EP0718561B1 - Combustor - Google Patents

Description

Technical field

The present invention relates to a combustion chamber according to Claim 1. It also concerns a procedure to operate such a combustion chamber.

State of the art

Combustion chambers with a wide load range turn up always the problem, like burning at a high Efficiency can be operated with low emissions. Stand there the majority of NOx emissions in the foreground, however it has been shown that the UHC- (= unsaturated Coal-water substances) and CO emissions in the future will be minimized vigorously. Especially when it comes to that liquid and / or gaseous fuels are used bring it up very quickly that the interpretation for the a type of fuel, for example for oil, and directed to Minimizing pollutant emissions, such as NOx emissions, other types of debt collection and others Pollutant emissions are not transmitted satisfactorily can. With multi-stage combustion chambers, one strives for the second Step lean to drive. However, this is only possible if on Entry of this second stage always a constant temperature has sufficient burnout in the second Level can also be reached with a small amount of fuel, i.e. the mix in the first stage would have to be largely constant are kept, for example, with the known diffusion burners not possible. As far as can be seen such a combustion chamber is not state of the art.

EP-A-0 694 740 discloses a two-stage combustion chamber in which in a first stage a fuel / air mixture is burned by means of a catalytic converter. In the hot gases formed in this way, fuel is generated downstream of vortex generators and air was injected and burned in a second combustion chamber stage.

Presentation of the invention

The invention seeks to remedy this. The invention how it is characterized in the claims, the task lies the basis for a combustion chamber and a method of the beginning mentioned type, all occurring during the combustion Minimize pollutant emissions regardless which type of fuel is used.

The main advantage of the combustion chamber according to the invention is that there are two burner characteristics to one inventive combinations are focused, with the final purpose, especially the NOx emissions towards zero to strive. The first part of the combustion chamber, based on a premix combustion, only with part of the Combustion air flows through, and supplies the hot gas for the downstream second part of the combustion chamber. The second Part of the combustion chamber, however, becomes the total mass flow flows through. The goal is the first part of the combustion chamber operate with the lowest possible temperature in "premix mode", the lowest possible basic NOx level of a few to achieve vppm. This is achieved by the temperature the combustion air before the first partial combustion chamber preheated to a temperature on the order of 500-700 ° C becomes. This combustion air can be relatively simple the compressor end temperature has been raised to the desired level be, preferably with the fact that they are previously direct used as cooling air for the combustion chamber itself or on integrated Heat exchanger elements is passed. The Hot gases are then downstream of the first partial combustion chamber by injecting the rest, in combustion air not used in the first partial combustion chamber brought to that temperature which in the second Combustion chamber part comes to self-ignition, this one second combustion chamber part is equipped with vortex generators.

Another advantage of the invention is that the second combustion chamber part as a single-stage load combustion chamber driven, in contrast to the first combustion chamber part, the is operated as an idle combustion chamber. The second part of the combustion chamber works up to gas temperatures of approx. 1600 ° C due to the extremely good mixture is NOX neutral and delivers Total NOx potential with a very flat temperature / NOx characteristic from 1-2 vppm.

Another advantage of the invention is that by adjusting the temperature at the entrance to the second Combustion chamber part the ignition delay times for different fuels can be optimally adjusted.

Advantageous and expedient developments of the inventive Task solution are in the further dependent claims characterized.

In the following, exemplary embodiments will be described with reference to the drawings the invention explained in more detail. All for immediate understanding are not necessary elements of the invention omitted. The same elements are in the different figures provided with the same reference numerals. The flow direction the media is indicated by arrows.

Brief description of the drawings

Fig. 1

eine Brennkammer, als Ringbrennkammer konzipiert, mit zwei Brennkammerteilen,

Fig. 2

einen Brenner in perspektivischer Darstellung, entsprechend aufgeschnitten,

Fig. 3-5

entsprechende Schnitte durch verschiedene Ebenen des Brenners,

Fig. 6

eine perspektivische Darstellung des Wirbel-Generators,

Fig. 7

eine Ausführungsvariante des Wirbel-Genenerators,

Fig. 8

eine Anordnungsvariante des Wirbel-Generators nach Fig. 7,

Fig. 9

einen Wirbel-Generators im Vormischkanal,

Fig. 10-16

Varianten der Brennstoffzuführung im Zusammenhang mit Wirbel-Generatoren.

