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WO2012001141A1 - Ensemble brûleur - Google Patents

Ensemble brûleur Download PDF

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Publication number
WO2012001141A1
WO2012001141A1 PCT/EP2011/061101 EP2011061101W WO2012001141A1 WO 2012001141 A1 WO2012001141 A1 WO 2012001141A1 EP 2011061101 W EP2011061101 W EP 2011061101W WO 2012001141 A1 WO2012001141 A1 WO 2012001141A1
Authority
WO
WIPO (PCT)
Prior art keywords
jet nozzles
full
attachment
along
burner
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.)
Ceased
Application number
PCT/EP2011/061101
Other languages
German (de)
English (en)
Inventor
Siegfried Bode
Matthias Hase
Jürgen MEISL
Timothy A. Fox
Sebastian Pfadler
Thomas Grieb
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 Canada Ltd
Siemens AG
Siemens Corp
Original Assignee
Siemens Canada Ltd
Siemens AG
Siemens Corp
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 Canada Ltd, Siemens AG, Siemens Corp filed Critical Siemens Canada Ltd
Priority to EP11728849.8A priority Critical patent/EP2588805B1/fr
Priority to JP2013517313A priority patent/JP6005040B2/ja
Priority to US13/806,895 priority patent/US20130104554A1/en
Publication of WO2012001141A1 publication Critical patent/WO2012001141A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F23R3/34—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 combustion chamber, the burner assembly comprising a centrally located pilot burner and a plurality of main burners surrounding the pilot burner, each of the main burners comprising a cylindrical housing having a lance centrally disposed therein and having a liquid fuel fuel passage wherein the lance is supported by swirl vanes on the housing and in the direction of the combustion chamber, an attachment is arranged on the lance, wherein at least one liquid fuel nozzle in the
  • Attachment is preferably arranged downstream of the swirl blades and connected to the fuel channel.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • the vanes serve to optimize the momentum transfer.
  • Swirl generator in which the oil is mixed with air.
  • the oil within the nozzles used for the injection into a swirling motion is added.
  • This oil nozzle is also called pressure-swirl nozzle
  • the oil nozzles can not be arranged so that the Mixing of the fuel with the air leads to an optimal result in terms of pressure pulsations.
  • the object of the present invention is therefore to provide a burner assembly of the type mentioned, which solves the above problem.
  • At least one liquid fuel nozzle is configured as a full jet nozzle and the at least one solid jet nozzle has a length and a diameter, wherein the length to diameter ratio is at least 1.5.
  • Fuel distribution can be changed very effectively.
  • Fuel admission pressure is converted into a larger penetration depth.
  • the jet nozzle may be configured as a bore extending in the attachment.
  • the liquid fuel nozzles designed as full jet nozzles according to the invention have a length to diameter ratio of at least 1.5.
  • a the nozzle issuing liquid fuel jet is provided which optimally mixes with the twisted by the swirl blades air.
  • the length to diameter ratio of at least 1.5 ensures that, for example, a
  • Length to diameter ratio selected in a range of 6 to 14.
  • a liquid fuel jet produced by a full jet nozzle with this length to diameter ratio behaves particularly optimally with regard to penetration depth and mixing properties.
  • Main swirl generators can be designated) as well as in the pilot burner at least one such full jet nozzle may be arranged in the essay.
  • the attachment arranged on the lance can be a component that is different from the lance.
  • the essay could also be made in one piece or in one piece with the lance.
  • Combustion system consisting of a central
  • Pilot burner with pilot cone and the main burner arranged around the pilot burner In principle, the penetration depth of the fuel by adjusting the
  • Nozzle diameter can be selectively varied to one
  • An advantageous embodiment of the invention may provide that the attachment comprises an attachment center axis, and the at least one solid jet nozzle comprises a central axis and the
  • At least one full jet nozzle is arranged in the attachment such that the central axis of the at least one full jet nozzle makes an angle of 90 ° to the center attachment axis of the
  • the center axis of the jet nozzle runs in the longitudinal direction of the jet nozzle.
