EP0909921A1 - Burner for operating a heat generator - Google Patents

Abstract

The bottom part of a mixer pipe (20) contains a pilot burner system (300) affecting the combustion space after the mixer pipe. The pilot burner system consists of at least two media-conveying chambers (301,302) and a shared following chamber (308) in which the media (303,304) from the two other chambers are mixed. The shared chamber has pilot burners (306) operated by the mixture of the two media.

Description

Technical field

The invention relates to a burner for operating a heat generator according to Preamble of claim 1.

State of the art

From EP-0 780 629 A2 a burner has become known, the upstream side consists of a swirl generator, the flow formed therein seamlessly in a mixing section is transferred. This is done using one at the beginning of the Mixing section flow geometry formed for this purpose, which consists of transition channels exists, which is sectoral, according to the number of those acting Partial body of the swirl generator, capture the end face of the mixing section and in Flow direction swirl. Downstream of these transition channels the mixing section has a number of filming holes, which one Ensure an increase in the flow velocity along the pipe wall. This is followed by a combustion chamber, the transition between the Mixing section and the combustion chamber formed by a cross-sectional jump in whose plane a backflow zone or backflow bubble forms.

The swirl strength in the swirl generator is selected so that the bursting of the vortex does not occur within the mixing section, but further downstream, as executed above, in the area of the cross-sectional jump. The length of the mixing section is dimensioned so that a sufficient mix quality for everyone Types of fuel is guaranteed.

Although this burner compared to those from the previous state the technology a significant improvement in terms of strengthening flame stability, lower pollutant emissions, lower pulsations, complete Burnout, large operating area, good cross-ignition between the different Burners, compact design, improved mixing, etc., guaranteed, it turns out that this burner has no autonomous arrangements, to drive the gas turbine safely, especially in its transient load ranges to be able to. For example, in the partial load range, the burner must have a support flame get supported. The integration of such precautions in the burner lead to no additional pollutant emissions which the operational and emissions advantages of the underlying burner could question.

Presentation of the invention

The invention seeks to remedy this. The invention as set out in the claims is characterized, the task is based on a burner at the beginning to propose precautions which strengthen the flame stability for stable operation, especially in the transient load ranges, ensure always under the further task that the Pollutant emissions remain low.

For this purpose, the burner is expanded in such a way that in the area of its transition a ring-shaped system for providing to the downstream combustion chamber of a fuel / air mixture is generally provided as Pilot stage acts. Through a number of circumferential exit bores Appropriate pilot burners are created in the combustion chamber, which are operated in diffusion mode for stability reasons and directly in the combustion chamber.

The main advantages of the subject matter according to the invention are therein see that these individual pilot burners are operated with a low gas content be so that the gas introduced there with a relatively small Air content mixed and as a premixed flame with minimized pollutant emissions burns.

This air volume initially takes over the cooling of the by means of impingement cooling side facing away from the combustion chamber before it then mixes with the gas and then as a pre-mixed flame with minimized pollutant emissions piloting the main flame in the combustion chamber is maintained.

This impingement cooling means that the surface of the pilot gas ring is hot and largely isolated from the flame radiation from the combustion chamber, so that the thermal load in this area is significantly reduced.

Even with 100% pilot operation, the individual pilot burners burn, for reasons of stability in diffusion mode, since here the proportion of the cooling air compared to the gas is very small.

The object according to the invention also ensures that the minimized Cooling amount can also be fed to the burning process.

Advantageous and expedient developments of the task solution according to the invention are characterized in the further claims.

Exemplary embodiments of the invention are described below with reference to the drawings explained in more detail. All of which are not essential for the immediate understanding of the invention Features have been left out. The same elements are in the different Figures with the same reference numerals. The flow direction the media is indicated by arrows.

Brief description of the drawings

Fig. 1

einen als Vormischbrenner ausgelegten Brenner mit einer Mischstrecke stromab eines Drallerzeugers sowie mit Pilotbrennern,

Fig. 2

eine schematische Darstellung des Brenners gemäss Fig. 1 mit Disposition der zusätzlichen Brennstoff-Injektoren,

Fig. 3

einen aus mehreren Schalen bestehenden Drallerzeuger in perspektivischer Darstellung, entsprechend aufgeschnitten,

Fig. 4

einen Querschnitt durch einen zweischaligen Drallerzeuger,

Fig. 5

einen Querschnitt durch einen vierschaligen Drallerzeuger,

Fig. 6

eine Ansicht durch einen Drallerzeuger, dessen Schalen schaufelförmig profiliert sind,

Fig. 7

eine Ausgestaltung der Uebergangsgeometrie zwischen Drallerzeuger und Mischstrecke und

Fig. 8

eine Abrisskante zur räumlichen Stabilisierung der Rückströmzone.

