EP0924460A1 - Two-stage pressurised atomising nozzle - Google Patents

Abstract

Both feed channels issue in a turbulence and/or swirl chamber limited by a first closure component in relation to an outer spade and by a second closure component in relation to the first feed channel. At least one connecting channel in the second closure component is connected with the first feed channel and via an outlet aperture in the first closure component with the outer space. In the turbulence and/or swirl chamber a separate central changeover body (16) divides the chamber into at least two part chambers. Each part chamber via at least one turbulence producer channel (18) is connected with the first feed channel (6), via at least one swirl channel (11) with the second feed channel (7) and via an outlet aperture (13) with the outer space.

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 is a 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 creates a very fuel-enriched one 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 Brenner, i.e. reach its outer areas. So in this case large NOx emissions are caused.

In order to inject the fuel droplets into the outer areas of the To produce burners, 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 evaporated 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 risk of the flame striking back in the wall Flow areas.

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 relatively simple and inexpensive two-stage pressure atomizing nozzle for at least one liquid to be atomized, with which one improved liquid distribution in the outer space of the pressure atomizing nozzle, in particular better fuel distribution in a premix burner can be.

According to the invention, this is achieved in that with a device according to the preamble of claim 1, in the turbulence and / or swirl chamber separate deflecting body is arranged centrally, which the turbulence and / or Swirl chamber divided into at least two subchambers. In addition, each sub-chamber via at least one turbulence generator channel with the first feed channel, via at least one swirl duct with the second feed duct and via an outlet opening connected to the outside space.

This creates a multi-point injection system with at least two outlet openings, which is an adjustment of the atomization quality, the 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, which is only a part of the total liquid mass flow can be made smaller than with a nozzle only one outlet opening is possible. Generate with the same liquid mass flow smaller outlet openings but a much thinner jet of liquid, resulting in smaller droplets with a lower entry depth in the swirl stage to be produced. That is why the application range of the pressure atomizer nozzle advantageously also shifted towards part-load operation. Because the training of the partial chambers is reached in the radial direction solely via the deflecting body and the latter as a separate insert for the turbulence and / or swirl chamber is designed in addition to the improved function of the pressure atomizing nozzle also realize a separate production of the deflecting body. Since that too Assembling the deflecting body with the rest of the pressure atomizing nozzle relatively can be done easily, there is ultimately a significantly cheaper nozzle Available.

The deflecting body is particularly advantageous at least on the second closure element attached. Such training facilitates the manufacture of the pressure atomizing nozzle in that the second closure element together with the deflecting body can be mounted. Alternatively, the deflecting body is located at least on the second closure element of the turbulence and / or swirl chamber and has a press fit to the inner tube. This can also simple manufacture of the pressure atomizing nozzle and a defined position of the Partial chambers can be realized.

Another advantageous variant for the arrangement of the deflecting body is that one of the number of sub-chambers between the deflecting body and the inner tube corresponding and connecting the latter in their outer area Number of free spaces is formed and the deflecting body also at least abuts the second closure element of the turbulence and / or swirl chamber. On this way it occurs in each of the free spaces, i.e. in the radially outer area of the sub-chambers, to a parallel and rectified course of the liquid flows neighboring subchambers. However, since the friction between two Currents is smaller than between a current and a solid body, can lower pressure loss and consequently better atomization of the Liquids can be reached. In addition, this arrangement variant is also a simple and therefore inexpensive assembly of the pressure atomizer nozzle is guaranteed.

It is also advantageous if the turbulence and / or swirl chamber through the Deflection body is divided into four sub-chambers, the deflection body with an inner, at least approximately centrally arranged and on the connecting channel of the second closure element connecting distribution channel and this distribution channel via each of the turbulence channels with each the subchambers is connected. There are also four with the second in the inner tube Feed channel connected swirl channels formed and each eccentrically into a of the sub-chambers arranged in the mouth.

According to this formation of the turbulence stage, the atomizing liquid via the first feed channel and the connecting channel into the distribution channel of the deflecting body and there via the turbulence generator channels evenly distributed across the four subchambers. When initiating the liquid flows In the subchambers, the strongly swirled already mentioned arises Flow that propagates downstream of the outlet openings. To this Wise, with constant atomization of the liquid, becomes a narrower one Spray angle of the four resulting liquid sprays realized. Thus, the The depth of penetration of the liquid spray increases and thereby a good radial Distribution of the liquid can be achieved.