  • the fuel is substantially transversely to
  • the attachment comprises a center attachment axis, the at least one
  • Full jet nozzle comprises a central axis and the at least one jet nozzle is arranged in the attachment so that the central axis of the at least one jet nozzle has an angle between 90 ° +/- 30 ° degrees to the center attachment axis of the attachment.
  • the angle refers to the inclination of the central axis in the direction of the center attachment axis.
  • the angular range is selected such that by tilting the central axis of the at least one full jet nozzle a variation of
  • Adjustment depth can be adjusted with substantially the same droplet size distribution and injection quantity of the fuel. This allows the tuning of the radial fuel profile with respect to the entire burner assembly, particularly the radial fuel profile of a main burner with respect to the pilot burner.
  • the attachment can also be considered advantageous for the attachment to have an attachment surface and the at least one solid jet nozzle to comprise a central axis, and the at least one solid jet nozzle to be arranged in the attachment so that the central axis of the at least one full jet nozzle is perpendicular to this attachment surface.
  • the advantageous embodiment of the invention makes it possible for a region of the attachment tapering towards an attachment tip to inject the liquid fuel jet transversely to the flow direction, thereby enabling the greatest possible penetration depth of the fuel for jet nozzles arranged in this region of the attachment.
  • Attachment has a top surface and the at least one full jet nozzle comprises a central axis, and the
  • At least one full jet nozzle is arranged in the attachment so that the central axis of the at least one full jet nozzle with the surface normal of the attachment surface a
  • the surface normal is perpendicular to the
  • the central axis can be used for this purpose both in the direction of the center attachment axis and in Circumferential (azimuthal angle) inclined.
  • the specified angle range of -10 degrees to + 10 degrees for the inclination of the center axis ensures a high penetration depth of the fuel jet without the droplet size distribution or the injected amount of fuel to change. This allows adjustment of the lance to be created
  • Diameter are provided, the diameter is between 0.55mm-0.8mm.
  • the number of eight to twelve jet nozzles is preferred. Also can be a number of 6 to 16 jet nozzles each
  • Main burner to be called beneficial. Also, a number of 8 to 20 jet nozzles may be considered advantageous.
  • Full jet nozzles are provided with a diameter between 0.6mm-0.7mm.
  • Full jet nozzles are provided with a diameter between 0, 55mm-0, 65mm.
  • a further advantageous embodiment of the invention can provide that full jet nozzles are provided with a diameter between 0.7mm-0.8mm. According to a further advantageous embodiment of the invention
  • Invention may be provided that in at least one of the main burner full jet nozzles along at least one extending around the tower around circumferential line are arranged.
  • the perimeter does not require any material realization, but merely serves to describe the arrangement of the full jet nozzles.
  • the circumferential line can run flat and closed around the lance.
  • the circumferential line may extend in a ring shape and perpendicular to the center attachment axis.
  • Pilot burner with pilot cone and the main burner arranged around the pilot burner requires the optimization of the fuel and droplet size distribution, especially in
  • Fuel profiles are taken into account. By increasing the number of full jet nozzles in the direction of pilot burner can be at the same radial
  • Fuel profile and thus identical penetration depth produce a higher fuel concentration in the direction of pilot burner. This allows you to adjust the flame position.
  • the embodiment according to the invention can be implemented in one or more of the main burners. For example, every other one of the main burners arranged around the pilot burner.
  • a further advantageous development of the invention can provide that the number density of the full-jet nozzles varies in the circumferential direction along at least one circumferential line. According to an embodiment of the advantageous
  • the circumferential line may extend in an annular manner and perpendicular to the middle attachment axis, wherein the full jet nozzles arranged along the circumferential line all have the same diameter.