It shows:

Fig. 1

a burner designed as a premix burner with a mixing section downstream of a swirl generator and with pilot burners,

Fig. 2

2 shows a schematic representation of the burner according to FIG. 1 with disposition of the additional fuel injectors,

Fig. 3

a swirl generator consisting of several shells in a perspective view, cut open accordingly,

Fig. 4

a cross section through a double-shell swirl generator,

Fig. 5

a cross section through a four-shell swirl generator,

Fig. 6

2 shows a view through a swirl generator, the shells of which are profiled in a shovel shape,

Fig. 7

an embodiment of the transition geometry between swirl generator and mixing section and

Fig. 8

a tear-off edge for spatial stabilization of the backflow zone.

WAYS OF CARRYING OUT THE INVENTION, INDUSTRIAL APPLICABILITY

Fig. 1 shows the overall structure of a burner. Initially, a swirl generator 100 is effective, the design of which is shown and described in more detail in the following FIGS. 3-6. This swirl generator 100 is a conical structure which is acted upon tangentially several times by a tangentially flowing combustion air flow 115. The flow formed here is seamlessly transferred to a transition piece 200 using a transition geometry provided downstream of the swirl generator 100, in such a way that no separation areas can occur there. The configuration of this transition geometry is described in more detail in FIG. 6. This transition piece 200 is extended on the outflow side of the transition geometry by a mixing tube 20, both parts forming the actual mixing section 220. Of course, the mixing section 220 can consist of a single piece, that is to say then that the transition piece 200 and the mixing tube 20 merge into a single coherent structure, the characteristics of each part being retained. If the transition piece 200 and the mixing tube 20 are created from two parts, these are connected by a bushing ring 10, the same bushing ring 10 serving as an anchoring surface for the swirl generator 100 on the head side. Such a bushing ring 10 also has the advantage that different mixing tubes can be used. On the outflow side of the mixing tube 20 is the actual combustion chamber 30 of a combustion chamber, which is here only symbolized by a flame tube. The mixing section 220 largely fulfills the task of providing a defined section downstream of the swirl generator 100, in which a perfect premixing of fuels of different types can be achieved. This mixing section, i.e. the mixing pipe 20 in the foreground, furthermore enables loss-free flow guidance, so that no backflow zone or backflow bubble can initially form even in operative connection with the transition geometry, so that the length of the mixing section 220 can influence the quality of the mixture for all types of fuel . However, this mixing section 220 has yet another property, which consists in that the axial velocity profile itself has a pronounced maximum on the axis, so that the flame cannot be re-ignited from the combustion chamber. However, it is correct that with such a configuration this axial speed drops towards the wall. To prevent re-ignition in this area, the mixing tube 20 is provided in the flow and circumferential direction with a number of regularly or irregularly distributed bores 21 of various cross-sections and directions through which an amount of air flows into the interior of the mixing tube 20 and along the wall in the In the sense of filming, induce an increase in the flow rate. These bores 21 can also be designed such that at least one additional effusion cooling is established on the inner wall of the mixing tube 20. Another possibility of increasing the speed of the mixture within the mixing tube 20 is to narrow its flow cross-section on the downstream side of the transition channels 201, which form the transition geometry already mentioned, as a result of which the overall speed level within the mixing tube 20 is increased. In the figure, these bores 21 run at an acute angle with respect to the burner axis 60. Furthermore, the outlet of the transition channels 201 corresponds to the narrowest flow cross-section of the mixing tube 20. The said transition channels 201 therefore bridge the respective cross-sectional difference without adversely affecting the flow formed. If the selected precaution triggers an intolerable pressure loss when guiding the pipe flow 40 along the mixing pipe 20, this can be remedied by providing a diffuser (not shown in the figure) at the end of this mixing pipe. A combustion chamber 30 (combustion chamber) then adjoins the end of the mixing tube 20, a cross-sectional jump formed by a burner front 70 being present between the two flow cross sections. Only here does a central flame front form with a backflow zone 50 which has the properties of a disembodied flame holder compared to the flame front. If a flow-like edge zone forms in this cross-sectional jump during operation, in which vortex detachments arise due to the prevailing negative pressure, this leads to an increased ring stabilization of the return flow zone 50. In addition, it should also be mentioned that the generation of a stable return flow zone 50 is also sufficiently high Twist number in a pipe required. If this is initially undesirable, stable backflow zones can be created by supplying small, strongly swirled air flows at the pipe end, for example by means of tangential openings. It is assumed here that the amount of air required for this is about 5-20% of the total amount of air. With regard to the configuration of the burner front 70 at the end of the mixing tube 20 for stabilizing the backflow zone or backflow bladder 50, reference is made to the description under FIG. 8.
A pilot burner system 300 is provided concentrically with the mixing tube 20 in the area of its outlet. This consists of an inner annular chamber 301 into which a fuel, preferably a gaseous fuel 303, flows. In addition to this inner annular chamber 301, there is a second annular chamber 302 into which an air quantity 304 flows. Both annular chambers 301, 302 have individually designed through openings, such that the individual media 303, 304 flow into a common downstream annular chamber 308 due to their function. The transfer of the gaseous fuel 303 from the annular chamber 301 into the downstream annular chamber 308 is accomplished by a number of openings 309 arranged in the circumferential direction. The passage geometry of these openings 309 is designed such that the gaseous fuel 303 flows into the downstream annular chamber 308 with a large mixing potential. The other annular chamber 302 closes with a perforated plate 305, the bores 310 provided here being designed in such a way that the air volume 304 flowing through there impacts cooling on the base plate 307 of the downstream annular chamber 308. This base plate has the function of a heat protection plate against the calorific load from the combustion chamber 30, so that this impingement cooling must be extremely efficient here.

