EP0924461B1 - Two-stage pressurised atomising nozzle - Google Patents

Description

Technical field

The invention relates to a two-stage pressure atomizing nozzle according to the preamble of claim 1, which, for example, in the premix burners of a gas turbine plant is used.

State of the art

With the increasing operating pressures of modern gas turbines, a good distribution becomes of liquid fuel is becoming a problem. The reasons are mainly in the increasing air density and in its momentum, which some have greater influence on the distribution of the fuel droplets.

EP 0 794 383 A2 has a two-stage pressure atomizing nozzle, which one Adjustment of the drop spray with regard to the atomization quality, the drop size and the spray angle to the respective load conditions. Farther the nozzle is characterized by a simple, little space requirement Type out. For this purpose, it comprises a nozzle body with an inside and communicating with an outside space via a nozzle bore Turbulence and / or swirl chamber. In addition, the pressure atomizer nozzle has at least a first channel for the liquid to be atomized, through which the latter can be fed under pressure. Opens into the turbulence and / or swirl chamber at least one further channel for part of the liquid to be atomized or for a second liquid to be atomized, through which said part of the Liquid or the second liquid can be supplied under pressure and with swirl.

However, it has been shown that ensuring an even fuel distribution even when using such a two-stage pressure atomizing nozzle with increasing size of the burners, i.e. in a development like this, for example when comparing Figures 12 and 17 of EP 0 794 383 A2 clearly is recognizable, becomes more difficult. This is due to the overwhelming influence attributed to the air by the distribution of the fuel droplets as also on the increasing diameter of the burners or on the opening angle their swirl generator.

The air around the central fuel nozzle of such a large burner flows, remains mainly in the area of the burner axis. Can do almost the whole The amount of fuel carried by this air is generated with fuel enriched center, with no large amounts of liquid fuel in the reach the outer area. Therefore, the main vaporization of the fuel takes place often takes place before the fuel droplets reach the desired points on the Brenners, i.e. reach its outer areas. So in this case large NOx emissions and a flashback are caused.

In order to inject the fuel droplets into the outer areas of the To realize the burner, swirl nozzles with large jet angles are often used. Such a swirl nozzle injects in the right direction, but it does the small droplets it produces do not have sufficient momentum to the liquid fuel before it is vaporized or before it is influenced by to transport the air to the outer areas of the burner. Because of the large scatter in the initial distribution of droplet sizes on the other hand, large drops get into the outer areas. These drops However, they are not vaporized and can ultimately reach the burner walls hit, with the danger of the flame striking back in the wall Flow regions.

If, on the other hand, a turbulence-enhanced device known for example from EP 0 794 383 A2 is used Used fuel jet, this produces large drops, with one sufficiently high momentum to get through the air field. These rays however have a small angle of propagation and cause the drops not to spread evenly in all directions.

Presentation of the invention

The invention tries to avoid all of these disadvantages. You have the task based on a two-stage pressure atomizing nozzle for at least one to be atomized To create fluid with which an improved fluid distribution in the outside of the pressure atomizer nozzle, in particular a better fuel distribution in a premix burner.

According to the invention, this is achieved in that with a device according to the preamble of claim 1, the pressure atomizing nozzle an the outside and the inner tube has a nozzle head connecting one another downstream and in Nozzle head arranged at least two separate turbulence and / or swirl chambers are. Each of these turbulence and / or swirl chambers is over at least one Swirl duct with the second feed duct, via at least one turbulence generator duct with the first feed channel and via an outlet opening to the outside space of the nozzle body connected.

This creates a multi-point injection system with at least two outlet openings, which is a change in atomization quality, speed as well as the direction of the liquid and thus an adjustment of the atomization and the distribution of the liquid to the respective load condition allowed. The Outlet openings, each of which is only a part of the total liquid mass flow can be made smaller than that of a nozzle is possible with only one outlet opening. With the same liquid mass flow however, smaller outlet openings in the swirl stage create a substantial one thinner liquid film, resulting in smaller droplets with less in the swirl stage Depth of entry are produced. That is why the range of uses of Pressure atomizer nozzle advantageously also shifted in the direction of part-load operation.

