of the full jet nozzle arranged in between is inclined in each instance in the direction of the central attachment axis. For example by 10 degrees from the surface normal in the direction of the central attachment axis in the flow direction.
  • the peripheral line can run for example perpendicular to the central attachment axis in a ring shape around the lance.
  • This embodiment of the invention allows an inclination in the peripheral direction (azimuthal angle) as an alternative or in addition to the inclination of the central axis in the direction of the central attachment axis.
  • This allows the interaction of the full fuel jet with the swirl flow to be set in respect of atomization. Isolated adjustment of the drop size distribution can largely be achieved over a limited range here, without producing a substantial change in the radial penetration depth.
  • This azimuthal setting of the central axis of the at least one full jet nozzle can be selected to be the same for example for all the full jet nozzles arranged along the peripheral line.
  • the azimuthal angle of inclination of the central axes could however also be selected for example as a function of the periphery.
  • the peripheral line runs perpendicular to the central attachment axis in a ring shape around the lance, with the fill jet nozzles having the same diameter along the peripheral line.
  • the central axes of the full jet nozzles run in an alternating manner, with the central axis of every second full jet nozzle running perpendicular to the attachment surface and the central axis of the full jet nozzle arranged in between having an azimuthal angle of 20 degrees to the surface normal.
  • the full jet nozzles can also be considered advantageous for the full jet nozzles to have different diameters along at least one peripheral line.
  • the different diameters result in different penetration depths for the fuel in the peripheral direction. This allows adjustment of the radial fuel profile of a main burner in respect of the overall burner assembly.
  • At least two-row arrangement of the full jet nozzles allows a much larger variation of the fuel profiles than with a single-row arrangement.
  • the at least two peripheral lines run in a ring shape and perpendicular to the central attachment axis around the lance at different axial positions.
  • An equal or different number of full jet nozzles can be arranged along the two peripheral lines. For example 4 to 10 nozzles can be arranged on each peripheral line.
  • the at least double arrangement of the peripheral lines allows better atomization of the fuel.
  • the arrangement of the full jet nozzles in two axial planes also allows fuel to be distributed in a more regular manner radially at the same peripheral position, by injecting it to different depths into the same flow line of the air flowing past at two axial positions.
  • the full jet nozzles arranged along an upstream peripheral line can also have a larger diameter than the full jet nozzles arranged along a downstream peripheral line.
  • This embodiment of the invention is advantageous when a regular radial distribution is to be achieved.
  • the full jet nozzles arranged along an upstream peripheral line can also have a smaller diameter than the full jet nozzles arranged along a downstream peripheral line.
  • This embodiment of the invention is advantageous when a narrow radial distribution is to be achieved.
  • This embodiment of the invention is advantageous in order to achieve a regular radial fuel distribution, when the fuel injected by the downstream full jet nozzles in particular has a smaller or much greater penetration depth than the fuel injected by the upstream full jet nozzles. A smaller penetration depth in particular is considered advantageous.
  • this embodiment also allows a narrow radial fuel distribution to be achieved, with the fuel injected by the downstream full jet nozzles being injected to the same radial position as the fuel injected by the upstream full jet nozzles.
  • the radial position here is selected in such a manner that the flame stabilizes at a point, the associated time delay of which cannot be initiated in the combustion system.
  • This embodiment of the invention is particularly advantageous for achieving a regular peripheral distribution of the fuel profile. It can be combined for example with a narrow or regular radial and axial distribution. A regular radial and regular axial distribution in particular is considered advantageous.
  • the radial position here is selected in such a manner that the flame stabilizes at a point, the associated time delay of which cannot be initiated in the combustion system.
  • the time delay spectrum can also be further broadened by the additional helical arrangement of the full jet nozzles.
  • a regular radial fuel profile can be achieved with the same full jet nozzle diameters.
  • This embodiment can be advantageous when an alternating periphery-based fuel distribution is required with the greatest possible shift of the time delay spectrum.
  • the arrangement of different full jet nozzle diameters here allows different radial fuel profiles to be set, with regular radial profiles being considered advantageous.
  • This embodiment of the invention is advantageous, when the radial profile is to be homogenized by enrichment of the region close to the axis.