  • Embodiment of the development increases the number density of full jet nozzles along the circumferential line in the direction of pilot burner. This can be at the same radial
  • Direction pilot burner can be generated.
  • Circumference varies.
  • Center attachment axis can be selected, for example, between 90 + -20 degrees, wherein the angle refers to the angle between the center axis inclined in the direction of the central attachment axis and the center attachment axis. There are thus also blunt angle of attack possible. By doing said angular range, a circumferential variation of the penetration depth can be achieved independently of the droplet size distribution and the injection quantity. It can be advantageously provided that the center axes of the full-jet nozzles arranged along the circumferential line are aligned alternately, wherein the center axes are alternately perpendicular to the central attachment axis and deviating therefrom inclined by at most 20 degrees in the direction of the center attachment axis.
  • each second full-jet nozzle runs on the circumferential line perpendicular to
  • arranged full-jet nozzle is inclined in each case in the direction of the center attachment axis. For example, from the
  • the circumferential line can, for example, perpendicular to
  • Center attachment axis run around the lance ring.
  • Full jet nozzle starting from a position perpendicular to the center axis has a tilt in the circumferential direction.
  • This embodiment of the invention allows alternatively or in addition to the inclination of the central axis in the direction of the center attachment axis, an inclination in the circumferential direction
  • Drop size distribution can be achieved without causing a significant change in the radial penetration depth.
  • the azimuthal angle of inclination of the central axes could, however, also be chosen, for example, as a function of the circumference. According to one embodiment of the
  • Circumference have an equal diameter.
  • Central axes of the full-jet nozzles run alternately, wherein the center axis of each second full-jet nozzle is perpendicular to the attachment surface and the center axis of the full-jet nozzle arranged therebetween has an azimuth angle of 20 degrees to the surface normal.
  • Circumferential direction This allows adaptation of the radial fuel profile of a main burner with respect to the entire burner assembly.
  • the full-jet nozzles have a same diameter along at least one circumferential line.
  • a further advantageous embodiment of the invention can provide that the solid jet nozzles are arranged at least along two circumferential lines.
  • An at least two-row arrangement of the full-jet nozzles allows a much greater variation of the
  • An equal or different number of full jet nozzles can be arranged along the two circumferential lines. For example, 4 to 10 nozzles per perimeter
  • the full jet nozzles arranged along an upstream circumferential line have a larger diameter than the full jet nozzles arranged along a downstream circumferential line.
  • This embodiment of the invention is advantageous if a uniform radial distribution is to be achieved. It can also be considered advantageous that the full jet nozzles arranged along an upstream circumferential line have a smaller diameter than the full jet nozzles arranged along a downstream circumferential line.
  • This embodiment of the invention is advantageous if a narrow radial distribution is to be achieved.
  • Circumferentially arranged full jet nozzles are arranged on common streamlines, wherein when flowing through the Swirl blades with air these along the streamlines
  • This embodiment of the invention is advantageous in order to achieve a uniform radial fuel distribution when, in particular, the fuel sprayed in by the downstream jet nozzles has a smaller or significantly greater penetration depth than that of the upstream
  • the design also makes it possible to achieve a narrow radial fuel distribution, wherein the jet injected from downstream full jet nozzles fuel is injected to the same radial position as the injected from upstream full jet nozzles fuel.
  • the radial position is chosen so that the flame is stabilized at a point whose associated time delay can not be excited in the combustion system.
  • it can further be provided that arranged along the downstream circumferential line
  • Circumferentially arranged full jet nozzles are arranged offset from one another such that when flowing through the
  • Full jet nozzles is arranged.
  • full-jet nozzles arranged along the downstream circumferential line Inject fuel to the same radial position as along the upstream perimeter line
  • Jet nozzles The radial position is chosen so that the flame stabilized at one point, the associated
  • Time delay is not excitable in the combustion system.
  • Full jet nozzle diameters allow the setting of various radial fuel profiles, with uniform radial profiles are considered advantageous.