It shows:

Fig. 1

a combustion chamber, designed as an annular combustion chamber, with two combustion chamber parts,

Fig. 2

a burner in perspective, cut open accordingly,

Fig. 3-5

appropriate cuts through different levels of the burner,

Fig. 6

a perspective view of the vortex generator,

Fig. 7

a variant of the vortex generator,

Fig. 8

7 shows a variant of the arrangement of the vortex generator according to FIG. 7,

Fig. 9

a vortex generator in the premixing channel,

Fig. 10-16

Variants of fuel supply in connection with vortex generators.

Ways of carrying out the invention, commercial usability

1 shows, as can be seen from the shaft axis 16, a Annular combustion chamber, which is essentially the shape of a coherent has annular or quasi-annular cylinder. In addition, such a combustion chamber can also be used a number of axially, quasi-axially or helically arranged and individually in self-contained combustion chambers consist. As such, the combustion chamber can also consist of a single one Pipe exist. The annular combustion chamber according to FIG. 1 exists from a first 1 and a second stage 2, which one after the other are switched, and wherein the second stage 2 also actual combustion zone 11 includes. The first stage 1 initially consists of a number of in the flow direction circumferentially arranged burners 100, this Brenner is further described below. What the following Description of the combustion chamber according to FIG. 1 concerns alone on the cutting plane shown. Of course all components of the combustion chamber are in the same Number arranged in the circumferential direction. Upstream of the mentioned burner 100 acts a compressor, not shown 18, in which the intake air is compressed. The then Air supplied by the compressor has a pressure of 10-40 cash on. A proportion of 30-60% of the compressed air flows into the burner 100, the mode of operation of which is shown in FIGS. 2-5 is described in more detail. Prior to the inflow into the Burner 100, this portion of air 115 to a temperature warmed up from 500-700 ° C. This is done by air previously used directly as cooling air for the combustion chamber becomes. Another way is to air 115th to flow through heat exchangers, not shown. Through this preheating and reduced proportion in the first Combustion chamber part, the NOx emissions are very low, in the order of 1-3 vppm. At the end of this first Combustion chamber part 1 is therefore largely NOx-free Hot gas 4 available. After leaving the first Combustion chamber part 1, the hot gases 4 flow into an inflow zone 5 and there they are accelerated to approx. 80-120 m / s. The Inflow zone 5 is on the inside and in the circumferential direction of the channel wall 6 with a series of vortex generating elements 200, hereinafter referred to as vortex generators only, which will be discussed in more detail below. The hot gases 4 are in this area by wall cooling effects and by injecting the remaining air 17, preferably by effusion cooling, this injection preferably is also carried out via the vortex generators 200, brought to a temperature of 800-1100 ° C. The total air is then swirled by the vortex generators 200 in such a way that in the subsequent premixing section 7 there are no recirculation areas more in the wake of the vortex generators mentioned 200 occur. Within this premix section 7, the can be designed as a venturi channel, several fuel lances 8 scheduled, which is the supply of a fuel 9 and a supporting air 10 take over. The feeder this media to the individual fuel lances 8 can, for example made via a ring line, not shown be, the fuel supply also via the vortex generators 200 integrated fuel lances 3 made can be. The one triggered by the vortex generators 200 Swirl flow ensures a large distribution of the introduced fuel 9, possibly also the admixed Support air 10 to a fuel / air mixture 19. Des the swirl flow also ensures homogenization of the Mixture of combustion air and fuel. The one through the Fuel lance 8 fuel 9 injected into the hot gases 4 triggers a self-ignition, as far as these hot gases 4 those have specific temperature, which is the fuel-dependent Auto ignition can trigger. Will the ring combustion chamber operated with a gaseous fuel must for the Initiation of self-ignition a temperature of the hot gases 4 greater than 800 ° C, which is also present here. At such a combustion, as already recognized above, in itself the danger of a flashback. This Problem is solved by using premixing zone 7 as the one hand Venturi channel (not shown in detail) is formed, on the other hand by the injection of the fuel 9 in the area of largest constriction in the premixing zone 7. The constriction in the premixing zone 7 increases the turbulence diminished by increasing the axial speed, what the risk of kickback by reducing the turbulent Flame speed is minimized. On the other hand, the large-scale distribution of the fuel 9 continues to be guaranteed, because the peripheral component of that of the vortex generators 200 originating swirl flow is not affected. Closes behind the relatively short premixing zone 7 the combustion zone 11. The transition between the a radial cross-sectional jump 12 formed, which is initially the flow cross section of the combustion zone 11 indexed. In the area of the cross-sectional jump 12 is also a flame front 21. To reignite to avoid the flame inside the premix zone 7 the flame front 21 must be kept stable. To this For this purpose, the vortex generators 200 are designed such that in the premix zone 7 is not yet being recirculated; first after the sudden widening of the cross-section the bursting takes place the swirl flow takes place. The swirl flow supports the quick reinstallation of the current behind the Cross-sectional jump 12, so that the most complete Utilization of the volume of the combustion zone 11 a high Burnout can be achieved with a short overall length. Within this cross-sectional jump 12 forms during the Operation a flow boundary zone, in which by the negative pressure of the vortex prevailing there, which then stabilize the flame front 21 to lead. These corner vortices 20 also form the ignition zones within the second stage 2. The provided in the combustion zone 11 hot working gases 13 are then applied a downstream turbine 14. The exhaust gases This turbine can then be used to operate a steam cycle are used, in the latter case the circuit is then a combination system.