In the swirl stage, the four are introduced into the subchambers via the swirl channels Partial flows of the liquid to be atomized into a directed swirl flow converted. This alignment also described above the swirl flow is caused by the eccentric injection of the partial flows into the Partial chambers reinforced. The directional swirl flow also settles downstream of the outlet openings so that even with low liquid flow a sufficiently high pressure drop for atomization through these outlet openings is available. Because of the relatively wide spray cone in the swirl stage the spray has a lower impulse current density and thus a lower penetration depth. This can result in a high liquid concentration in the center even at partial load the outside of the nozzle and sufficient liquid evaporation be achieved. This enables stable nozzle operation in the partial load range.

Both the turbulence generator channels and the swirl channels are advantageous in arranged upstream of the upstream region of the partial chambers. Because of this is an early injection of the liquid into the sub-chambers reached, so that in the turbulence stage a strongly swirled flow and in the swirl stage can form a directional swirl flow.

It is particularly expedient if all subchambers are of the same size are. In this way, a uniform liquid distribution in the outside space the pressure atomizer nozzle can be guaranteed.

According to one embodiment of the invention, the deflecting body is in cross section star-shaped. This creates a streamlined geometry Partial chambers generated, which for a good deflection of the eccentrically entering Liquid and thus for an improvement of the already described above, directional swirl flow.

In a further embodiment of the invention, the deflecting body is in cross section double ax-shaped, with two first bars and two at right angles to it arranged, second webs formed. The first two webs run each sickle-shaped, while the two second webs at least approximately each have parallel sides. Two of the swirl channels are at least approximately parallel to each other, one of the two second webs on both sides arranged opening into the subchambers. In this way, a changed one arises Geometry of the subchambers with further improved deflection properties for the swirl flow.

Finally, the pressure atomizing nozzle is advantageously used with a premix burner connected that the outside of the pressure atomizing nozzle at the same time is an interior of the premix burner. To do this, there is the premix burner in the essentially of four hollow ones positioned one on top of the other in the direction of flow Partial cone bodies with a constant cone half angle β in the direction of flow. The longitudinal symmetry axes of the partial cone bodies are radially offset from one another, so that there are four opposite, tangential air inlet slots are designed for a combustion air flow. Here is the pressure atomizer nozzle or their nozzle body in the part cone body, arranged hollow conical interior of the premix burner. Each partial cone body has a wake area downstream. In the turbulence and / or Swirl chamber are formed four sub-chambers, the outlet openings each aligned to the trailing area of the adjacent partial cone body are.

In this embodiment of the invention, the fuel mass flow is over the sub-chambers divided into four equal sub-streams. Because the subchambers each have a smaller outlet opening than that with only one turbulence and / or Swirl chamber with a single outlet opening can be realized thus thinner fuel sprays are generated. As a result, smaller ones emerge Fuel droplets, which have a lower penetration depth into the interior of the burner and much faster, i.e. before hitting the inside wall of the Partial cone body, evaporate. Due to the alignment of the outlet openings of the Partial chambers on the side of the partial cone body facing away from the combustion air flow the fuel droplets are exposed to lower aerodynamic forces and are therefore better mixed radially into the combustion air. Ultimately, this results in an even distribution of oil vapor at the burner outlet and thus 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 to a mixed operation at the full load or Partial load requirements of a gas turbine can be adjusted. The burner can be used throughout Load range of the gas turbine in premix mode. At full load are high Penetration depths of the fuel spray possible without causing problems under partial load e.g. comes through wall application of fuel drops. Because the deflector constantly flowed through by the fuel of the turbulence stage and thus cooled cooling of the swirl stage is not necessary during the switching process, so that a fast load change can also be realized. Because of the versatile Switching options between swirl-enhanced and turbulence-enhanced Spray is the solution for most machine and performance conditions applicable.