The nozzle body and the turbulence and / or swirl chambers each have one Central axis. The central axes of the turbulence and / or swirl chambers are radial offset to the central axis of the nozzle body, preferably both radially and arranged obliquely to the central axis of the nozzle body in the tangential direction. In general, this can result in better liquid distribution over large areas Cross-sectional areas can be achieved. When designing the pressure atomizer nozzle the radial displacement and the inclination of the central axes of the turbulence and / or swirl chambers to the central axis of the nozzle body to the desired Adjusted spraying directions of the sprays being formed.

Between the first feed channel and each of the turbulence and / or swirl chambers is a sealing cover which receives the at least one turbulence generator channel arranged. This results in a relatively simple manufacture of the turbulence and / or swirl chambers guaranteed, for example by milling or drilling into the nozzle head and then using the mounting cover to be covered upstream. By the arrangement the turbulence generator duct in the outer area of the respective cover, can increase the turbulence of the liquid used and therefore a finer spray can be achieved.

In addition, the first feed channel opens into a first, upstream of the cover trained plenum, while between the second feed channel and the a second, rotating plenum is formed. As a result, all turbulence and / or swirl chambers can advantageously be used with only one first and only a second feed line can be provided, which is a very compact trained nozzle body allows. The first one is particularly advantageous Plenum has a larger cross-section than the feed channel acting on it, whereby a more uniform fluid loading of the turbulence and / or Swirl chambers is reached. The cross sections have the same advantage of the two plenums also larger than the sum of the cross sections of the Turbulence generator or swirl channels acted upon them.

It is particularly useful if all turbulence and / or swirl chambers are equally large. In this way, an even liquid distribution be guaranteed in the outer space of the nozzle body.

In addition, the nozzle head is hemispherical in its downstream area educated. This can lead to the emergence of a so-called dead water area in the wake of the nozzle and thus possibly connected with droplet deposits Flow separations can be counteracted. In this hemispherical Recesses are made in the contour of the nozzle head, with each outlet opening opens into one of the recesses and each recess is rectangular is arranged to the outlet opening into it. Because of this design of the outlet area can be the liquid distribution in the exterior of the nozzle body can be further improved.

In one embodiment of the invention, the nozzle body is with a premix burner connected that its exterior space is simultaneously an interior space of the Premix burner is. The premix burner consists essentially of four in Hollow partial cone bodies positioned one on top of the other with a constant cone half angle β in the direction of flow. The longitudinal symmetry axes the partial cone body are radially offset from one another, so that four flow opposite, tangential air inlet slots for a combustion air flow are trained. The nozzle body is in through the tapered body formed, hollow cone-shaped interior of the premix burner. Downstream of each partial cone body is a trailing area of the partial cone body educated. There are four turbulence and / or in the nozzle head of the pressure atomizing nozzle Swirl chambers arranged, the outlet openings of which on the wake area of the adjacent partial cone body are aligned.

In this embodiment of the invention, the fuel mass flow is over the turbulence and / or swirl chambers are divided into four equal partial flows. Since the Turbulence and / or swirl chambers each have a smaller outlet opening, than that with only one turbulence and / or swirl chamber with a single one Outlet opening can be realized, a thinner fuel spray can thus be generated become. This results in smaller droplets of fuel, which are smaller Penetration depth into the burner interior and much faster, i.e. Vaporize before hitting the inner wall of the partial cone body. As a result of Alignment of the outlet openings of the turbulence and / or swirl chambers on the Trailing areas of the partial cone bodies, the fuel droplets are smaller exposed to aerodynamic forces and can therefore do better in the radial direction penetrate the combustion air. Ultimately this will result in the exit of the Brenners a uniform liquid fuel vapor distribution and thus one enables improved combustion.

Such a pressure atomizing nozzle or the burner equipped with it can by simply regulating the fuel supply, i.e. by switching from turbulence operation to the swirl operation or mixed operation to the full load or part load requirements be adjusted. Because of the versatile switch options between swirl-enhanced and turbulence-enhanced spray mist is the solution applicable to most machine and performance conditions.

Brief description of the drawing

In the drawing, two embodiments of the invention are based on one two-stage pressure atomizer nozzle shown.