In summary, it can be said that due to the high Flow rate an onset of afterburning in the Flow channel is excluded. When burning oil can prevent immediate ignition by adding water become. As before, serves to stabilize the afterburning explains the cross-sectional jump 12. In the corner vertebrae 20 auto-ignition occurs due to the long stay of the mixture. The flame front 21 moves to the middle the combustion zone 11 away. Shortly downstream of the union point the CO burnout is also on both sides of the flame completed. Typical combustion temperatures are 1300-1600 ° C. The process of injecting fuel into a hot gas is predestined to produce little NOx in our case 1-2 vppm.

The proposed method also behaves very well regarding a wide load range. Because the mix kept largely constant in the first stage 1 UHC or CO emissions can also be prevented become. The constant temperature at the entrance to the second Level 2 ensures a safe auto-ignition of the mixture, regardless of the amount of fuel in the second stage 2. The inlet temperature is still high enough to get you sufficient burnout in the second stage 2 even at low To reach the amount of fuel. The power regulation over the gas turbine load is essentially due to the adaptation the amount of fuel in the second stage 2.

The first stage 1 is operated as an idle combustion chamber second stage 2 operated as a single-stage load combustion chamber.

To better understand the structure of burner 100, it is of advantage if the individual at the same time as FIG. 2 Cuts according to Figures 3-5 can be used. Furthermore, in order not to make Fig. 2 unnecessarily confusing, are those shown schematically in FIGS. 3-5 Baffles 121a, 121b have only been hinted at. The following is the description of FIG. 2 as needed referred to the remaining figures 3-5.