Brief description of the drawing

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

Fig. 1

einen Längsschnitt durch eine Druckzerstäuberdüse des Standes der Technik;

Fig. 2

einen Längsschnitt durch eine erfindungsgemässe Druckzerstäuberdüse, in einem ersten Ausführungsbeispiel;

Fig. 3

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

Fig. 4

eine Darstellung analog der Fig. 2, jedoch entlang der Linie IV-IV in Fig. 3 geschnitten;

Fig. 5

eine vergrösserte, perspektivische Ansicht der Turbulenz- und/oder Drallkammer beim Einsatz als Turbulenzstufe, dargestellt gemäss Fig. 2 und 4, jedoch um 90° gedreht;

Fig. 6

eine Darstellung der Turbulenz- und/oder Drallkammer analog Fig. 5; jedoch beim Einsatz als Drallstufe;

Fig. 7

einen Darstellung analog Fig. 4, jedoch in einem zweiten Ausführungsbeispiel;

Fig. 8

eine Darstellung analog Fig. 3, jedoch entsprechend dem Ausführungsbeispiel gemäss Fig. 7;

Fig. 9

einen Vormischbrenner mit integrierter Druckzerstäuberdüse;

Fig. 10

einen Schnitt X-X durch den Vormischbrenner.

Show it:

Fig. 1

a longitudinal section through a pressure atomizing nozzle of the prior art;

Fig. 2

a longitudinal section through a pressure atomizing nozzle according to the invention, in a first embodiment;

Fig. 3

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

Fig. 4

a representation analogous to Figure 2, but cut along the line IV-IV in Fig. 3.

Fig. 5

an enlarged, perspective view of the turbulence and / or swirl chamber when used as a turbulence stage, shown in Figures 2 and 4, but rotated by 90 °.

Fig. 6

a representation of the turbulence and / or swirl chamber analogous to FIG. 5; however when used as a swirl stage;

Fig. 7

a representation analogous to Figure 4, but in a second embodiment;

Fig. 8

a representation analogous to FIG. 3, but corresponding to the embodiment of FIG. 7;

Fig. 9

a premix burner with integrated pressure atomizing nozzle;

Fig. 10

a section XX through the premix burner.

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 two-stage pressure atomizer nozzle of the prior art shown in FIG Technology has a nozzle body 1 with two concentrically arranged to each other Pipes 2, 3 on the downstream of a conical cover, first closure element 4 to be closed to an outside space 5. The inner tube 2 encloses a first feed channel 6, while between the outer tube 3 and the inner tube 2 a second feed channel 7 is formed is. A turbulence and / or closes downstream of the first feed channel 6 Swirl chamber 8, which is directed outwards from the inner tube 2, downstream from the cover 4 and upstream of a second one designed as an insert of the inner tube 2 Closure element 9 is limited. The turbulence and / or swirl chamber 8 stands with the first feed channel 6 via turbulence generator channels arranged in the insert 9 10, with the second feed channel 7 over several, the inner tube 2 penetrating swirl channels 11 and with the outer space 5 via one in the Longitudinal axis 12 of the nozzle body 1 arranged outlet opening 13 in connection.

With this solution, the two-stage pressure atomizing nozzle or with it equipped burners by simply regulating the fuel supply, i.e. by Switch from turbulence mode to swirl mode or to mixed mode can be adapted to the full load or partial load requirements of a gas turbine. The supply of liquid fuel as a liquid to be atomized 14 to Nozzle body 1 takes place in a manner known per se, via lines, not shown, as shown and described for example in EP 0 794 383 A2 is. At any point in time, i.e. when using the turbulence and / or the swirl stage of the pressure atomizing nozzle, the liquid fuel 14 injected or introduced into the outer space 5 through the only outlet opening 13.

In contrast, Figures 2 to 6 show a first embodiment of a pressure atomizing nozzle according to the invention. It is in the turbulence and / or Swirl chamber 8 is a separate one that divides them into four subchambers 15 of the same size Deflector 16 arranged centrally (Fig. 2). The deflection body 16 is in the Cross-section formed in a star shape (Fig. 3). It is considered a separate component of the Turbulence and / or swirl chamber 8 is made and is due to the two closure elements 4, 9. Is between the deflection body 16 and the inner tube 2 a number of free spaces 17 corresponding to the number of subchambers 15 educated.

The subchambers 15 are upstream through the insert 9, downstream through the cover 4, radially outwards from the inner tube 2 and in its inner area limits the deflection body 16. The free spaces 17 connect the subchambers 15 in their outer area with each other. Each sub-chamber 15 is via a turbulence generator channel 18 with a centrally formed inside the deflecting body 16 Distribution channel 19 connected, which in turn via an in use 9th arranged connecting channel 20 communicates with the first feed channel 6 (Fig. 2). In addition, each sub-chamber 15 is connected to the second via a swirl channel 11 Feed channel 7 connected, the swirl channels 11 each eccentrically in the open upstream of the partial chambers 15 (Fig. 3, Fig. 4). Finally, each partial chamber 15 has an outlet opening arranged in the cover 4 13 to the outside 5 of the pressure atomizing nozzle. The outlet openings 13 are evenly distributed over the circumference of the cover 4 and on a common one Circumferential circle arranged.

