EP0899508A1 - Burner for a heat producing device - Google Patents

Abstract

The fuel jet (105) produced by the fuel nozzle (104) has an emission angle which corresponds approximately to the adjustment angle of the components (101,102) forming the spin producer (100) in relation to the axis of the burner or of the combustion chamber. The spin producer comprises a number of circular blades. Use - As a burner for a heat producer.

Description

Technical field

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

State of the art

A low-pollution combustion of liquid fuels, such as Heating oil EL (= extra light), requires the complete evaporation of the fuel drops as well as the premixing of the fuel with the combustion air before reaching it the flame front. Even small zones with a higher fuel concentration lead to elevated temperatures in the reaction zone and thus to increased temperatures Formation of thermal nitrogen oxides.

It has become known from the prior art that the oil with various Types of swirl or air-assisted central and head side of the premixing section arranged to atomize nozzles. The atomization quality that can be achieved in this way However, this burner is restricted for various types of operation. This is essentially due to the fact that the momentum of the drop sprays formed from the fuel injection are relatively small, with a directed introduction of this fuel into certain burner zones is deficient or not possible at all.

Because with such a constellation the fuel drops quickly from the to the Combustion air flowing into the premixing section can be braked are not well distributed radially in the incoming combustion air. The consequence from this defective premix, there is insufficient evaporation of the injected fuel, which is reflected in that on the burner axis form fuel-rich zones, which then cause in the combustion zone are responsible for an increased formation of thermal nitrogen oxides.

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 by which a perfect premix of the fuel used is guaranteed, while maintaining an operationally reliable and optimal flame positioning.

According to the invention, the injection of the fuel is proposed on a certain radius from the burner axis.

The main advantages of the invention are that enrichment the central zone is prevented, and the fuel drops increasing radius within the premixing section a stronger radial acceleration are exposed in such a way that they enter into the Can mix in combustion air well.

In the case of a premixing section consisting of several shells Swirl generator of a burner, as can be seen, for example, from EP-B1-0 321 809, works well as an injection position of the fuel in the wake zones along the leeward side of the corresponding shell, or the guide vanes of one appropriately designed swirl generator. The drop spray is less there exposed to aerodynamic forces, and it is therefore better radial mixed into the combustion air.

The number of injection points is adapted to the burner design, at least one injection per bowl or scoop is to be provided.

a) Stabile Flammenposition;

b) Tiefere Schadstoff-Emissionen (Co, UHC, NOx);

c) Minimierung der Pulsationen;

d) Vollständiger Ausbrand;

e) Grosse Betriebsbereich-Abdeckung;

f) Gute Querzündung zwischen den verschiedenen Brennern, insbesondere bei gestufter Lasterstellung, bei welcher dieBrenner untereinander interdependent betrieben werden;

g) Die Flamme kann der entsprechenden Brennkammergeometrie angepasst werden;

h) Kompakte Bauweise;

i) Verbesserte Mischung der Strömungsmedien;

j) Verbesserter "Patternfaktor" der Temperaturverteilung in der Brennkammer (= ausgeglichener Temperaturprofil der Brennkammerströmung).

According to the invention, the following further advantages result in connection with a premix burner of the newer generation:

a) Stable flame position;

b) Lower pollutant emissions (Co, UHC, NOx);

c) minimization of pulsations;

d) complete burnout;

e) Large operating area coverage;

f) Good cross-ignition between the different burners, especially with a stepped load position, in which the burners are operated interdependently with one another;

g) The flame can be adapted to the corresponding combustion chamber geometry;

h) compact design;

i) Improved mixing of the flow media;

j) Improved "pattern factor" of the temperature distribution in the combustion chamber (= balanced temperature profile of the combustion chamber flow).

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 Brenner mit anschliessender Brennkammer,

Fig. 2

einen Drallerzeuger in perspektivischer Darstellung, entsprechend aufge schnitten,

Fig. 3

einen Schnitt durch den 2-Schalen-Drallerzeuger, nach Fig. 2,

Fig. 4

einen Schnitt durch einen 4-Schalen-Drallerzeuger,

Fig. 5

einen Schitt durch einen Drallerzeuger, dessen Schalen schaufelförmig profiliert sind,

Fig. 6

eine Darstellung der Form der Uebergangsgeometrie zwischen Drallerzeu ger und Mischrohr,

Fig. 7

eine Abrisskante zur räumlichen Stabilisierung der Rückströmzone und

Fig. 8

einen Drallerzeuger mit einer Drallbeschaufelung.