The burner 100 of FIG. 2 consists of two hollow conical ones Partial bodies 101, 102 that are nested offset from one another are. The offset of the respective central axis or longitudinal symmetry axis 201b, 202b of the tapered partial body 101, 102 creates each other on both sides, in mirror image arrangement, each with a tangential air inlet slot 119, 120 free (Fig. 3-5), through which the Combustion air 115 in the interior of burner 100, i.e. in the cone cavity 114 flows. The cone shape of the one shown Partial body 101, 102 has a certain direction of flow fixed angle. Of course, depending on the operational use, can the partial body 101, 102 in the direction of flow have an increasing or decreasing taper, similar a trumpet resp. Tulip. The latter two Shapes are not recorded in the drawing, since they are for the specialist are easily felt. The two tapered Partial bodies 101, 102 each have a cylindrical initial part 101a, 102a, which also, analogous to the tapered partial bodies 101, 102, offset from one another, so that the tangential Air inlet slots 119, 120 over the entire length of burner 100 are present. In the area of the cylindrical Initially, a nozzle 103 is housed, its injection 104 roughly with the narrowest cross section of the through the tapered Part body 101, 102 formed conical cavity 114 coincides. The injection capacity and the type of this nozzle 103 depends on the given parameters of the respective Brenner 100. Of course, the burner 100 can be pure conical, that is, without cylindrical starting parts 101a, 102a his. The tapered body 101, 102 have the further each have a fuel line 108, 109 which runs along the tangential entry slots 119, 120 and are provided with injection openings 117 through which preferably a gaseous fuel 113 in there combustion air 115 flowing through is injected, like this want to symbolize the arrows 116. These fuel lines 108, 109 are preferably at the latest at the end of the tangential Inflow, before entering the cone cavity 114, placed in order to achieve an optimal air / fuel mixture receive. The exit opening goes in the area of the inflow zone 5 of the burner 100 into a front wall 110, in which there are a number of bores 110a. The latter come into operation when necessary, and ensure that dilution air or cooling air 110b the front part of the inflow zone 5 is supplied. The one brought up through the nozzle 103 It is preferably a fuel liquid fuel 112, which at most with a recirculated Exhaust gas can be enriched. This fuel 112 is injected into the cone cavity 114 at an acute angle. A nozzle is thus formed from the nozzle 103 Fuel profile 105 that flows in from the tangential rotating combustion air 115 is enclosed. In axial Direction, the concentration of the fuel 112 becomes continuous through the incoming combustion air 115 to a optimal mixture degraded. If the burner 100 with a operated gaseous fuel 113, this can also over the fuel nozzle 103 happen, but preferably happens this via opening nozzles 117, the formation of this fuel / air mixture right at the end of the air inlet slots 119, 120 comes about. At fuel injection 112 via the fuel nozzle 103 becomes 100 at the end of the burner the optimal, homogeneous fuel concentration across the cross-section reached. The combustion air 115 is additional preheated or enriched with a recirculated exhaust gas, this supports the evaporation of the liquid fuel 112 sustainable. The same considerations also apply if via the lines 108, 109 instead of gaseous liquid Fuels are supplied. When designing the tapered Partial body 101, 102 with respect to the cone angle and Width of the tangential air inlet slots 119, 120 are to adhere to narrow limits, so that the desired Flow field of combustion air 115 at the burner outlet 100 can set. The critical swirl number arises at the exit of burner 100: A also forms there Backflow zone (vortex breakdown) with a flame stabilizing Effect. Generally speaking, that is a minimization the cross section of the tangential air inlet slots 119, 120 is predestined, a backflow zone 106 to build. The construction of the burner 100 is suitable another excellent, the size of the tangential air inlet slots 119, 120 change, with what no change the overall length of the burner 100 is a relatively large operational one Bandwidth can be captured. Of course the partial bodies 101, 102 also in a different plane to one another slidable, thereby even overlapping them can be controlled. It is even possible to use the partial body 101, 102 by counter-rotating motion to nest into each other.

3-5 now shows the geometric configuration of the Baffles 121a, 121b. They have a flow initiation function these, according to 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 by opening or closing the guide plates 121a, 121b by one in the area of the entry of this channel into the Cone cavity 114 placed pivot point 123 can be optimized, this is particularly necessary if the original gap size the tangential air inlet slots 119, 120 motives mentioned above is to be changed. Of course these dynamic arrangements can also be provided statically become an integral part by making required baffles form with the tapered partial bodies 101, 102. Likewise the burner 100 can also be operated without baffles, or other aids can be provided for this.

The actual inflow zone 5 is not shown in FIGS. 6, 7 and 8. In contrast, the flow of hot gases 4 is shown by an arrow, which also specifies the direction of flow. According to these figures, a vortex generator 200, 201, 202 essentially consists of three freely flowing triangular surfaces. These are a roof surface 210 and two side surfaces 211 and 213. In their longitudinal extension, these surfaces run at certain angles in the direction of flow. The side walls of the vortex generators 200, 201, 202, which preferably consist of right-angled triangles, are fixed with their long sides on the channel wall 6 already mentioned, preferably gas-tight. They are oriented so that they form a joint on their narrow sides, including an arrow angle α. The joint is designed as a sharp connecting edge 216 and is perpendicular to each channel wall 6 with which the side surfaces are flush. The two side surfaces 211, 213 including the arrow angle a are symmetrical in shape, size and orientation in FIG. 4, they are arranged on both sides of an axis of symmetry 217 which is aligned in the same direction as the channel axis.
The roof surface 210 lies against the same channel wall 6 as the side surfaces 211, 213 with a very narrow edge 215 running transverse to the flow channel. Its longitudinal edges 212, 214 are flush with the longitudinal edges of the side surfaces 211 protruding into the flow channel , 213. The roof surface 210 extends at an angle of attack e to the channel wall 6, the longitudinal edges 212, 214 of which, together with the connecting edge 216, form a point 218. Of course, the vortex generator 200, 201, 202 can also be provided with a bottom surface with which it is attached to the channel wall 6 in a suitable manner. Such a floor area is, however, unrelated to the mode of operation of the element.