Fig. 1

die Druckzerstäuberdüse in perspektivischer Darstellung;

Fig. 2

eine Draufsicht auf die Druckzerstäuberdüse, gemäss Fig. 1;

Fig. 3

einen Schnitt durch die Druckzerstäuberdüse, entlang der Linie III-III in Fig. 2, verkleinert dargestellt;

Fig. 4

einen Schnitt durch die Druckzerstäuberdüse, entlang der Linie IV-IV in Fig. 2, verkleinert dargestellt;

Fig. 5

einen Schnitt durch die Druckzerstäuberdüse, entlang der Linie V-V in Fig. 2, verkleinert dargestellt;

Fig. 6

eine Ansicht der Druckzerstäuberdüse, gemäss Fig. 1, jedoch von unten;

Fig. 7

einen Vormischbrenner mit integrierter Druckzerstäuberdüse;

Fig. 8

einen Schnitt VIII-VIII durch den Vormischbrenner, gemäss Fig. 7.

Show it:

Fig. 1

the pressure atomizing nozzle in a perspective view;

Fig. 2

a plan view of the pressure atomizing nozzle, according to FIG. 1;

Fig. 3

a section through the pressure atomizing nozzle, along the line III-III in Fig. 2, shown reduced;

Fig. 4

a section through the pressure atomizing nozzle, along the line IV-IV in Fig. 2, shown reduced;

Fig. 5

a section through the pressure atomizing nozzle, along the line VV in Fig. 2, shown reduced;

Fig. 6

a view of the pressure atomizing nozzle, according to Figure 1, but from below.

Fig. 7

a premix burner with integrated pressure atomizing nozzle;

Fig. 8

a section VIII-VIII through the premix burner, according to FIG. 7.

Only the elements essential for understanding the invention are shown. For example, the combustion chamber receiving the premix burner is not shown and the gas turbine connected to it. The flow direction of the Work equipment is indicated by arrows.

Way of carrying out the invention

The pressure atomizer nozzle has a nozzle body 1, which consists of an outer tube 2 and an inner tube 3 and downstream of a nozzle head 4 is completed (Fig. 1, Fig. 2). In the inner tube 3 is a first feed channel 5 and between the outer tube 2 and the inner tube 3, a second feed channel 6 for formed at least one liquid fuel 7. Is upstream of the nozzle head 4 between the inner tube 3 and the outer tube 2 is used for stabilization Spacer 8 arranged. The nozzle head 4 takes four equally large turbulence and / or swirl chambers 9, 10, 11, 12. Of course, the turbulence and / or Swirl chambers 9, 10, 11, 12 under appropriate operating conditions also have a different size (not shown), but on it It is important to ensure that there is always a symmetrical injection.

Both the turbulence and / or swirl chambers 9, 10, 11, 12 and the nozzle body 1 each have a central axis 9 ', 10', 11 ', 12', 13, the central axes 9 ', 10', 11 ', 12' of the turbulence and / or swirl chambers 9, 10, 11, 12 both in radial as well as in the tangential direction obliquely to the central axis 13 of the nozzle body 1 are arranged. An imaginary plane cuts through the central axis 13 of the nozzle body 1, the imaginary planes through the central axes 9 ', 10 ', 11', 12 'of the turbulence and / or swirl chambers 9, 10, 11, 12 inside the Nozzle head 4 both in a radial and in a tangential angle (Fig. 3). The location of the turbulence and / or swirl chambers 9, 10, 11, 12 inside of the nozzle head 4 is also in FIGS. 4 and 5 corresponding to that in FIG. 2 shown cuts shown. With a concrete pressure atomizer nozzle the inclination of the central axes 9 ', 10', 11 ', 12' to the central axis 13 of the Nozzle body 1 according to the desired injection directions of the developing Fuel sprays 37. According to the specific operating conditions of the Pressure atomizing nozzle can the central axes 9 ', 10', 11 ', 12' of the turbulence and / or Swirl chambers 9, 10, 11, 12 therefore only offset parallel to the central axis 13 of the nozzle body 1 may be arranged.

Each of the turbulence and / or swirl chambers 9, 10, 11, 12 is by means of a sealing cover 14 to the first feed channel 5 completed. In the outer area of each cover 14, two turbulence channels 15 are arranged, which the respective turbulence and / or swirl chamber 9, 10, 11, 12 with the first Connect feed channel 5. In addition, the turbulence and / or swirl chambers 9, 10, 11, 12 each via a swirl duct 16 with the second feed duct 6 (FIG. 1, Fig. 2) and each connected to an outer space 18 via an outlet opening 17 (Fig. 3, Fig. 6). The nozzle body 1 thus has four outlet openings 17, which each only let through a quarter of the total fuel mass flow. For this purpose, they are designed to be smaller than one that takes up the entire mass flow Single hole nozzle and produce at similar liquid fuel pressures smaller droplets.