It shows:

Fig. 1

a burner with subsequent combustion chamber,

Fig. 2

a swirl generator in perspective, cut accordingly,

Fig. 3

3 shows a section through the 2-shell swirl generator, according to FIG. 2,

Fig. 4

a section through a 4-shell swirl generator,

Fig. 5

a step through a swirl generator, the shells of which are profiled in a shovel shape,

Fig. 6

a representation of the shape of the transition geometry between the swirl generator and the mixing tube,

Fig. 7

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

Fig. 8

a swirl generator with a swirl blading.

WAYS OF CARRYING OUT THE INVENTION, INDUSTRIAL APPLICABILITY

Fig. 1 shows the overall structure of a burner. Initially there is a swirl generator 100 effective, the design of which is shown in more detail in the following FIGS. 2-5 is shown and described. This swirl generator 100 is a cone-shaped structure that tangentially inflows several times from a tangentially Combustion air flow 115 is applied. The one forming here Flow is provided based on a swirl generator 100 downstream Transition geometry seamlessly transferred into a transition piece 200, 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 on the outflow side of the transition geometry through a pipe 20 extended, both parts of the actual mixing tube 220, also mixing section called, form the burner. Of course, the mixing tube 220 can be made from one consist of only one piece, i.e. then that the transition piece 200 and Tube 20 are fused into a single coherent structure, keeping the characteristics of each part. Become a transition piece 200 and tube 20 created from two parts, so these are by one Socket ring 10 connected, this head side as an anchoring surface for serves the swirl generator 100. Such a sleeve ring 10 also has the Advantage that different mixing tubes can be used. Outflow side of the tube 20 is the actual combustion chamber 30, which is here is only symbolized by the flame tube. The mixing tube 220 fulfills that Condition that a defined mixing section is provided downstream of the swirl generator 100 in which a perfect premixing of different fuels Kind is achieved. This mixing section, ie the mixing tube 220, enables the further a loss-free flow control, so that there is also an operative connection cannot initially form a backflow zone with the transition geometry, with which over the length of the mixing tube 220 to the quality of the mixture for all types of fuel Influence can be exercised. This mixing tube 220 has another another property, which then is that in the mixing tube 220 itself Axial velocity profile has a pronounced maximum on the axis, so that the flame cannot be re-ignited from the combustion chamber. Indeed it is correct that with such a configuration this axial speed drops to the wall. To prevent reignition in this area, the mixing tube 220 becomes a number in the flow and circumferential directions regularly or irregularly distributed holes 21 different Provide cross sections and directions through which an amount of air enters the interior of the mixing tube 220 flows, and along the wall in the manner of a film induce an increase in speed. Another possibility To achieve the same effect, the flow cross section of the Mixing tube 220 downstream of the transition channels 201, which are already mentioned transition geometry form, undergoes a narrowing, whereby the entire speed level within the mixing tube 220 is raised becomes. In the figure, these bores 21 run at an acute angle the burner axis 60. Furthermore, the outlet corresponds to the transition channels 201 the narrowest flow cross section of the mixing tube 220. Die named transition channels 201 therefore bridge the respective cross-sectional difference, without negatively influencing the flow formed. If the chosen precaution in guiding the pipe flow 40 along the Mixing tube 220 triggers an intolerable pressure loss, can counteract this Remedy can be created by not at the end of the mixing tube in the figure shown diffuser is provided. At the end of the mixing tube 220 closes a combustion chamber 30, wherein between the two flow cross sections a cross-sectional jump is present. Only here does a central backflow zone form 50, which has the properties of a flame holder. Forms there is a flow within this cross-sectional jump during operation Edge zone, in which by the prevailing negative pressure Vertebral detachments occur, this leads to an increased ring stabilization the backflow zone 50. The combustion chamber 30 has a number of openings at the end 31 through which an amount of air jumps directly into the cross section flows, and there lower others help that the ring stabilization of the Backflow zone 50 is strengthened. In addition, it should not go unmentioned that the Generation of a stable backflow zone 50 also a sufficiently high one Twist number in a pipe required. If this is initially undesirable, you can stable return flow zones through the supply of small, strongly swirled air flows generated at the end of the tube, for example by tangential openings become. It is assumed here that the amount of air required for this in is about 5-20% of the total air volume. As for fuel injection in the swirl generator, reference is made to the following Fig. 2-5. The The configuration of the tear-off edge at the end of the mixing tube 220 is shown in FIG. 7 described in more detail.