After cooling, this air mixes within this annular chamber 308 with the inflowing gaseous fuel 303 from the openings 309 of the upstream annular chamber 301 before this mixture through a number of bores 306 arranged on the combustion chamber side into the combustion chamber 30 flows out. The mixture flowing out burns as a premixed diffusion flame with minimized pollutant emissions and forms accordingly Bore 306 a pilot burner acting in the combustion chamber 30, which one guaranteed stable operation.

Fig. 2 shows a schematic view of the burner according to Fig. 1, here in particular the flushing of a centrally arranged fuel nozzle 103 and the effect of fuel injectors 170 is pointed out. The mode of action the remaining main components of the burner, namely swirl generator 100 and transition piece 200 are closer under the following figures described. The fuel nozzle 103 is spaced with a ring 190 encased in which a number of circumferentially bored holes 161 through which an amount of air 160 is placed in an annular chamber 180 flows and carries out the flushing of the fuel lance there. These holes 161 are slanted forward so that it is appropriate axial component arises on the burner axis 60. In active connection with these Additional fuel injectors 170 are provided in holes 161 a certain amount, preferably a gaseous fuel, into the Enter the respective amount of air 160 in such a way that a sets uniform fuel concentration 150 over the flow cross-section, as the representation in the figure is intended to symbolize. Exactly this even Fuel concentration 150, especially the strong concentration the burner axis 60 ensures that the flame front is stabilized at the outlet of the burner, which causes combustion chamber pulsations be avoided.

In order to better understand the structure of the swirl generator 100, it is advantageous to if at least FIG. 4 is used at the same time as FIG. 3. Hereinafter 3 is referred to the other figures as necessary in the description of FIG.