In its downstream area, the nozzle head 4 is hemispherical, each outlet opening 17 into a in the hemispherical contour of the nozzle head 4 introduced recess 19 opens and each recess 19th arranged at right angles to the outlet opening 17 each opening into it is. Of course, any other streamlined design of the downstream is Area of the nozzle head 4 suitable, for example an elliptical shape.

A first plenum 20 is formed upstream of the closure cover 14, into which the first feed channel 5 opens. The first plenum 20 has a larger one Cross-section than the feed channel 5 which acts on it second feed channel 6 and the swirl channels 16 connected to it is a second, circumferential plenum 21 is formed. The cross sections of the two plenums 20, 21 are designed to be larger than the sum of the cross sections of those to which they are subjected Turbulence generator channels 15 or swirl channels 16. This is a more compact one Nozzle body 1 realized, which consists of four partial nozzles, each with a turbulence as well as a swirl stage, with a common geometry and with a uniform Diameter exists.

The liquid fuel 7 is supplied to the nozzle body 1 in a manner known per se Way over lines not shown, such as in EP 0 794 383 A2 shown and described.

When operating the turbulence stage, the liquid fuel 7 passes through the first Feed channel 5 into the first plenum 20. From there it is through the turbulence channels 15 the cap 14 as a turbulent flow in the respective turbulence and / or swirl chamber 9, 10, 11, 12 initiated. Because of the compared to the first feed channel 5 enlarged cross section of the first plenum 20 a relatively uniform application of liquid to the turbulence and / or swirl chambers 9, 10, 11, 12 reached. The injection is then carried out of liquid fuel 7 into the outside space 18, via the outlet openings 17 of the turbulence and / or swirl chambers 9, 10, 11, 12 Turbulence and / or swirl chambers 9, 10, 11, 12 four fuel sprays of the same size 37 with an improved droplet distribution. Because of the right angle injection of the liquid fuel 7 into the respective recess 19 the outside space 18 circular fuel sprays 37 are formed, what fuel distribution further improved.

In contrast, the swirl stage via the second feed channel 6 with liquid fuel 7 acted upon. The latter first reaches the second plenum 21 and from there it is evenly distributed over the tangential swirl channels 16 divided into the turbulence and / or swirl chambers 9, 10, 11, 12.

Of course, in the partial load range there is also a combination of partially turbulence-reinforced Operation and partial swirl operation possible. In this case, the Arrangement of the turbulence channels 15 in the outer region of the cover 14, i.e. near the side walls of the turbulence and / or swirl chambers 9, 10, 11, 12 contribute to the fact that the liquid fuel full cone spray, not shown forms evenly and thus the distribution of the fuel droplets is further improved.

In a second exemplary embodiment of the invention, the nozzle body 1 is also included connected to a premix burner 22 that the outer space 18 of the nozzle body 1 is at the same time an interior 18 'of the premix burner 22 (FIG. 7). The Premix burner 22 is a cone-shaped structure and essentially consists from four superimposed hollow partial cone bodies 23, 24, 25, 26 with one constant cone half angle β to the burner axis in the direction of flow 27. Im narrowest cross section of the hollow cone-shaped body formed by the partial cone bodies 23, 24, 25, 26 Interior 18 'of the premix burner 22 is the nozzle body 1 arranged. Analogously to FIGS. 1 to 6, the nozzle body 1 has four turbulence and / or Swirl chambers 9, 10, 11, 12 each with an outlet opening 17.

The partial cone bodies 23, 24, 25, 26 each have an axis of longitudinal symmetry 23 ', 24', 25 ', 26'. The latter run radially offset from one another, so that four flow opposite, tangential air inlet slots 28 for a combustion air mass flow 29 are formed (Fig. 8). In addition, the Partial cone bodies 23, 24, 25, 26 along the air inlet slots 28 each have a feed line 30, which has longitudinal openings 31 for supplying a gaseous fuel 32 are provided in the interior 18 'of the premix burner 22 (FIG. 7). If necessary, this fuel 32 becomes through the tangential air inlet slots 28 admixed combustion air mass flow 29 introduced into the interior 18 '. A mixed operation of the premix burner 22 via the pressure atomizing nozzle and the feed lines 30 is possible.