  • the diameters of the full jet nozzles arranged along the at least one helical peripheral line can also be considered advantageous for the diameters of the full jet nozzles arranged along the at least one helical peripheral line to be configured in such a manner that the diameters increase counter to the flow direction.
  • This embodiment of the invention is advantageous when a narrow radial fuel profile is preferred.
  • the helical peripheral line may not run along a flow line.
  • This embodiment allows regular periphery-based fuel distribution, it being possible for the diameters of the full jet nozzles arranged along the peripheral line to increase or decrease in the flow direction, depending on the desired radial fuel profile.
  • the angle of inclination of the central axis of the full jet nozzles can also be varied in the flow direction toward the central attachment axis and/or in the peripheral direction along the helical peripheral line, to set the interaction of the swirled flow of air with the full fuel jet in respect of atomization as a function of the nozzle position.
  • full jet nozzles can also be considered advantageous for the full jet nozzles to be arranged along two helical peripheral lines.
  • the double helix can also run anti-parallel, thereby allowing more regular peripheral distributions to be achieved.
  • the diameters of the full jet nozzles here can all be selected to be the same size.
  • the enrichment of the fuel concentration can serve to enrich the shear flow between pilot burner and a main burner.
  • the full jet nozzles arranged along the peripheral line can have regular distances from one another and can all have the same diameter.
  • the distances and/or diameters can however all vary in a regular sequence.
  • the radial fuel profile is essential for thermoacoustic stability, as it determines the delay time between injection and combustion. The delay time in turn determines which combustor frequencies can be initiated.
  • an independent variation of the penetration depth and fuel distribution can be achieved by a sequence of combined full jet nozzle diameters along the peripheral line. For example two different diameters or more can be combined in a regular sequence.
  • the size ratios of the full jet nozzle diameters it is possible to set the radial region, in which the fuel distribution of the different nozzle diameters is superimposed.
  • the degree of overlap can also be set by selecting the peripheral positions of the full jet nozzles, in particular the mutual distances.
  • a full jet nozzle with a smaller diameter is arranged along the peripheral line between two full jet nozzles of the same diameter, to produce a fuel profile with a ring-shaped zone of a first fuel distribution and a ring-shaped zone of a second fuel distribution.
  • full jet nozzles for example can be provided on the lance.
  • a diameter between 0.5 mm and 0.7 mm can be selected for the smaller full jet nozzles and a diameter between 0.6 mm and 0.8 mm can be selected for the larger full jet nozzles.
  • the two zones can overlap, for example by arranging the full jet nozzle with the smaller diameter closer to one of the two full jet nozzles with a larger diameter.
  • the full jet nozzles arranged along at least one peripheral line can be configured in such a manner that a fuel injected by means of the nozzles has a radial fuel distribution about the central attachment axis, the fuel distribution comprising a ring-shaped zone of a first fuel distribution and a ring-shaped zone of a second fuel distribution.
  • the advantageous fuel distribution can be produced by varying the distances, diameters, angles of inclination and/or course of the peripheral line.
  • a fuel profile can be produced by means of a peripheral line running in a ring shape perpendicular to the central attachment axis, along which full jet nozzles are arranged at equal distances from one another, their diameters alternating between two different sizes.
  • the ring-shaped zone of a first fuel distribution and the ring-shaped zone of a second fuel distribution can also be considered advantageous for the ring-shaped zone of a first fuel distribution and the ring-shaped zone of a second fuel distribution to be at a distance from one another.
  • FIG. 1 shows a schematic diagram of a section through a main burner of the inventive burner assembly according to a first exemplary embodiment
  • FIG. 2 shows a schematic diagram of a perspective view of a section through the attachment 13 of the exemplary embodiment illustrated in FIG. 1 ,
  • FIG. 3 shows a schematic diagram of a section through a main burner of the inventive burner assembly according to a second exemplary embodiment
  • FIG. 4 shows a schematic diagram of a section through a main burner of the inventive burner assembly according to a third exemplary embodiment
  • FIG. 5 shows a diagram to clarify the exemplary embodiment illustrated in FIG. 4 .