The first part of the burner according to FIG. 1 forms the swirl generator 100 shown in FIG. 3. It consists of two hollow, conical partial bodies 101, 102, which are nested one inside the other. The number of conical partial bodies can of course be greater than two, as shown in FIGS. 5 and 6; This depends on the operating mode of the entire burner, as will be explained in more detail below. In certain operating constellations, it is not excluded to provide a swirl generator consisting of a single spiral. The offset of the respective central axis or longitudinal symmetry axes 101b, 102b (see FIG. 4) of the conical partial bodies 101, 102 to one another creates a tangential channel, ie an air inlet slot 119, 120 (see FIG. 4), through which the combustion air 115 flows into the interior of the swirl generator 100, ie into the cone cavity 114 thereof. The conical shape of the partial bodies 101, 102 shown in the flow direction has a specific fixed angle. Of course, depending on the operational use, the partial bodies 101, 102 can have an increasing or decreasing cone inclination in the direction of flow, similar to a trumpet or. Tulip. The last two forms are not included in the drawing, since they can be easily understood by a person skilled in the art. The two conical partial bodies 101, 102 each have a cylindrical, ring-shaped initial part 101a. The fuel nozzle 103 already mentioned under FIG. 2 is accommodated in the region of this cylindrical starting part and is preferably operated with a liquid fuel 112. The injection 104 of this fuel 112 coincides approximately with the narrowest cross section of the conical cavity 114 formed by the conical partial bodies 101, 102. The injection capacity and the type of this fuel nozzle 103 depend on the specified parameters of the respective burner. The tapered partial bodies 101, 102 further each have a fuel line 108, 109, which are arranged along the tangential air inlet slots 119, 120 and are provided with injection openings 117, through which a gaseous fuel 113 is preferably injected into the combustion air 115 flowing through there, such as arrows 116 symbolize this.
These fuel lines 108, 109 are preferably arranged at the latest at the end of the tangential inflow, before entering the cone cavity 114, in order to obtain an optimal air / fuel mixture. As mentioned, the fuel 112 brought up through the fuel nozzle 103 is normally a liquid fuel, and it is readily possible to form a mixture with another medium, for example with a recirculated flue gas. This fuel 112 is injected into the cone cavity 114 at a preferably very acute angle. A conical fuel spray 105 thus forms from the fuel nozzle 103 and is enclosed and broken down by the rotating combustion air 115 flowing in tangentially.
The concentration of the injected fuel 112 is then continuously reduced in the axial direction by the inflowing combustion air 115 to mix in the direction of evaporation. If a gaseous fuel 113 is introduced via the opening nozzles 117, the fuel / air mixture is formed directly at the end of the air inlet slots 119, 120. If the combustion air 115 is additionally preheated or, for example, enriched with a recirculated flue gas or exhaust gas, this provides lasting support the evaporation of the liquid fuel 112 before this mixture flows into the downstream stage, here in the transition piece 200 (see FIGS. 1 and 7). The same considerations also apply if liquid fuels should be supplied via lines 108, 109. When designing the conical partial bodies 101, 102 with regard to the cone angle and the width of the tangential air inlet slots 119, 120, strict limits have to be observed so that the desired flow field of the combustion air 115 can be set at the outlet of the swirl generator 100. In general, it can be said that a reduction in the size of the tangential air inlet slots 119, 120 already favors the faster formation of a backflow zone in the region of the swirl generator. The axial speed within the swirl generator 100 can be increased or stabilized by a corresponding supply of an air quantity described in more detail in FIG. 2 (item 160). A corresponding swirl generation in operative connection with the downstream transition piece 200 (see FIGS. 1 and 7) prevents the formation of flow separations within the mixing tube downstream of the swirl generator 100. The design of the swirl generator 100 is furthermore particularly suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operational bandwidth can be recorded without changing the overall length of the swirl generator 100. Of course, the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which an overlap thereof can even be provided. It is also possible to interleave the partial bodies 101, 102 in a spiral manner by counter-rotating movement. It is thus possible to vary the shape, the size and the configuration of the tangential air inlet slots 119, 120 as desired, with which the swirl generator 100 can be used universally without changing its overall length.

4 shows, among other things, the geometric configuration of optional ones Baffles 121a, 121b. They have a flow initiation function which, according to their length, the respective end of the tapered Partial bodies 101, 102 in the flow direction with respect to the combustion air 115 extend. The channeling of the combustion air 115 into the cone cavity 114 can be opened or closed by one of the baffles 121a, 121b Area of entry of this channel into the fulcrum 114 placed cone cavity 123 can be optimized, especially if the original Gap size of the tangential air inlet slots 119, 120 changed dynamically should be, for example, to change the speed of the combustion air 115 to achieve. Of course, these can be dynamic Precautions can also be provided statically by using baffles as needed form a fixed component with the conical partial bodies 101, 102.

5 shows that the swirl generator 100 now consists of four partial bodies 130, 131, 132, 133 is constructed. The associated longitudinal symmetry axes for each sub-body are marked with the letter a. To this Configuration is to be said that it is due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged Slot width is best suited, the bursting of the vortex flow on the downstream side to prevent the swirl generator in the mixing tube, thus causing the mixing tube to can fulfill the intended role.