When the premix burner 22 is operated via the pressure atomizing nozzle, is dependent both of the material thickness of its partial cone bodies 23, 24, 25, 26 as also from the flow velocity of the combustion air mass flows 29, downstream of each partial cone body 23, 24, 25, 26 inevitably a trailing area 33, 34, 35, 36, in which there are significantly lower aerodynamic forces than in the adjacent areas of the interior 18 '. Each of the four outlet openings 17 of the turbulence and / or swirl chambers 9, 10, 11, 12 is on one of the trailing areas 33, 34, 35, 36 of the partial cone bodies 23, 24, 25, 26 aligned. This turns the liquid fuel 7 into four separate fuel sprays 37 via the outlet openings 17 into the interior 18 'of the premix burner 22, more precisely in the trailing areas 33, 34, 35, 36 of the partial cone body 23, 24, 25, 26 of the premix burner 22, injected. As a result of this alignment of fuel sprays 37 are the lower aerodynamic fuel droplets Exposed to forces and are therefore better radially into the combustion air mass flows 29 mixed in. The improved premix leads to a uniformly prepared firing mixture at the end of the burner and thus to improved combustion with significantly lower NOx values.

At full load of a gas turbine, not shown, connected to a combustion chamber the pressure atomizing nozzles will each act on the combustion chamber Premix burner 22 operated almost entirely via its turbulence stage. As a result, fuel sprays 37 with small, to the burner inner walls 38th aligned angles and generated with large droplet pulses. These droplets of fuel penetrate into the surrounding, from the combustion air mass flow 29 air fields formed and reach the outer areas in large numbers of the interior 18 'of the premix burner 22. In this way finally, a uniform fuel-vapor profile is formed at the burner outlet become.

In general, the combustion air mass flow 29 and thus at partial load also reduces its momentum, which necessitates a lower fuel mass flow, a lower spray impulse and therefore smaller fuel droplets causes. Therefore, the respective swirl stage of the pressure atomizing nozzles in this operating state the gas turbine is subjected to a greater load than the turbulence stage. An increasing swirl ratio gradually and automatically reduces the mass flow of liquid fuel 7. Because the swirl stage also has a lower Mass flow realized as the turbulence stage, the amount of fuel drops of liquid fuel 7 accordingly. About an increase in droplet size and thus the impact of the fuel droplets on the inner walls 38 of the burner to prevent the transition from the turbulence stage towards the swirl stage. In contrast, when the gas turbine load decreases, i.e. with further decreasing Influence of the combustion air mass flow 29 through the transition to one full swirl operation, further reducing the droplet size of the Liquid fuel 7 reached.

Of course, the premix burner can also, according to EP 0 704 657 A2 consist of a swirl generator and a downstream mixing tube, the swirl generator being essentially the premix burner described above 22 corresponds or also a solution for double cone burners i.e. can be realized for a premix burner with two partial cone bodies (not shown). Likewise, the premix burner cannot be conical and / or consist of a number of circularly arranged blades (likewise not shown).

LIST OF REFERENCE NUMBERS

1

nozzle body

2

outer tube

3

inner tube

4

nozzle head

5

Feed channel, first

6

Feed channel, second

7

liquid fuel

8th

spacer

9

Turbulence and / or swirl chamber

10

Turbulence and / or swirl chamber

11

Turbulence and / or swirl chamber

12

Turbulence and / or swirl chamber

13

Central axis, from 1

14

cap

15

Turbulence generator duct

16

swirl channel

17

outlet opening

18

Outside space from 1

19

recess

20

Plenary, first

21

Plenum, second

22

premix

23

Partial conical bodies

24

Partial conical bodies

25

Partial conical bodies

26

Partial conical bodies

27

Brenner

28

Air inlet slot

29

Scales combustion mass flow

30

supply

31

opening

32

Fuel, gaseous

33

Trail area, from 23

34

Trail area, from 24

35

Trail area, from 25

36

Trail area, from 26

37

Fuel spray, spray

38

Brenner inner wall

9 '

Central axis, from 9

10 '

Central axis, from 10

11 '

Central axis, from 11

12 '

Central axis, from 12

18 '

Interior of 22

23 '

Longitudinal symmetry axis, from 23

24 '

Longitudinal axis of symmetry, from 24

25 '

Longitudinal symmetry axis, from 25

26 '

Longitudinal symmetry axis, from 26

β

Cone half angle

Claims (11)