The mode of operation of the vortex generator 200, 201, 202 is the following: When flowing around edges 212 and 214, the Main flow converted into a pair of counter-rotating vortices, as schematically sketched in the figures. The Vortex axes lie in the axis of the main flow. The Swirl number and the location of the vortex breakdown (vortex breakdown), if the latter is sought, be replaced by appropriate Choice of the angle of attack Θ and the arrow angle α certainly. With increasing angles, the vortex strength or the number of twists increases, and the location of the vortex burst shifts upstream into the area of the vortex generator 200, 201, 202 themselves. Depending on the application, these are both angles Θ and α due to structural conditions and determined by the process itself. Need to be adjusted these vortex generators only in terms of length and height, as this will be explained in more detail below under FIG. 9 will arrive.

6 forms the connecting edge 216 of the two side surfaces 211, 213 the downstream edge of the vortex generator 200. The one running across the canal Edge 215 of roof surface 210 is thus that of the channel flow edge applied first.

In Fig. 7 is a so-called half "vortex generator" the base of a vortex generator shown in FIG. 6. At the Vortex generator 201 shown here is only one of the two Provide side surfaces with the arrow angle α / 2. The other Side surface is straight and aligned in the direction of flow. In contrast to the symmetrical vortex generator only a vortex on the swept side is created here, like this is symbolized in the figure. Accordingly, it is downstream this vortex generator does not have a vortex-neutral field, but instead a swirl is imposed on the current.

Fig. 8 differs from Fig. 6 in so far as here the sharp connecting edge 216 of the vortex generator 202 is the point which is affected first by the channel flow becomes. The element is therefore rotated by 180 °. How it can be seen from the illustration that the two have opposite directions Vortex changed their sense of rotation.

Fig. 9 shows the basic geometry of one in a channel 5 built-in vortex generator 200. Usually the height h of the connecting edge 216 with the channel height H, or the height of the channel part, which the vortex generator is assigned so that the generated vortex is immediate one such downstream of the vortex generator 200 Size reached such that the full channel height H is filled out. This leads to an even speed distribution in the loaded cross section. On Another criterion, the influence on the ratio to be chosen of the two heights h / H is the pressure drop, that occurs when the vortex generator 200 flows around. It it goes without saying that with a larger ratio h / H the Pressure loss coefficient increases.

The vortex generators 200, 201, 202 are mainly used when it comes to two currents with each other to mix. The main flow 4 attacked as hot gases in the direction of the arrow, the transverse edge 215, respectively the Connecting edge 216. The secondary flow in the form of a gaseous and / or liquid fuel, which at most with a portion of supporting air is enriched (see FIG. 1) a significantly smaller mass flow than the main flow on. This secondary flow is in the present case introduced into the main flow downstream of the vortex generator, as can be seen particularly well from FIG. 1.

In the example shown in FIG. 1 there are four vortex generators 200 distributed at a distance over the circumference of the channel 5. Of course, the vortex generators can be in Circumferential direction are also lined up so that none Spaces on the channel wall 6 are left blank. For the Choice of the number and arrangement of the vortex generators is ultimately the vortices to be generated are decisive.

Figures 10-16 show other possible forms of introduction of fuel in hot gases 4. These options can interact with each other and with a central Fuel injection, such as that shown in FIG. 1 emerges can be combined.