  • FIG. 6 shows a schematic diagram of a section through a main burner of the inventive burner assembly according to a fourth exemplary embodiment
  • FIG. 7 shows a cross section through the attachment illustrated in FIG. 6 .
  • FIG. 8 shows a diagram to clarify the exemplary embodiment illustrated in FIG. 6 .
  • FIG. 9 shows a schematic diagram of a section through a main burner of the inventive burner assembly according to a fifth exemplary embodiment
  • FIG. 10 shows a schematic diagram of a section through a main burner of the inventive burner assembly according to a sixth exemplary embodiment
  • FIG. 11 shows a schematic diagram of a cross section through a radial fuel profile, which can be produced by means of the main burner illustrated in FIG. 10 , and
  • FIG. 12 shows a schematic diagram of a perspective view of an inventive burner assembly.
  • FIG. 1 shows a detail of an inventive burner assembly in the region of a main burner 107 .
  • Swirl blades 17 are arranged around the lance in the housing 12 of the main burner 107 .
  • the swirl blades 17 are arranged along the periphery of the lance in the housing 12 .
  • the swirl blades 17 direct a compressor air flow 15 into the part of the burner 107 leading to a combustor. The air is made to swirl by the swirl blades 17 .
  • the lance also comprises a fuel channel 16 .
  • the burner 107 further comprises an attachment 13 on the side leading to a combustor.
  • the attachment 13 can be welded or screwed to the lance for example.
  • the fuel nozzles are preferably arranged downstream of the swirl blades 17 in the attachment 13 and are thus connected for flow purposes to the fuel channel 16 , shown here as an oil channel.
  • the inventive burner assembly preferably comprises eight such main burners 107 arranged in a circle (see FIG. 12 ).
  • the main burners 107 here are arranged around a pilot burner (see FIG. 12 ) with pilot cone.
  • Pressure swirl nozzles used hitherto in the prior art exhibit significant pressure pulsations. However major problems then occur in basic load operation. This is now avoided with the aid of the invention.
  • the plurality of fuel nozzles are therefore embodied as full jet nozzles 1 according to the invention.
  • the embodiment of the nozzle as a full jet nozzle 1 , the full jet nozzle size and arrangement allow the penetration depth of the fuel to be set so that an advantageous fuel profile results.
  • the parameters available here are the diameters of the full jet nozzles 1 and the number of full jet nozzles 1 .
  • the fuel distribution is set so that ignition of the fuel/air mixture takes place with an advantageous time delay.
  • the time delay between injection and combustion of the fuel is significant for the formation of thermoacoustic feedback loops, from which combustor pulsations can result.
  • the full jet nozzles 1 have a length, the length to diameter ratio being at least 1.5, to achieve thorough mixing. It means that the divergence of the full jet is small enough to prevent drops spinning off in an unwanted manner.
  • full jet nozzles 1 therefore allows the setting of the fuel profile, in particular of the radial fuel distribution, to be changed very effectively.
  • the full jet nozzle 1 has the advantage that a higher preliminary fuel pressure can be converted primarily to a greater penetration depth.
  • the pressure swirl nozzles of the prior art smaller drops are formed due to a higher preliminary pressure and these penetrate less effectively. Therefore a much higher pressure is required for a greater penetration depth with pressure swirl nozzles than with full jet nozzles. There is therefore no need for expensive pumps, which can supply a greater preliminary fuel pressure, or pipe systems with high pressure stages for example with the full jet nozzle 1 .
  • FIG. 2 shows a schematic diagram of a perspective view of a section through the attachment 13 .
  • the central attachment axis of the attachment 13 is shown with the reference character 18 .
  • the attachment 13 is embodied to taper conically in the direction of the combustor. It comprises a number of full jet nozzles 1 , in the present exemplary embodiment four.
  • the full jet nozzles 1 are arranged on the outer periphery of the attachment 13 .
  • the central axes of the full jet nozzles 1 are shown with the reference character 19 .
  • the central axes 19 of the full jet nozzles 1 are at an angle 20 to the central attachment axis 18 of the attachment 13 .
  • the fuel enters the attachment 13 through the fuel channel 16 along the flow direction shown with the reference character 26 .