  • the diameters along the at least one helical circumferential line arranged full jet nozzles are designed such that the diameter increase in the flow direction.
  • This embodiment of the invention is advantageous if a homogenization of the radial profile by enrichment of the near-axis region is to take place.
  • Diameter of the along the at least one helical circumferential line disposed full jet nozzles are formed such that the diameter opposite to
  • This embodiment of the invention is advantageous when a narrow radial fuel distribution is preferred.
  • the helical circumferential line may according to another
  • Embodiment of the invention do not run along a streamline.
  • This embodiment allows a uniform circumferential fuel distribution, wherein the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial fuel profile. Also, the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial fuel profile. Also, the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial fuel profile. Also, the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial fuel profile. Also, the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial fuel profile. Also, the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial
  • Flow direction can be varied to the center post axis and / or circumferentially along the helical circumferential line to adjust the interaction of the swirling flow of the air with the fuel full jet with respect to atomization in dependence on the nozzle position. Further, it can be considered advantageous that the
  • Full jet nozzles along two helical circumferential lines are arranged.
  • the double helix can also run antiparallel in addition to a parallel arrangement, whereby more uniform circumferential distributions can be achieved.
  • the diameters of the full-jet nozzles can all be the same size.
  • Fuel concentration may be the accumulation of
  • Full jet nozzles have distances from each other and diameter, with their sequence repeated along the circumferential line.
  • the full jet nozzles arranged along the circumferential line can have regular distances from each other and all have the same diameter.
  • the distances and / or the diameters can also be in regular succession
  • Diameter of the full jet nozzles along the circumference For example, two different diameters may be mixed in a regular sequence or more.
  • the radial range can be set, in which the fuel distribution of the different nozzle diameters superimposed.
  • the degree of overlap can additionally be adjusted by selecting the circumferential position of the full-jet nozzles, in particular the mutual distances.
  • an advantageous embodiment of the invention is for generating a fuel profile with an annular zone of a first fuel distribution and an annular zone of a second fuel distribution along the circumferential line between two full jet nozzles with the same
  • Diameter arranged a full-jet nozzle with a smaller diameter.
  • the lance can be provided on the lance, for example, according to an embodiment of the advantageous embodiment 8 to 16 full jet nozzles.
  • a diameter between 0.5mm-0.7mm and for the larger jet nozzles a diameter between 0.6mm-0.8mm can be chosen.
  • the two zones may overlap, for example by the full-jet nozzle with the smaller diameter closer to one of the two full-jet nozzles with a larger diameter
  • Full jet nozzles are designed such that a fuel injected by means of the nozzle has a radial
  • Fuel distribution around the center attachment axis wherein the fuel distribution comprises an annular zone of a first fuel distribution and an annular zone of a second fuel distribution.
  • the advantageous fuel distribution can be generated by varying the distances, the diameter, the inclination angle and / or the course of the circumferential line.
  • such a fuel profile can be produce by means of an annular, perpendicular to the center attachment axis extending circumferential line along which equally spaced full jet nozzles are arranged, whose diameters have alternately two different sizes.
  • annular zone of a first fuel distribution and the annular zone of a second fuel distribution overlap each other.
  • annular zone of a first fuel distribution and the annular zone of a second fuel distribution have a distance from each other.
  • Fig. 1 shows schematically a section through a
  • FIG. 2 schematically shows a section through the attachment 13 of the embodiment shown in Figure 1 in a perspective view
  • FIG. 3 shows schematically a section through a
  • Figure 4 shows schematically a section through a
  • Main burner of the burner assembly according to the invention according to a third embodiment 5 shows a diagram to illustrate the embodiment shown in Figure 4, schematically shows a section through a main burner of the burner assembly according to the invention according to a fourth embodiment, shows a cross section of the attachment shown in Figure 6, shows a diagram to illustrate the in FIG. 6 schematically shows a section through a main burner of the burner assembly according to the invention according to a fifth embodiment, schematically shows a section through a main burner of the burner assembly according to the invention according to a sixth embodiment,
  • Fig.12 shows schematically an inventive
  • FIG. 1 shows a detail of an inventive
  • Burner arrangement in the region of a main burner 107 In the housing 12 of the main burner 107, swirl vanes 17 are arranged around the lance. The swirl blades 17 are arranged along the circumference of the lance in the housing 12. Through the swirl vanes 17, a compressor air flow 15 is passed into the leading to a combustion chamber part of the burner 107. The air is displaced by the swirl blades 17 in a swirling motion.