As shown in FIG. 2, the liquid fuel 14 arrives when the turbulence stage is operating via the first feed channel 6 and the connecting channel 20 in the Distribution channel 19. From there it is through the four turbulence generator channels 18 as a turbulent flow into the subchambers 15 where it is due from flow separations to strongly swirled flows with a uniform Liquid application of the subchambers 15 comes (Fig. 5). About the Outlet openings 13 are then injected with the liquid fuel 14 into the outside space 5, in the form of four separate fuel sprays 21. Zum Achieve good atomization quality and a high penetration depth the injection pressure should be up to 100 bar.

In contrast, as shown in FIG. 4, the swirl stage is via the second feed channel 7 applied with the liquid fuel 14. The latter first gets into the Swirl channels 11 and is divided from there to the subchambers 15. Here the liquid fuel 14 is introduced into the upstream region of the partial chambers 15, so that due to the aerodynamic design the sub-chambers 15 and because of their eccentric flow a directed Imprints swirl flow, which also via the four outlet openings 13 in the outer space 5 of the pressure atomizing nozzle is introduced (FIG. 6). For a good The injection pressure should also reach atomization quality up to 100 bar. The maximum mass flow achievable with the swirl stage is the same Injection pressure below that of the turbulence stage, but should not be less than 50% of the fuel flow at full load.

Switching between the turbulence stage and the swirl stage is smooth, by appropriately loading the first or connected to the second feed channel 6, 7 fuel lines. To this In this way, instabilities in the combustion are avoided. Regarding the switching regime is in turn to EP 0 794 383 A2, in particular to their Figures 8 and 9 and to the associated description.

In a second embodiment of the invention (Fig. 7, Fig. 8) is the deflecting body 16 in cross section double ax-shaped, with two first webs 22 and formed with two second webs 23 arranged at right angles thereto. Here the first two webs 22 each run out sickle-shaped, while the two second webs 23 each have at least approximately parallel sides 24. In addition are each two of the swirl channels 11 at least approximately parallel to each other and in each case one of the two second webs 23 on both sides into the partial chambers 15 arranged at the mouth. During its assembly, the deflection body 16 is in the Turbulence and / or swirl chamber 8 pressed, for which purpose between the first two Web 22 and the inner tube 2, a press fit 25 is formed. Of course, another suitable fastening of the deflecting body 16, for example by welding with the second closure element 9. The turbulence and / or swirl chamber 8 is divided into four by the webs 22, 23 separate sub-chambers 15 divided (Fig. 8). As a result of the changed geometry the deflection body 16 and thus the subchambers 15, the deflection of the entering liquid fuel 14 further improved, so that better centering the swirl flow takes place. This leads to a more even swirl spray and thus to smaller drops. The latter evaporate faster at part load, whereby an improved premix can be achieved.

Of course, the supply of the liquid fuel 14 into the subchambers 15 both in the first and in the second embodiment directly through Turbulence generator channels 10 in the insert 9 of the inner tube 2 take place as they do are shown for example in Figure 1.

In a further exemplary embodiment of the invention, the nozzle body 1 is also included connected to a premix burner 26 that the outer space 5 of the nozzle body 1 is at the same time an interior 5 'of the premix burner 26 (FIG. 9). Here the longitudinal axis 12 of the nozzle body 1 and the burner axis 27 coincide. The premix burner 26 is a conical structure and essentially consists from four superposed conical bodies 28, 29, 30 31 with a constant cone half angle β to the burner axis in the direction of flow 27. In the narrowest cross section of the through the partial cone body 28, 29, 30, 31 formed, hollow cone-shaped interior 5 'of the premix burner 26 is the Nozzle body 1 arranged. Analogously to FIGS. 1 to 8, the nozzle body 1 a turbulence and / or swirl chamber 8, which by a deflecting body 16 is divided into four subchambers 15, each with an outlet opening 13.