  • the fuel is then injected by the full jet nozzles 1 in direction 25 into the air flow coming from the swirl blades 17 .
  • the central axis 19 of the full jet nozzles 1 is arranged essentially perpendicular (90 degrees) to the central attachment axis 18 of the full jet nozzles 1 .
  • the central axis 19 of the nozzle 1 can also be perpendicular to the attachment surface.
  • the jet is thus introduced into the air flow in a perpendicular manner, resulting in thorough mixing.
  • An arrangement of 90+/ ⁇ 30 degrees, in particular 90+/ ⁇ 10 degrees, from the central axis 19 of the full jet nozzles 1 to the axis 18 or the attachment surface however also produces a very advantageous assembly.
  • the attachment 13 comprises a cylindrical part 130 and a part 140 tapering conically in the direction of a combustor.
  • the conical part 140 can have a cone angle of 10 to 20 degrees. This embodiment prevents the flow being fractured at the attachment tip.
  • the full jet nozzles 1 here can be arranged on the conically tapering part 140 of the attachment 13 .
  • the position of the full jet nozzles 1 can change as a function of the automatic ignition of the mixture.
  • eight to twelve full jet nozzles are preferably used (not shown) per attachment 13 .
  • Six to sixteen full jet nozzles 1 are also advantageous. These are distributed in a regular manner on the periphery of the attachment 13 .
  • the full jet nozzles 1 can be configured as holes in the attachment 13 .
  • a length to diameter ratio of six to fourteen in particular is advantageous in respect of mixing.
  • the length of the full jet nozzle is shown with the reference character 32 .
  • the diameter of the full jet nozzle is shown with the reference character 33 .
  • the preferred diameter of the full jet nozzles 1 here is 0.55 mm to 0.8 mm but 0.5 mm to 1 mm (not shown) is also advantageous.
  • Combinations of eight nozzles with a diameter of 0.7 to 0.8 mm or of ten nozzles with 0.6 to 0.7 mm diameter and twelve nozzles with 0.55 mm to 0.65 mm diameter (also not shown) in particular are advantageous.
  • the full jet nozzles 1 also allow easy adjustment for different thermodynamic conditions, which result for example in a changed air crossflow speed, air density or fuel mass flow, by adjusting the diameters 33 of the full jet nozzles 1 correspondingly.
  • FIG. 3 shows a detail of the inventive burner assembly in the region of a main burner 107 .
  • the main burner 107 comprises a cylindrical housing 12 , in which a lance 14 is arranged centrally, being enclosed by a main swirler 10 .
  • the schematically illustrated main swirler 10 has swirl blades 17 (not shown), which support the lance 14 on the housing 12 .
  • a compressor air flow 15 flows through the main swirler 10 in the direction of the combustor (not shown).
  • the lance 14 extends along a central attachment axis 18 , on which an attachment 13 is arranged in the direction of the combustor (not shown).
  • the attachment 13 has a cylindrical part 130 and transitions into a conically tapering part 140 in the direction of the combustor.
  • full jet nozzles 1 (shown by circles), which are arranged along a peripheral line 11 that runs perpendicular to the central attachment axis 18 and in a ring shape around the central attachment axis 18 .
  • the outlets of the full jet nozzles 1 opening toward the attachment surface are arranged along a peripheral line 11 running on the attachment surface, the peripheral line 11 running in the peripheral direction 22 around the attachment 13 .
  • Half of the peripheral line 11 is shown in the sectional view.
  • the peripheral direction 22 does not necessarily run perpendicular to the central attachment axis 18 . It is only important here that the peripheral line 11 running in a peripheral direction 22 on the attachment surface encircles the central attachment axis 18 .
  • the peripheral line 11 illustrated in FIG. 3 does not have to have an actual correspondence but simply serves to describe the full jet nozzle arrangement.
  • the number density of the full jet nozzles 1 varies in the peripheral direction 22 , as the number density of the full jet nozzles 1 above the central attachment axis 18 is greater than below the central attachment axis 18 .
  • the side of the attachment 13 shown above the central attachment axis 18 faces the pilot burner (not shown).