  • the lance also includes a Fuel channel 16.
  • the burner 107 further comprises an attachment 13 on the side leading to a combustion chamber.
  • the attachment 13 can be welded or screwed to the lance, for example.
  • the fuel nozzles are arranged in the attachment 13 preferably downstream of the swirl vanes 17 and are fluidically connected to the fuel channel 16, here represented as an oil channel.
  • the burner assembly according to the invention comprises eight such
  • Main burner 107 arranged circular (see Figure 12). At this time, the main burners 107 become one (see FIG. 12).
  • Pilot burner with pilot cone arranged Pilot burner with pilot cone arranged.
  • the plurality of fuel nozzles according to the invention are designed as full jet nozzles 1.
  • the configuration of the nozzle as a full jet nozzle 1, the full jet nozzle size and also arrangement make it possible for the penetration depth of the
  • Fuel profile arises.
  • the parameters are the diameter of the full jet nozzles 1 and the number of
  • thermoacoustic feedback loops From which
  • the full jet nozzles 1 have a length, wherein the length to diameter
  • Ratio is at least 1.5, in order to achieve a good mixing.
  • the divergence of the full jet is small enough, so that it is not an undesirable
  • Adjustment of the fuel profile, in particular the radial fuel distribution can be changed very effectively.
  • the full-jet nozzle 1 Compared to a pressure-swirl nozzle, the full-jet nozzle 1 has the advantage that a higher fuel admission pressure is converted, above all, in a greater penetration depth. In the pressure swirl nozzles of the prior art smaller drops are formed by a higher pre-pressure, which in turn penetrate less effectively. It follows that for a higher penetration depth in pressure-swirl nozzles a significantly higher
  • the attachment 13 is conical towards the combustion chamber, tapered designed. It comprises several, in the present embodiment four, full-jet nozzles 1. Die
  • Full jet nozzles 1 are arranged on the outer circumference of the attachment 13.
  • the center axes of the full-jet nozzles 1 are identified by the reference numeral 19.
  • the central axes 19 of the full-jet nozzles 1 point to the center attachment axis 18 of the
  • the central axis 19 of the full-jet nozzles 1 is substantially perpendicular (90 degrees) to
  • the attachment 13 comprises a cylindrical portion 130 and a portion 140 tapering towards a combustion chamber.
  • the conical portion 140 may have a cone angle of 10-20 degrees.
  • the full-jet nozzles 1 can be arranged on the conical tapering part 140 of the attachment 13. The position of the
  • Full jet nozzles 1 may change depending on the autoignition time of the mixture. In order to achieve a good fuel distribution, eight to twelve full-jet nozzles per attachment 13 are preferably used (not shown). Also advantageous are six to sixteen full jet nozzles 1 (not shown). These are evenly distributed on the circumference of the article 13. A good fuel distribution is necessary to the
  • the full-jet nozzles 1 may be formed as bores in the attachment 13. In terms of mixing, in particular, a length to diameter ratio of six to fourteen is advantageous.
  • the length of the full jet nozzle is designated by the reference numeral 32.
  • Diameter of the full-jet nozzles 1 are 0.55-0.8 mm, also advantageous are 0.5 -1 mm (not shown).
  • Combinations of eight nozzles with a diameter of 0.7-0.8 mm, or of ten nozzles with 0.6-0.7 mm diameter and twelve nozzles of 0.55-0.65 mm diameter advantageous.