1. Two-stage pressure atomizer nozzle for at least one liquid to be atomized, having a nozzle body (1) consisting of an outer tube (2) and an inner tube (3), a first feed passage (5) being formed in the inner tube and a second feed passage (6) being formed between the outer tube and the inner tube, both feed passages leading into a turbulence and/or swirl chamber (9, 10, 11, 12), and the latter being connected to an exterior space (18) via a discharge opening (17), characterized in that

   a) the nozzle body (1) has a nozzle head (4) connecting the outer and inner tubes (2, 3) to one another downstream,

   b) at least two separate turbulence and/or swirl chambers (9, 10, 11, 12) are arranged in the nozzle head (4),

   c) each of the turbulence and/or swirl chambers (9, 10, 11, 12) is connected to the second feed passage (6) via at least one swirl passage (16), to the first feed passage (5) via at least one turbulence-generator passage (15) and to the exterior space (18) via a discharge opening (17).
2. Two-stage pressure atomizer nozzle according to Claim 1, characterized in that the nozzle body (1) and the turbulence and/or swirl chambers (9, 10, 11, 12) each have a centre axis (13, 9', 10', 11', 12'), and the centre axes (9', 10', 11', 12') of the turbulence and/or swirl chambers (9, 10, 11, 12) are arranged so as to be radially offset from the centre axis (13) of the nozzle body (1), preferably at an angle to the centre axis (13) of the nozzle body (1) in both the radial and tangential directions.
3. Two-stage pressure atomizer nozzle according to Claim 2, characterized in that a cover lid (14) accommodating the at least one turbulence-generator passage (15) is arranged between each turbulence and/or swirl chamber (9, 10, 11, 12) and the first feed passage (5).
4. Two-stage pressure atomizer nozzle according to Claim 3, characterized in that the at least one turbulence-generator passage (15) is arranged in the outer region of the respective cover lid (14).
5. Two-stage pressure atomizer nozzle according to Claim 3 or 4, characterized in that the first feed passage (5) leads into a first plenum (20) formed upstream of the cover lid (14), and a second, encircling plenum (21) is formed between the second feed passage (6) and the swirl passages (16) connected to the latter.
6. Two-stage pressure atomizer nozzle according to Claim 5, characterized in that the first plenum (20) has a larger cross section than the feed passage (5) admitting liquid to it.
7. Two-stage pressure atomizer nozzle according to Claim 5, characterized in that the cross section of the first plenum (20) is larger than the sum of the cross sections of the turbulence-generator passages (15), and the cross section of the second plenum (21) is larger than the sum of the cross sections of the swirl passages (16).
8. Two-stage pressure atomizer nozzle according to Claim 6 or 7, characterized in that all the turbulence and/or swirl chambers (9, 10, 11, 12) are designed to be the same size.
9. Two-stage pressure atomizer nozzle according to Claim 8, characterized in that the nozzle head (4) is of hemispherical design in its downstream region, and a number of recesses (19) corresponding to the number of discharge openings (17) are made in the hemispherical contour of the nozzle head (4), each discharge opening (17) leading into one of the recesses (19), and each recess (19) being arranged at right angles to the discharge opening (17) leading into it in each case.
10. Two-stage pressure atomizer nozzle according to one of the preceding claims, characterized in that the nozzle body (1) is connected to a premix burner (22), and the exterior space (18) of the nozzle body (1) is at the same time an interior space (18') of the premix burner (22).
11. Two-stage pressure atomizer nozzle according to Claim 10, characterized in that

    a) four turbulence and/or swirl chambers (9, 10, 11, 12) are arranged in the nozzle head (4),

    b) the premix burner (22) essentially comprises four hollow sectional cone bodies (23, 24, 25, 26) which are positioned one upon the other in the direction of flow and have a constant cone half angle β in the direction of flow and whose longitudinal symmetry axes (23', 24', 25', 26') run radially offset from one another, so that four fluidically opposed, tangential air-inlet slots (28) for a combustion-air mass flow (29) are formed,

    c) the nozzle body (1) is arranged in the hollow conical interior space (18'), formed by the sectional cone bodies (23, 24, 25, 26), of the premix burner (22),

    d) a wake zone (33, 34, 35, 36) is formed downstream of each sectional cone body (23, 24, 25, 26), and

    e) each discharge opening (17) of the turbulence and/or swirl chambers (9, 10, 11, 12) is oriented to the wake zone (33, 34, 35, 36) of the sectional cone body (23, 24, 25, 26) adjacent to it.

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