In order to better understand the structure of the swirl generator 100, it is advantageous to if at least Fig. 3 is used at the same time as Fig. 2. Furthermore, in order not to make this Fig. 2 unnecessarily confusing, are the after Figure 3 schematically shown guide plates 121a, 121b only hinted at been. The following is the description of FIG. 2 as needed referred to the figures mentioned.

The first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 2 100. This consists of two hollow conical partial bodies 101, 102, which are nested in a staggered manner. The number of conical Partial body can of course be larger than two, like the examples 4 and 5 show. The number of conical partial bodies depends in each case depends on which operating mode is used. It is with certain operating constellations not ruled out a single spiral Provide swirl generator. The offset of the respective central axis or longitudinal symmetry axes 201b, 202b of the tapered partial bodies 101, 102 to one another creates a mirror image of the neighboring wall, one tangential channel each, i.e. an air inlet slot 119, 120 (FIG. 3), through which the combustion air 115 in the interior of the swirl generator 100, i.e. flows into the cone cavity 114 of the same. The cone shape of the partial body shown 101, 102 in the flow direction has a certain fixed angle. Of course, depending on the operational use, the partial bodies 101, 102 in Flow direction have an increasing or decreasing cone inclination, similar to a trumpet or Tulip. The latter two forms are not recorded in the drawing, since they can be easily understood by the expert are. The two conical partial bodies 101, 102 each have a cylindrical one Initial part 101a, 102a, which also, analogous to the conical partial bodies 101, 102, run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the swirl generator 100. In the area of the cylindrical initial part is a main nozzle 103, preferably for one liquid fuel 112 housed.

The fuel is introduced into the cone cavity 114 here a decentralized injection, which is carried out by a number of nozzle pipes 104 becomes. The angle of the fuel jet formed from these nozzle tubes 104 105 compared to the burner axis (Fig. 1, item 60) corresponds approximately the tapered course of the partial bodies 101, 102. If the swirl generator is characterized by an in blade configuration acting on a plane, the angle corresponds the fuel jet 105 the angle of attack of the blades compared to the Combustion chamber axis. In this connection, reference is made to FIG. 8. The preferably to be provided injection position of the fuel jet 105 with respect the inflow level of the combustion air 115 is closer to Fig. 3-5 explained. The injection capacity and injection type of the individual nozzle pipes 104 depends on the given parameters of the respective burner. Each depending on the burner size, turbulence-assisted Provide pressure atomization nozzle for the individual nozzle tubes 104, the Injection pressure to achieve good atomization qualities be around 100 bar should. The length of the nozzle tubes 104 is the required injection radius adjust, but should not be more than 1/4 of the partial body, respectively. Blade length (Fig. 8), otherwise there is an inherent risk that during operation with gaseous fuels, the nozzle tubes 104 act as a flame holder. For long partial body or blades (Fig. 8) a decentralized injection must be provided, in which the nozzle tubes 104 directly from the partial body, respectively. Shovels (Fig. 8) emerges in the wake flow. Thus, the fuel can be targeted Zones of high air velocity are sprayed. A company can also be operated Maintained with minimized pollutant emissions without the addition of water gets along. It is then essential that the fine atomization is connected with a high fuel pulse, good conditions for rapid evaporation of fuel as well as maximized premix.

Of course, the swirl generator 100 can be purely conical, that is to say without a cylindrical one Initial parts 101a, 102a. The tapered partial bodies 101, 102 have furthermore each have a fuel line 108, 109 which runs along the tangential Air inlet slots 119, 120 arranged and with injection openings 117 are provided, by means of which a gaseous fuel 113 in preferably the combustion air 115 flowing through there is injected, as is the case with the arrows 116 want to symbolize. These fuel lines 108, 109 are preferred at the latest at the end of the tangential inflow, before entering the cone cavity 114, placed this in order to obtain an optimal air / fuel mixture. The fuel 112 fed through the main nozzle 103 is concerned as mentioned, it is normally a liquid fuel, one of which is Mixture formation with another medium is easily possible. Is the combustion air 115 additionally preheated, or for example with a recycled flue gas or exhaust gas enriched, this supports sustainably the vaporization of the liquid fuel 112 within the length of the burner pre-mixing section before this mixture in the downstream Combustion stage flows. The same considerations also apply if liquid fuels should be supplied via lines 108, 109. When designing the tapered partial bodies 101, 102 with regard to the taper angle and the width of the tangential air inlet slots 119, 120 are narrow per se Adhere to limits so that the desired flow field of the combustion air 115 can set at the output of the swirl generator 100. General is to say that a reduction in tangential air inlet slots 119, 120 the faster formation of a backflow zone already in the area of the swirl generator favored. The axial speed within the swirl generator 100 can be by a corresponding supply of an axial combustion air flow 115a change, this air inflow being held so that the Fuel jet 105 is not affected or negatively influenced. A corresponding Swirl generation prevents the formation of flow separations within the the mixing tube 100 downstream of the swirl generator. The construction of the swirl generator 100 is also excellent, the size of the tangential Air inlet slots 119, 120 to change, so without changing the overall length of the swirl generator 100 a relatively large operational bandwidth can be detected can. Of course, the partial bodies 101, 102 are also in another Plane can be shifted towards each other, which even overlaps them can be provided. It is also possible to use the partial bodies 101, 102 can be nested spirally in one another by a counter-rotating movement. Thus, it is possible to change the shape, size and configuration of the tangential Air inlet slots 119, 120 to vary as desired, with which the swirl generator 100 can be used universally without changing its overall length.