The partial cone bodies 28, 29, 30, 31 each have a longitudinal axis of symmetry 28 ', 29', 30 ', 31'. The latter run radially offset from one another, so that four flow opposite, tangential air inlet slots 32 for a combustion air flow 33 are formed (Fig. 10). In addition, the partial cone bodies have 28, 29, 30, 31 along the air inlet slots 32 each have a fuel feed line 34 on. These fuel supply lines 34 are provided with openings 35 on the longitudinal side, through which a gaseous fuel 36 into the interior 5 'of the premix burner 26 can flow (Fig. 9). This fuel 36 is used when needed that introduced through the tangential air inlet slots 32 into the interior 5 ' Combustion air stream 33 mixed. A mixed operation of the premix burner 26 via the pressure atomizing nozzle and the fuel supply lines 34 is possible.

When the premix burner 26 is operated via the pressure atomizing nozzle, is dependent both of the material thickness of its partial cone body 28, 29, 30, 31 as also from the flow rate of the combustion air streams 33 downstream each partial cone body 28, 29, 30, 31 inevitably has a trailing area 37, 38, 39, 40 trained in which there are significantly lower aerodynamic forces than in the adjacent areas of the interior 5 '. Each of the four outlet openings 13 of the subchambers 15 is on the trailing area 37, 38, 39, 40 of the adjacent one Part cone body 28, 29, 30, 31 aligned. This will make the liquid fuel 14 in the form of the four separate fuel sprays 21 via the outlet openings 13 in the interior 5 'of the premix burner 26, more precisely in the Trailing areas 37, 38, 39, 40 of the partial cone bodies 28, 29, 30, 31 of the premix burner 26, injected. As a result of this alignment of the fuel sprays 21 are the fuel droplets are exposed to lower aerodynamic forces and are accordingly better mixed radially into the combustion air streams 33. The improved premix leads to an evenly prepared one Burning mixture at the end of the burner and thus to improved combustion 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 26 operated almost entirely via its turbulence stage. As a result, fuel sprays 21 with small internal burner walls 41 aligned angles and generated with large droplet pulses. These droplets of fuel penetrate into the surrounding, formed by the combustion air flow 33 Air field and reach the outer areas of the Interior 5 'of the premix burner 26. In this way, finally on Burner outlet a uniform fuel-vapor profile can be formed.

In general, the combustion air flow 33 and thus also at partial load its momentum is reduced, reducing the need for a lower mass flow of liquid fuel 14, a lower spray pulse and therefore a smaller one Fuel droplets. Therefore, the gas turbine is in this operating state the respective swirl stage of the pressure atomizing nozzles is acted upon more than the turbulence level. An increasing swirl ratio gradually and automatically reduces the mass flow of the liquid fuel 14. Because the swirl stage realizes a lower mass flow than the turbulence stage, the fuel pressure drops of the liquid fuel 14 accordingly. About an increase in droplet size and thus the impact of the fuel droplets on the inner walls of the burner To prevent a constant fuel pressure is required. On the other hand when the gas turbine load decreases, i.e. with further decreasing influence the combustion air flow 33, by the transition to an almost complete Swirl operation, a further reduction in the droplet size of the liquid fuel 14 reached.

Of course, the premix burner 26, according to EP 0 704 657 A2, can also consist of a swirl generator and a downstream mixing tube, wherein the swirl generator is essentially the premix burner described above 26 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).

Reference list

1

Nozzle body

2nd

Tube, inner

3rd

Tube, outer

4th

first closure element, cover

5

Outside space

6

Feed channel, first

7

Feed channel second

8th

Turbulence and / or swirl chamber

9

second closure element, insert

10th

Turbulence channel

11

Swirl channel

12th

Longitudinal axis, from 1

13

Outlet opening

14

Liquid, liquid fuel

15

Sub-chamber

16

Deflector

17th

free space

18th

Turbulence Channel, in 16

19th

Distribution channel, in 16

20th

Connecting channel, in 9

21

Fuel spray

22

Footbridge, first

23

Footbridge, second

24th

Page of 23

25th

Press fit

26

Premix burner

27

Burner axis

28

Partial cone body

29

Partial cone body

30th

Partial cone body

31

Partial cone body

32

Air inlet slot

33

Combustion air flow

34

Fuel supply

35

opening

36

Fuel, gaseous

37

Trail area

38

Trail area

39

Trail area

40

Trail area

41

Inner wall of the burner

5 '

Interior, from 26

28 '

Longitudinal symmetry axis

29 '

Longitudinal symmetry axis

30 '

Longitudinal symmetry axis

31 '

Longitudinal symmetry axis

β

Cone half angle

Claims (14)