FIG. 6 differs from FIG. 5 in that the partial bodies 140 here 141, 142, 143 have a blade profile shape which is used to provide a certain Flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same. The admixture of fuel 116 in the combustion air flow 115 happens from inside the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades. Here, too, are the longitudinal axes of symmetry with the individual partial bodies Letter a marked.

7 shows the transition piece 200 in a three-dimensional view. The transition geometry is corresponding for a swirl generator 100 with four partial bodies 5 or 6, built. Accordingly, the transition geometry as a natural extension of the upstream partial bodies, four transition channels 201 on, whereby the conical quarter area of said partial body is extended until it cuts the wall of the mixing tube. The same considerations also apply if the swirl generator is based on a principle other than the one below Fig. 3 described, is constructed. The down in the direction of flow running surface of the individual transition channels 201 has a flow direction spiral shape, which has a crescent shape Course describes, corresponding to the fact that the flow cross-section is present of the transition piece 200 flared in the flow direction. The swirl angle of the transition channels 201 in the flow direction is selected so that that the pipe flow then up to the cross-sectional jump on Combustion chamber entrance still has a sufficient distance to be perfect Premix with the injected fuel. Further increases the axial speed is also affected by the above-mentioned measures on the mixing tube wall downstream of the swirl generator. The transition geometry and the measures in the area of the mixing tube bring about a significant increase of the axial velocity profile towards the center of the mixing tube, see above that the danger of early ignition is decisively counteracted.

8 shows the tear-off edge already mentioned, which emerges at the burner outlet is formed. The flow cross section of the tube 20 receives one in this area Transition radius R, the size of which basically depends on the flow within of the tube 20 depends. This radius R is chosen so that the Applies flow to the wall and so the swirl number increases sharply. Quantitatively the size of the radius R can be defined so that it is> 10% of the inside diameter d of the tube is 20. Opposite a flow without a radius Now the backflow bladder 50 increases enormously. This radius R runs to the exit plane of the tube 20, the angle β between the beginning and end of curvature is <90 °. Along one leg of the angle β runs the tear-off edge A into the interior of the tube 20 and thus forms a tear-off step S opposite the front point of the tear-off edge A, whose depth> 3 mm is. Of course, this can be parallel to the exit plane of the tube 20 running edge based on a curved course back to the exit level to be brought. The angle β ', which is between the tangent of the tear-off edge A and perpendicular to the exit plane of the tube 20 is the same size like angle β. The advantages of this formation of this tear-off edge come from EP-0 780 629 A2 under the chapter "Presentation of the invention". Another Design of the tear-off edge for the same purpose can be done with the combustion chamber achieve toroidal notches. This publication is inclusive the scope of protection there regarding the tear-off edge is an integrating one Part of this description.

Reference list

10th

Bushing ring

20th

Mixing tube, part of the mixing section 220

21

Holes, openings

30th

Combustion chamber, combustion chamber

40

Flow, pipe flow in the mixing pipe, main flow

50

Backflow zone, backflow bubble

60

Burner axis

100

Swirl generator

101, 102

Partial conical body

101a

Annular initial part

101b, 102b

Longitudinal symmetry axes

103

Fuel nozzle

104

Fuel injection

105

Fuel spray (fuel injection profile)

108, 109

Fuel lines

112

Liquid fuel

113

Gaseous fuel

114

Cone cavity

115

Combustion air (combustion air flow)

116

Fuel injection from lines 108, 109

117

Fuel nozzles

119, 120

Tangential air inlet slots

121a, 121b

Baffles

123

Pivot point of the guide plates

130, 131, 132, 133

Partial body

131a, 131a, 132a, 133a

Longitudinal symmetry axes

140, 141, 142, 143

Vane-shaped partial body

140a, 141a, 142a, 143a

Longitudinal symmetry axes

150

Fuel concentration

160

Air volume, mixed air

161

Holes, openings

170

Fuel injectors

180

Annular air chamber

190

ring

200

Transition piece, part of the mixing section 220

201

Transition channels

220

Mixing section

300

Pilot burner system

301

Inner ring chamber

302

Secondary ring chamber

303

Gaseous fuel

304

Air volume

305

Perforated plate

306

Drilling in the combustion chamber, pilot burner

307

Heat shield

308

Downstream ring chamber

309

Openings of the inner ring chamber

310

Holes for impingement cooling of the heat protection plate

Claims (18)