3 now shows the geometric configuration of the guide plates 121a, 121b. They have a flow introduction function, and this, accordingly their length, the respective end of the tapered partial body 101, 102 in the direction of flow extend towards the combustion air 115. The channeling the combustion air 115 into the cone cavity 114 can be opened or closing the guide plates 121a, 121b by one in the area of the entrance thereof Channel in the cone cavity 114 pivot point 123 are optimized, this is particularly necessary if the original gap size of the tangential Air inlet slots 119, 120 are to be changed dynamically. Of course these dynamic arrangements can also be provided statically, by making required baffles an integral part with the tapered Form partial bodies 101, 102. The swirl generator 100 can also be used without Baffles are operated, or other aids can be provided for this become.

4 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. 5 differs from FIG. 4 in that the partial body 140, 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.

In the aforementioned FIGS. 3-5, that is within the flow cross section positioned one-tip positions of the fuel jet 105, which of the Flow of the combustion air corresponds to the opposite sides. Usually it will a nozzle tube is provided for each combustion air inflow, one such Assignment is not essential. Preferably the number of fuel jets adapted to the burner design. The individual fuel jets 105 are positioned in such a way that, in compliance with the procedure shown in FIG underlying angle of the fuel jet, along the leeward side of the partial body 101 and 102, 130-133, 140-143, as can be seen from FIGS. 3-5, respectively. of the guide vanes act in a configuration of the swirl generator according to FIG. 8. There the drop spray is exposed to lower aerodynamic forces, so that it is better mixed radially into the combustion air 115.

6 shows the transition piece 200 in a three-dimensional view. The transition geometry is corresponding for a swirl generator 100 with four partial bodies 4 or 5, 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 the wall of the tube 20 resp. of the mixing tube 220 cuts. The same considerations also apply if the swirl generator comes from another Principle, as that described under Fig. 2, is constructed. The down area of the individual transition channels 201 running in the direction of flow has a spiral shape in the flow direction, which has a describes crescent-shaped course, corresponding to the fact that present the flow cross section of the transition piece 200 in the flow direction flared. The swirl angle of the transition channels 201 in the flow direction is selected so that the pipe flow then up to the cross-sectional jump there is still a sufficiently large distance at the combustion chamber inlet, to achieve a perfect premix with the injected fuel. Furthermore, the measures mentioned above also increase the axial speed on the mixing tube wall downstream of the swirl generator. The Transition geometry and the measures in the area of the mixing tube a significant increase in the axial speed profile towards the center of the mixing tube, so that the risk of early ignition is decisively counteracted becomes.

7 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 as large as angle β. The benefits of this training are already below Chapter "Representation of the invention" discussed in more detail.

FIG. 8 shows a swirl generator 150 which uses swirl blading 151 is constructed. Concentric to the central main nozzle powered by fuel 112 103 a swirl generator is scheduled, which consists of a swirl blading 151 exists, i.e. the blades arranged in a ring effect here a swirl, analogous to that of Fig. 2. The combustion air supplied 115 can take place here using an annular channel, not shown in more detail, which extends upstream of the swirl blading 151. Downstream of the swirl blading 151, the central main fuel nozzle 103 has a number of nozzle pipes 104, whose fuel jet 105 is the angle of attack of the swirl blades 151 relative to the burner axis 60 respectively. the axis of the combustion chamber 30 corresponds. Here, too, the injection takes place in the wake zones along the The leeward side of the individual blades of this swirl blading 151 continues as follows has been extensively explained above, with this configuration according to 8 the same effects as set out above can be achieved.