  • the central axes 19 of the full jet nozzles 1 run perpendicular to the attachment surface. In other words each of the central axes 19 runs in the direction of a surface normal 23 .
  • randomly selected surface normals 23 a , 23 b , 23 c are shown in FIG. 3 , the surface normal 23 b being shown in the outlet region of a full jet nozzle 1 .
  • FIG. 4 shows a schematic sectional view of a detail of an inventive burner assembly in the region of a main burner 107 according to a third exemplary embodiment.
  • the structure of the main burner here corresponds to the exemplary embodiment illustrated in FIG. 3 apart from the arrangement of the full jet nozzles 1 .
  • these are arranged along a peripheral line 11 running in a ring shape and perpendicular to the main attachment line 18 .
  • the inclination of the central axes 19 of the full jet nozzles here runs in an alternating manner along the peripheral line 11 .
  • the central axis 19 of the full jet nozzle 1 following on the peripheral line 11 is inclined 10 degrees from this in the direction of the central attachment axis 18 in the flow direction of the compressor air flow 15 . In this sense the inclination of the central axes 19 of the full jet nozzles 1 varies in the peripheral direction 22 along the peripheral line 11 .
  • the marked angle ⁇ shows the angle between central axis 19 and attachment surface.
  • FIG. 5 shows a diagram to clarify the exemplary embodiment illustrated in FIG. 4 .
  • it shows the angle ⁇ between central axis 19 and attachment surface of several full jet nozzles 1 as a function of the peripheral position along the peripheral line 11 .
  • the angle ⁇ is referred to as the setting angle.
  • FIG. 6 shows a schematic sectional view of a main burner 107 according to a fourth exemplary embodiment.
  • the structure of the main burner 07 here corresponds to the exemplary embodiment illustrated in FIG. 3 apart from the arrangement of the full jet nozzles 1 .
  • the full jet nozzles 1 are arranged along a peripheral line 11 running in a ring shape and perpendicular to the main attachment line 18 .
  • the inclination of the central axes 19 of the full jet nozzles here runs in an alternating manner along the peripheral line 11 .
  • the central axis 19 of the full jet nozzle 1 following on the peripheral line 11 is inclined 20 degrees from this in the peripheral direction 22 .
  • the angle of inclination in the peripheral direction 22 can also be referred to as the azimuthal angle.
  • FIG. 7 shows a cross section through the attachment 13 at the axial height of the peripheral line 11 to clarify the fourth exemplary embodiment illustrated in FIG. 6 .
  • the full jet nozzles 1 arranged along the peripheral line 11 are shown by circles. In other words the openings of the full jet nozzles are arranged along the peripheral line 11 .
  • the central axes 19 of the full jet nozzles 1 and therefore also the direction 25 of the fuel jet leaving the full jet nozzle run in an alternating manner perpendicular to the attachment surface and are therefore inclined in the direction of a surface normal 23 or 20 degrees from this in the peripheral direction 22 .
  • the angle between surface normal 23 and central axis 19 is shown as iv.
  • FIG. 8 shows a diagram to clarify the fourth exemplary embodiment illustrated in FIG. 6 .
  • it shows the angle between central axis 19 and surface normal 23 in the peripheral direction (azimuthal angle ⁇ ) of several full jet nozzles 1 as a function of the peripheral position along the peripheral line 11 .
  • FIG. 9 shows a schematic sectional view of a main burner 107 according to a fifth exemplary embodiment.
  • the structure of the main burner 107 here corresponds to the exemplary embodiment illustrated in FIG. 3 apart from the arrangement of the full jet nozzles 1 . These are arranged along a helical peripheral line 11 , the diameter of the full jet nozzles 1 increasing counter to the flow direction of the compressor air flow 15 .
  • the air which is swirled as it flows through the main swirler 10 , flows along flow lines 27 along the attachment 13 in the direction of the combustor (not shown).
  • the helical peripheral line 11 here runs in such a manner that the full jet nozzles 1 are arranged on a common flow line 27 .
  • FIG. 10 shows a schematic sectional view of a main burner 107 according to a sixth exemplary embodiment.