In Fig. 10, the fuel is added to channel wall bores 220, which are located downstream of the vortex generators, also injected via wall holes 221, which are immediately next to the side surfaces 211, 213 and in their Longitudinal extension in the same channel wall 6 are located on the the vortex generators are arranged. The introduction of the Fuel through the wall holes 221 gives the generated Whirl an extra impulse, which is the lifespan of the vortex generator extended.

11 and 12, the fuel is fed through a slot 222 or injected via wall holes 223, both precautions immediately in front of the cross-canal extending edge 215 of the roof surface 210 and in the Longitudinal extension in the same channel wall 6 are located on the the vortex generators are arranged. The geometry of the Wall bores 223 or the slot 222 is selected such that the fuel at a certain injection angle into the Main flow 4 is entered and the re-placed vortex generator as a protective film against the hot main flow 4 largely shielded by flow.

In the examples described below, the secondary flow (See above) first of all via guides not shown through the channel wall 6 into the hollow interior of the vortex generators initiated. In this way, an internal cooling facility for the vortex generators created.

13 the fuel is injected via wall bores 224, which is located directly within the roof area 210 behind and along the one running across the channel Edge 215. The vortex generator is cooled here more external than internal. The emerging secondary flow forms a flow against the roof surface 210 against the hot main flow 4 shielding protective layer.

14 the fuel is injected via wall bores 225, which within the roof surface 210 along the line of symmetry 217 are staggered. With this variant the channel walls 6 are particularly good before the hot main flow 4 protected because the fuel is initially on the outer circumference the vertebra is introduced.

15, the fuel is injected via wall bores 226, which are located in the longitudinal edges 212, 214 of the Roof area 210 are located. This solution ensures a good one Cooling of the vortex generators because of the fuel on it Extremities emerge and thus the inner walls of the element fully washed. The secondary flow is here directly put the resulting vortex into what to define Flow conditions leads.

16, the injection takes place via wall bores 227, which are in the side surfaces 211 and 213, on the one hand in the area of the longitudinal edges 212 and 214, on the other hand in Area of the connecting edge 216. This variant has a similar effect like those of Fig. 10 (bores 221) and from 15 (bores 226).

Reference list

1

First stage

2nd

Second step

3rd

Alternative fuel lance

4th

Hot gases, main flow

5

Inflow zone, channel of the inflow zone

6

Canal wall of the inflow zone

7

Premixing zone

8th

Fuel lance

9

fuel

10th

Support air

11

Combustion zone

12th

Cross-sectional jump

13

Hot working gases

14

turbine

16

Shaft axis

17th

Residual air, from the original compressor air

18th

compressor

19th

Air / fuel mixture

20th

Corner swirls, ignition zones

21

Flame front

100

burner

101, 102

Partial body

101a, 102a

Cylindrical starting parts

101b, 102b

Longitudinal symmetry axes

103

Fuel nozzle

104

Fuel injection

105

Fuel injection profile

108, 109

Fuel lines

110

Front wall

110a

Air holes

110b

Cooling air

112

Liquid fuel

113

Gaseous fuel

114

Cone cavity

115

Combustion air

116

Fuel injection

117

Fuel nozzles

119, 120

Tangential air inlet slots

121a, 121b

Baffles

123

Pivot point of the guide plates

200, 201, 202

Vortex generators

210

Roof area

211, 213

Side faces

212, 214

Longitudinal edges

215

Transverse edge

216

Connecting edge

217

Axis of symmetry

218

top

220-227

Drilling holes for fuel injection

L, h,

Dimensions of the vortex generator

H

Height of the channel

α

Arrow angle

Θ

Angle of attack

Claims (16)