Reference list

10th

Beech ring

20th

pipe

21

Holes, openings

30th

Combustion chamber

31

Openings

40

Flow, pipe flow in the mixing pipe

50

Backflow zone, backflow bubble

60

Burner axis

100

Swirl generator

101, 102

Partial body

101a, 102b

Cylindrical starting parts

101b, 102b

Longitudinal symmetry axes

103

Main fuel nozzle

104

Nozzle pipe

105

Fuel jet

108, 109

Fuel lines

112

Liquid fuel

113

Gaseous fuel

114

Cone cavity

115

Combustion air (combustion air flow)

115a

Axial 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

Swirl generator

151

Shovels

200

Transition piece

201

Transition channels

220

Mixing tube

d

Inner diameter of the tube 20

R

Transition radius

T

Tangent line of the tear-off edge

A

Tear-off edge

S

Demolition level

β

Transition angle from R

β '

Angle between T and A

Claims (20)

Burners for heat generation with an upstream of the combustion zone arranged swirl generator, which is in operative connection with at least is a fuel nozzle, characterized in that the Fuel nozzle (104) is arranged on the outflow side of the swirl generator (100, 150) and that the injection angle of the fuel nozzle (104) associated fuel jet (105) approximately the angle of attack of the Swirl generator elements (101, 102; 130-133; 140-143; 151) opposite corresponds to the axis (60) of the burner or the combustion chamber (30). Burner according to claim 1, characterized in that the fuel jet (105) along the side of the den Swirl generator (100, 150) forming elements is directed. Burner according to claim 1, characterized in that the swirl generator (100) from at least two hollow, conical, in the direction of flow there are nested partial bodies (101, 102; 130-133; 140-143), that the respective longitudinal symmetry axes (101b, 102b; 130a-133a; 140a-143a) these partial bodies run offset from one another, such that that the adjacent walls of the partial body in their longitudinal extent tangential channels (119, 120) for a flow of a combustion air flow (115) form. Burner according to claim 3, characterized in that an axial combustion air flow (115a) can be inserted into the swirl generator (100) on the head side is. Burner according to claim 1, characterized in that the swirl generator consists of a number of circularly arranged blades (151). Burner according to claims 1 to 4 or 1, 2 and 5, characterized in that that the number of fuel nozzles (104) is at least the number corresponds to the swirl-forming elements of the swirl generator (100, 150). Burner according to claim 3, characterized in that downstream of the Swirl generator (100) is arranged a mixing section (220), which within of a first section part (200) extending in the flow direction Transition channels (201) for transferring a swirl generator (100) flow (40) formed into a downstream of the transition channels (201) downstream pipe (20). Burner according to claim 7, characterized in that the exit plane of the tube (20) to the combustion chamber (30) with a tear-off edge (A) Stabilization and enlargement of a downstream backflow zone (50) is formed. Burner according to claim 7, 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 7, characterized in that that of the transition channels (201) downstream pipe (20) in the flow and circumferential direction with openings (21) for injecting an air flow into the interior of the tube (20) is provided. Burner according to claim 10, characterized in that the openings (21) at an acute angle with respect to the burner axis (60) of the Pipe (20) run. Burner according to claim 8, characterized in that the tear-off edge (A) from a transition radius (R) in the area of the exit plane of the Pipe (20) and one offset from the exit plane of the pipe (20) Demolition level (S) exists. Burner according to claim 12, characterized in that the transition radius (R) is> 10% of the inside diameter of the tube (20), and that the demolition step (S) has a depth> 3 mm. Burner according to claim 7, characterized in that the flow cross section the pipe (20) downstream of the transition channels (201) smaller, the same size or larger than the cross section of those in the swirl generator (100) formed flow (40). Burner according to claim 7, 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 claims 7 and 8, characterized in that upstream of the tear-off edge (A) there is a diffuser and / or a venturi section is. Burner according to claims 3 and 6, characterized in that in Area of the tangential channels (119, 120) in their longitudinal extension further fuel nozzles (117) are arranged. Burner according to claim 3, characterized in that the partial body (140-143) have a blade-shaped profile in cross section. Burner according to claim 3, characterized in that the partial body (101, 102; 130-133; 140-143) a fixed cone angle in the direction of flow, or an increasing taper, or a decreasing taper exhibit. Burner according to claim 3, characterized in that the partial body (101, 102; 130-133; 140-143) are nested in a spiral.

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