  • the structure of the main burner 107 here corresponds to the exemplary embodiment illustrated in FIG. 3 apart from the arrangement of the full jet nozzles 1 . These are arranged along a peripheral line 11 running in a ring shape and perpendicular to the central attachment axis, the full jet nozzles 1 having distances from one another and diameters along the peripheral line 11 , the sequence of which is repeated along the peripheral line 11 .
  • the full jet nozzles 1 are an equal distance from one another, with a full jet nozzle 1 with a smaller diameter arranged between two full jet nozzles 1 of the same diameter.
  • the central axes (not shown) of the full jet nozzles 1 point perpendicular to the central attachment axis 18 in a radial direction.
  • FIG. 11 shows a fuel profile that can be produced by means of the full jet nozzles 1 illustrated in FIG. 10 .
  • the injected fuel here produces a radial fuel distribution around the central attachment axis 18 , the fuel channel 16 and the attachment 13 , the fuel distribution comprising a ring-shaped zone of a first fuel distribution 28 from the full jet nozzles with large diameter and a ring-shaped zone of a second fuel distribution 29 from the full jet nozzles with small diameter.
  • the fuel distribution from an individual full jet nozzle with large diameter is shown with the reference character 30 .
  • the fuel distribution from an individual full jet nozzle with small diameter is shown with the reference character 31 .
  • the selected distances between the full jet nozzles 1 and the size ratios of the diameters mean that the ring-shaped zone of a first fuel distribution 28 and the ring-shaped zone of a second fuel distribution 29 overlap.
  • FIG. 12 shows an inventive burner assembly 108 with a pilot burner 106 with pilot cone 109 and a plurality of main burners 107 arranged around the pilot burner 106 .
  • Each of the main burners 107 comprises an essentially cylindrical housing 12 , in which a lance is arranged centrally, with an attachment 13 arranged on the lance in the direction of a combustor (not shown).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
US13/806,895 2010-07-01 2011-07-01 Burner assembly Abandoned US20130104554A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10168107A EP2402652A1 (de) 2010-07-01 2010-07-01 Brenner
EP10168107.0 2010-07-01
PCT/EP2011/061101 WO2012001141A1 (de) 2010-07-01 2011-07-01 Brenneranordnung

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US13/806,895 Abandoned US20130104554A1 (en) 2010-07-01 2011-07-01 Burner assembly

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EP (2) EP2402652A1 (enExample)
JP (1) JP6005040B2 (enExample)
WO (1) WO2012001141A1 (enExample)

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US20180094817A1 (en) * 2016-10-03 2018-04-05 United Technologies Corporation Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US20180163629A1 (en) * 2016-10-03 2018-06-14 United Technologies Corporation Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine
US20180313541A1 (en) * 2017-04-28 2018-11-01 Doosan Heavy Industries & Construction Co., Ltd. Device to Correct Flow Non-Uniformity Within a Combustion System
US10443855B2 (en) 2014-10-23 2019-10-15 Siemens Aktiengesellschaft Flexible fuel combustion system for turbine engines
US20220082257A1 (en) * 2020-09-11 2022-03-17 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US20220205637A1 (en) * 2020-12-30 2022-06-30 General Electric Company Mitigating combustion dynamics using varying liquid fuel cartridges
US20220214043A1 (en) * 2021-01-06 2022-07-07 Doosan Heavy Industries & Construction Co., Ltd. Fuel nozzle, fuel nozzle module having the same, and combustor
US11499481B2 (en) 2014-07-02 2022-11-15 Nuovo Pignone Tecnologie Srl Fuel distribution device, gas turbine engine and mounting method
US20230065831A1 (en) * 2021-08-24 2023-03-02 Solar Turbines Incorporated Micromix fuel injection air nozzles
US20230138744A1 (en) * 2020-03-17 2023-05-04 Dometic Sweden Ab Heating Apparatus, Recreational Vehicle With Heating Apparatus and Method for Heating Fluids in a Recreational Vehicle
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US9759425B2 (en) * 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