1. Combustion chamber, which essentially comprises a first stage (1) and a second stage (2) arranged downstream in the direction of flow, in which combustion chamber the first stage (1) has on the head side at least one burner (100) in which a first quantity of fuel (112, 113) is mixed with a first partial flow of combustion air (115) and is burned in the first stage (1) in order to form a hot gas (4), and in which combustion chamber a second partial flow of combustion air (17) is injected downstream of the burner (100), vortex generators (200, 201, 202) are arranged in the outflow side of the first stage (1), and a gaseous and/or liquid fuel (9) is injected into the main flow on the outflow side of the vortex generators (200, 201, 202), and in which combustion chamber the second stage (2) downstream of the vortex generators has a jump (12) in cross section which produces backflow bubbles (20) for stabilizing a flame front (21).
2. Combustion chamber according to Claim 1, a vortex generator (200) having three surfaces around which flow occurs freely and which extend in the direction of flow and of which one forms the top surface (210) and the other two form the side surfaces (211, 213), the side surfaces (211, 213) being flush with an identical wall segment of the duct (5) and enclosing the arrow angle (α) with one another, the top surface (210) bearing, with an edge (215) running transversely to the duct (5) through which flow occurs, against the same wall segment of the duct (6) [sic] as the side surfaces (211, 213), and longitudinally directed edges (212, 214) of the top surface (210) being flush with the longitudinally directed edges of the side surfaces (211, 213) projecting into the duct (5) and running at a setting angle () to the wall segment of the duct (5).
3. Combustion chamber according to Claim 2, the two side surfaces (211, 213), enclosing the arrow angle (α), of the vortex generator (200) being arranged symmetrically around a symmetry axis (217).
4. Combustion chamber according to Claim 2, the two side surfaces (211, 213) enclosing the arrow angle (α, α/2) enclosing a connecting edge (116) [sic] with one another which together with the longitudinally directed edges (212, 214) of the top surface (210) form [sic] a point (218), and the connecting edge (216) lying in the radial line of the circular duct (5).
5. Combustion chamber according to Claim 4, characterized in that the connecting edge (216) and/or the longitudinally directed edges (212, 214) of the top surface (210) are designed to be at least more or less sharp.
6. Combustion chamber according to one of Claims 1-4, the symmetry axis (217) of the vortex generator (200) running parallel to the duct axis, that [sic] the connecting edge (216) of the two side surfaces (211, 213) forms the downstream edge of the vortex generator (200), and the edge (215) of the top surface (210) running transversely to the duct (5) through which flow occurs being the edge acted upon first by the main flow (4).
7. Combustion chamber according to Claim 1, the ratio of height (h) of the vortex generator to height (H) of the duct (5) being selected in such a way that the vortex produced fills the full height (H) of the duct (5) and the full height (h) of the duct part allocated to the vortex generator (200) directly downstream of the vortex generator (200).
8. Combustion chamber according to Claim 1, the burner (100) comprising at least two hollow, conical sectional bodies (101, 102) which are nested one inside the other in the direction of flow and whose respective longitudinal symmetry axes (101b, 102b) run offset from one another, the adjacent walls of the sectional bodies (101, 102) forming ducts (119, 120), tangential in their longitudinal extent, for a combustion-air flow (115), and at least one fuel nozzle (103) being arranged in the conical hollow space (114) formed by the sectional bodies (101, 102).
9. Combustion chamber according to Claim 8, further fuel nozzles (117) being arranged in the region of the tangential ducts (119, 120) in their longitudinal extent.
10. Combustion chamber according to Claim 8, the sectional bodies (101, 102) widening at a fixed angle in the direction of flow or have increasing or decreasing conicity.
11. Combustion chamber according to Claim 8, the sectional bodies (101, 102) being nested spiral-like one inside the other.
12. Combustion chamber according to Claim 1, which combustion chamber is an annular combustion chamber.
13. Combustion chamber according to Claim 1, a section on the outflow side of the vortex generators (200, 201, 202) being designed in a venturi shape, and the fuel (9) being is [sic] injected in the region of the greatest reduction in area of the venturi-shaped section.
14. Method of operating a combustion chamber according to Claim 1, a portion of the combustion air (115), which has previously undergone preheating, flowing into the first stage (1), and the remaining portion of the combustion air (17) being fed in downstream of the first stage (1) and upstream of the fuel injection (9).
15. Method according to Claim 14, a first portion of combustion air (115) of 30-60% of the entire quantity of combustion air being fed into the first stage (1), this first portion being (115) being previously preheated to 500-700°C, and, by the admixing of the remaining portion of combustion air (17), an air mixture at a temperature of 800-1050°C being prepared for the combustion.
16. Use of the combustion chamber according to Claim 1 in a gas turbine assembly, a compressor being arranged upstream of the first stage (1) of the combustion chamber, in the direction of flow of the operating medium of the gas turbine assembly, and a turbine (14) being arranged downstream of the second stage (2) of the combustion chamber.

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