  • solid jet nozzles 1 can easily be adapted to other thermodynamic conditions, which are e.g. result in a changed air cross flow velocity, air density or fuel mass flow,
  • the diameter 33 of the full jet nozzles 1 is adjusted accordingly.
  • FIG. 3 shows a detail of the invention
  • the main burner 107 comprises a cylindrical housing 12, in which a lance 14 is centrally arranged, which is surrounded by a main whirlwind 10.
  • the main vortex generator 10 shown schematically has swirl vanes 17 (not shown), which support the lance 14 on the housing 12.
  • a compressor air flow 15 flows in the direction of the combustion chamber (not shown).
  • the lance 14 extends along an center attachment axis 18, on which in the direction of the combustion chamber (not shown) an attachment 13 is arranged.
  • the attachment 13 has a cylindrical part 130 and merges in the direction of the combustion chamber into a tapered part 140. In the tapered portion 140 of the article 13 are surrounded by circles
  • Center attachment axis 18 are arranged around circumferential line 11. In other words, they are for
  • Attachment surface opening out the full jet nozzles 1 along a running on the attachment surface
  • Circumferential line 11 is arranged, wherein the circumferential line 11 extends in the circumferential direction 22 around the attachment 13 around. From the circumferential line 11, one half can be seen in the sectional view.
  • the circumferential direction 22 is not necessarily perpendicular to the center attachment axis 18. Important here is only that extending in the circumferential direction 22 on the attachment surface circumferential line 11, the center attachment axis 18th
  • the circumferential line 11 shown in FIG must have no real equivalent, but only serves to describe the full jet nozzle arrangement. According to the
  • the burner assembly according to the invention varies the number density of the full jet nozzles 1 in the circumferential direction 22, since the
  • Center attachment axis 18 is greater than below the
  • main burner 107 is the above the
  • central axes 18 shown side of the attachment 13 to the pilot burner (not shown) facing.
  • the central axes 19 of the full-jet nozzles 1 run perpendicular to the attachment surface according to the illustrated embodiment. That is, each of the central axes 19 extends in the direction of a surface normal 23.
  • FIG. 4 shows a schematic sectional view of a detail of a burner arrangement according to the invention in the region of a main burner 107 according to a third exemplary embodiment.
  • the construction of the main burner here corresponds to the embodiment shown in Figure 3 except for the arrangement of the full jet nozzles 1. According to the third embodiment, these are along an annular and perpendicular to the
  • Main essay line 18 extending circumferential line 11 is arranged.
  • the inclination of the central axes 19 of the full-jet nozzles in this case runs alternately along the circumferential line 11
  • Deviating line 11 following jet nozzle 1 is deviating from this by 10 degrees in the direction of the center attachment axis 18th inclined in the flow direction of the compressor air flow 15. In this sense, the inclination of the center axes 19 of the full-jet nozzles 1 varies in the circumferential direction 22 along the
  • Circumferential line 11 denotes the angle between the central axis 19 and top surface.
  • FIG. 5 shows a diagram to clarify the embodiment shown in FIG. Illustrated is the example of the angle ⁇ between the central axis 19 and
  • the angle ⁇ is denoted by the angle of attack.
  • 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 corresponds to the embodiment shown in Figure 3 except for the
  • the central axis 19 and thus also the direction 25 of the fuel jet, in which it leaves the jet nozzle 1, runs perpendicular to the attachment surface and thus in the direction of a surface normal 23 in the case of a first full jet nozzle 1 11 following full jet nozzle 1 is deviating from this by 20 degrees in the circumferential direction 22 inclined.
  • the inclination angle in the circumferential direction 22 can also with
  • Figure 7 shows to illustrate the illustrated in Figure 6 fourth embodiment, a cross section of the attachment 13 at the axial height of the circumferential line 11.