DE102014102777B4 (de) 2013-03-12 2023-07-20 General Electric Company System mit Vielrohr-Brennstoffdüse mit mehreren Brennstoffinjektoren
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
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US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US20140338339A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US20160209040A1 (en) * 2013-09-27 2016-07-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and gas turbine engine equipped with same
CN105473944A (zh) * 2013-09-27 2016-04-06 三菱日立电力系统株式会社 燃气涡轮燃烧器和具备该燃气涡轮燃烧器的燃气涡轮发动机
US11499481B2 (en) 2014-07-02 2022-11-15 Nuovo Pignone Tecnologie Srl Fuel distribution device, gas turbine engine and mounting method
CN104315540A (zh) * 2014-09-26 2015-01-28 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机燃烧室预混燃料喷嘴
US10443855B2 (en) 2014-10-23 2019-10-15 Siemens Aktiengesellschaft Flexible fuel combustion system for turbine engines
US20170328568A1 (en) * 2014-11-26 2017-11-16 Siemens Aktiengesellschaft Fuel lance with means for interacting with a flow of air and improve breakage of an ejected liquid jet of fuel
US11365884B2 (en) 2016-10-03 2022-06-21 Raytheon Technologies Corporation Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10393030B2 (en) * 2016-10-03 2019-08-27 United Technologies Corporation Pilot injector fuel shifting in an axial staged combustor for a gas turbine engine
US20180094817A1 (en) * 2016-10-03 2018-04-05 United Technologies Corporation Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10508811B2 (en) * 2016-10-03 2019-12-17 United Technologies Corporation Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US20180163629A1 (en) * 2016-10-03 2018-06-14 United Technologies Corporation Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine
US10739003B2 (en) * 2016-10-03 2020-08-11 United Technologies Corporation Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10738704B2 (en) * 2016-10-03 2020-08-11 Raytheon Technologies Corporation Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine
US20180094590A1 (en) * 2016-10-03 2018-04-05 United Technologies Corporatoin Pilot injector fuel shifting in an axial staged combustor for a gas turbine engine
US20180094814A1 (en) * 2016-10-03 2018-04-05 United Technologies Corporation Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10584877B2 (en) * 2017-04-28 2020-03-10 DOOSAN Heavy Industries Construction Co., LTD Device to correct flow non-uniformity within a combustion system
US11137142B2 (en) 2017-04-28 2021-10-05 Doosan Heavy Industries & Construction Co., Ltd. Device to correct flow non-uniformity within a combustion system
US20180313541A1 (en) * 2017-04-28 2018-11-01 Doosan Heavy Industries & Construction Co., Ltd. Device to Correct Flow Non-Uniformity Within a Combustion System
US20230138744A1 (en) * 2020-03-17 2023-05-04 Dometic Sweden Ab Heating Apparatus, Recreational Vehicle With Heating Apparatus and Method for Heating Fluids in a Recreational Vehicle
US11421883B2 (en) * 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US20220082257A1 (en) * 2020-09-11 2022-03-17 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US20220205637A1 (en) * 2020-12-30 2022-06-30 General Electric Company Mitigating combustion dynamics using varying liquid fuel cartridges
US20220214043A1 (en) * 2021-01-06 2022-07-07 Doosan Heavy Industries & Construction Co., Ltd. Fuel nozzle, fuel nozzle module having the same, and combustor
US11680710B2 (en) * 2021-01-06 2023-06-20 Doosan Enerbility Co., Ltd. Fuel nozzle, fuel nozzle module having the same, and combustor
US20230065831A1 (en) * 2021-08-24 2023-03-02 Solar Turbines Incorporated Micromix fuel injection air nozzles
US12025311B2 (en) * 2021-08-24 2024-07-02 Solar Turbines Incorporated Micromix fuel injection air nozzles
WO2024228777A3 (en) * 2023-04-28 2024-12-12 Siemens Energy Global GmbH & Co. KG Fuel lance for burner of gas turbine engine

Also Published As

Publication number Publication date
EP2588805A1 (de) 2013-05-08
EP2588805B1 (de) 2016-04-20
JP6005040B2 (ja) 2016-10-12
EP2402652A1 (de) 2012-01-04
JP2013529771A (ja) 2013-07-22
WO2012001141A1 (de) 2012-01-05

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