Two-stage pressure atomizer nozzle for at least one liquid to be atomized, with a nozzle body consisting of an outer tube and an inner tube, a first feed channel being formed in the inner tube and a second feed channel being formed between the outer and the inner tube, both feed channels into a turbulence and / or swirl chamber open, the latter is delimited from an outside space by means of a first closure element and from the first feed channel by means of a second closure element and is connected to the first feed channel via at least one connecting channel arranged in the second closure element and to the outside space via an outlet opening arranged in the first closure element, characterized in that a) in the turbulence and / or swirl chamber (8) a separate deflection body (16) dividing the latter into at least two partial chambers (15) is arranged centrally, b) each partial chamber (15) via at least one turbulence generator channel (10, 18) with the first feed channel (6), via at least one swirl channel (11) with the second feed channel (7) and via an outlet opening (13) with the outside space (5 ) connected is. Two-stage pressure atomizing nozzle according to claim 1, characterized in that that the deflecting body (16) at least on the second closure element (9) the turbulence and / or swirl chamber (8) is attached. Two-stage pressure atomizing nozzle according to claim 1, characterized in that that the deflecting body (16) at least on the second closure element (9) of the turbulence and / or swirl chamber (8) and a press fit (25) to the inner tube (2). Two-stage pressure atomizing nozzle according to claim 1, characterized in that that the deflecting body (16) at least on the second closure element (9) of the turbulence and / or swirl chamber (8) rests between the deflecting body (16) and the inner tube (2) one of the number of subchambers (15) corresponding and connecting the latter in their outer area Number of free spaces (17) is formed. Two-stage pressure atomizing nozzle according to one of claims 1 to 4, characterized characterized in that the turbulence and / or swirl chamber (8) four Partial chambers (15), four in the inner tube (2) with the second feed channel (7) connected swirl channels (11) and each eccentric are arranged opening into one of the subchambers (15). Two-stage pressure atomizing nozzle according to claim 5, characterized in that that the deflecting body (16) with an at least approximately central, connecting to the connecting channel (20) of the second closure element (9) Distribution channel (19) and this distribution channel (19) one of the turbulence generator channels (18) with each of the subchambers (15) is connected. Two-stage pressure atomizing nozzle according to claim 5, characterized in that that in use (9) of the inner tube (2) four turbulence channels (10) are arranged and each turbulence generator channel (10) with a the subchambers (15) is connected. Two-stage pressure atomizing nozzle according to claim 6 or 7, characterized in that that both the turbulence generator channels (10, 18) and the swirl channels (11) in the upstream region of the partial chambers (15) flow into. Two-stage pressure atomizing nozzle according to claim 8, characterized in that that the subchambers (15) are of equal size. Two-stage pressure atomizing nozzle according to claim 9, characterized in that that the deflecting body (16) is star-shaped in cross section. Two-stage pressure atomizing nozzle according to claim 9, characterized in that that the deflecting body (16) has a double ax shape in cross section, with two first webs (22) and with two second ones arranged at right angles thereto Webs (23) is formed, the two first webs (22) each sickle-shaped run out and the two second webs (23) at least each have approximately parallel sides (24). Two-stage pressure atomizing nozzle according to claim 10 or 11, characterized in that that two of the swirl channels (11) at least approximately parallel to each other, one of the two second webs (23) on both sides into the Partial chambers (15) are arranged opening. Two-stage pressure atomizing nozzle according to one of claims 1 to 13, characterized characterized in that the nozzle body (1) with a premix burner (26) connected and the outside space (5) at the same time an inside space (5 ') of the premix burner (26). Two-stage pressure atomizing nozzle according to claim 14, characterized in that a) four partial chambers (15) are formed in the turbulence and / or swirl chamber (8), b) the premix burner (26) consists essentially of four hollow partial cone bodies (28, 29, 30, 31) positioned one on top of the other in the flow direction with a cone half angle β constant in the flow direction, the longitudinal symmetry axes (28 ', 29', 30 ', 31' ) run radially offset from one another so that four tangential air inlet slots (32) which are opposite in terms of flow are formed for a combustion air flow (33), c) the nozzle body (1) is arranged in the hollow-conical interior (5 ') of the premix burner (26) formed by the partial cone bodies (28, 29, 30, 31), d) a trailing region (37, 38, 39, 40) is formed downstream of each partial cone body (28, 29, 30, 31) and the outlet openings (13) of the partial chambers (15) each onto the trailing region (37, 38, 39, 40 ) of the adjacent partial cone body (28, 29, 30, 31) are aligned.

Images