  • the arranged along the circumferential line 11 full jet nozzles 1 are illustrated by circles.
  • the openings of the full-jet nozzles are arranged along the circumferential line 11.
  • FIG. 8 shows a diagram to clarify the fourth embodiment shown in FIG. Illustrated is the example of the angle between the central axis 19 and
  • FIG. 9 shows a schematic sectional view of a
  • Main burner 107 according to a fifth embodiment.
  • the structure of the main burner 107 corresponds to the embodiment shown in Figure 3 except for the
  • Full jet nozzles 1 are arranged on a common streamline 27.
  • FIG. 10 shows a schematic sectional view of a
  • Main burner 107 according to a sixth embodiment.
  • the structure of the main burner 107 corresponds to the embodiment shown in Figure 3 except for the
  • the Full jet nozzles 1 along the circumferential line 11 have distances from each other and diameter, with their sequence along the circumferential line 11 is repeated.
  • the full jet nozzles 1 are equally spaced from each other, wherein between each two full jet nozzles 1 with the same diameter a
  • Full jet nozzle 1 is arranged with a smaller diameter.
  • the central axes (not shown) of the full-jet nozzles 1 are perpendicular to the central attachment axis 18 in radial
  • FIG. 11 shows a fuel profile that can be generated by means of the solid jet nozzles 1 shown in FIG. Of the
  • the fuel distribution from a single full-jet nozzle with large diameter is designated by the reference numeral 30.
  • the fuel distribution from a single full-jet small diameter nozzle is designated by reference numeral 31. Due to the selected distances between the full jet nozzles 1 and the size ratios of the diameters, the annular zone of a first fuel distribution 28 and the annular zone of a second fuel distribution 29 overlap one another.
  • FIG. 12 shows a burner arrangement 108 according to the invention with a pilot burner 106 with pilot cone 109 and a multiplicity of main burners 107 arranged around the pilot burner 106.
  • Each of the main burners 107 comprises a substantially cylindrical housing 12 in which a lance is centrally arranged, in the direction of Combustion chamber (not shown) an attachment 13 is arranged on the lance.

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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)

Abstract

L'invention concerne un ensemble brûleur pour une turbine à gaz, comprenant au moins une chambre de combustion, présentant un brûleur pilote disposé au centre, et plusieurs brûleurs principaux (107) entourant le brûleur pilote, chacun des brûleurs principaux (107) comprenant un boîtier cylindrique (12) muni d'une lance disposée au centre, présentant un canal (16) pour le carburant liquide, ladite lance prenant appui, via des aubes de turbulence (17), sur le boîtier (12), un ajutage (13) étant disposé sur la lance, en direction de la chambre de combustion, au moins une buse de carburant liquide étant disposée dans l'ajutage (13), de préférence en aval des aubes de turbulence (17) et étant raccordée avec le canal de carburant (16). Dans le but d'obtenir un mélange amélioré du carburant avec l'air, au moins la buse de carburant liquide est configurée en tant que buse jet plein (1), et la buse jet plein (1) présente une longueur et un diamètre, ayant un rapport longueur/diamètre d'au moins 1,5.
PCT/EP2011/061101 2010-07-01 2011-07-01 Ensemble brûleur Ceased WO2012001141A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP11728849.8A EP2588805B1 (fr) 2010-07-01 2011-07-01 Brûleur
JP2013517313A JP6005040B2 (ja) 2010-07-01 2011-07-01 バーナー装置
US13/806,895 US20130104554A1 (en) 2010-07-01 2011-07-01 Burner assembly

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EP10168107A EP2402652A1 (fr) 2010-07-01 2010-07-01 Brûleur

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JP6005040B2 (ja) 2016-10-12
EP2588805B1 (fr) 2016-04-20
EP2588805A1 (fr) 2013-05-08
US20130104554A1 (en) 2013-05-02
EP2402652A1 (fr) 2012-01-04

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