Burner for operating a heat generator, the burner essentially from a swirl generator for a stream of combustion air Means for injecting at least one fuel into the combustion air flow there is a mixing section arranged downstream of the swirl generator which is within a first section in the flow direction a number of transition channels for transferring one in the swirl generator formed flow in a downstream downstream of these transition channels Mixing tube, characterized in that in the lower Area of the mixing tube (20) with effect in a the mixing tube (20) downstream combustion chamber (30) a pilot burner system (300) is arranged which consists of at least two media-carrying chambers (301, 302) and from another common downstream chamber (308) there is that in this downstream chamber (308) the media (303, 304) are miscible from the other two chambers (301, 302), and that the downstream chamber (308) means for forming in the Combustion chamber (30) acting on the mixture of the two media (303, 304) operable pilot burners (306). Burner according to claim 1, characterized in that by the media leading Chambers (301, 303) formed annular and adjacent are that through the first annular chamber (301) a gaseous fuel (303) and through the second annular chamber (302) an amount of air (304) flow that means (305) installed in the second annular chamber (302) are, through which the air flowing there (304) impingement cooling on Heat protection plate arranged at the end of the pilot burner system (300) (307) accomplished. Burner according to claim 2, characterized in that the means for Impingement cooling formation in the adjacent annular chamber (302) bottom-forming perforated plate (305). Burner according to claim 1, characterized in that the means from one head side of the swirl generator (100) and in operative connection with a Fuel nozzle (103) arranged ring (190) that the ring (190) has a number of bores (161) arranged in the circumferential direction, and that in an amount of air flowing through the bores (161) (160) a fuel (170) can be injected. Burner according to claim 4, characterized in that the bores (161) are directed obliquely forward. Burner according to claim 4, characterized in that the fuel nozzle (103) is surrounded by a ring-shaped air chamber (180). Burner according to claim 1, characterized in that the burner front of the mixing tube (20) to the downstream combustion chamber (30) with a tear-off edge (A) is formed. Burner according to claim 1, characterized in that the number of Transition channels (201) in the mixing section (220) the number of the Swirl generator (100) corresponds to the partial flows formed. Burner according to claim 1, characterized in that the transition channels (201) downstream mixing tube (20) in flow and Circumferential direction with openings (21) for injecting an air stream into Interior of the mixing tube (20) is provided. Burner according to claim 9, characterized in that the openings (21) at an acute angle with respect to the burner axis (60) of the Mixing tube (20) run. Burner according to claim 1, characterized in that the flow cross section the mixing tube (20) downstream of the transition channels (201) smaller, the same size or larger than the cross-section of the swirl generator (100, 100a) is formed flow (40). Burner according to claim 1, characterized in that downstream of the Mixing section (220) a combustion chamber (30) is arranged that between the mixing section (220) and the combustion chamber (30) a cross-sectional jump is present, which is the initial flow cross section of the combustion chamber (30) induced, and that in the area of this cross-sectional jump a Backflow zone (50) is effective. Burner according to claim 1, characterized in that upstream of the Burner front (70) there is a diffuser and / or a venturi section. Burner according to claim 1, characterized in that the swirl generator (100) from at least two hollow, conical, in the direction of flow nested partial bodies (101, 102; 130, 131, 132, 133; 140, 141, 142, 143) there is that the respective longitudinal symmetry axes (101b, 102b; 130a, 131a, 132a, 133a; 140a, 141a, 142a, 143a) of these partial bodies mutually offset, such that the neighboring walls the partial body has tangential channels (119, 120) for a combustion air flow (115) and that in the Partial body formed interior (114) at least one fuel nozzle (103 is effective. Burner according to claim 14, characterized in that in the region of tangential channels (119, 120) in their longitudinal extension further fuel nozzles (117) are arranged. Burner according to claim 14, characterized in that the partial body (140, 141, 142, 143) have a blade-shaped profile in cross section. Burner according to claim 14, characterized in that the partial body in Flow direction a fixed cone angle, or an increasing cone inclination, or have a decreasing taper. Burner according to claim 14, characterized in that the partial body are nested in a spiral.

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