JP7128672B2 - Combustion chamber of gas turbine, gas turbine, and method of operating gas turbine - Google Patents

Description

The invention relates to a combustion chamber of a gas turbine according to the first claim. Furthermore, the invention relates to a gas turbine having such a combustion chamber and a method for operating the gas turbine.

A gas turbine has a combustion chamber and a turbine downstream of the combustion chamber. In the combustion chamber of a gas turbine, fuel is combusted, producing hot exhaust gases. The hot exhaust gas expands in the turbine of the gas turbine, providing energy that can be used to provide driving force, for example, to drive a generator to generate electric current. Gas turbines configured as dual-fuel gas turbines are already known from practice, such dual-fuel gas turbines comprising a dual-fuel combustion chamber in which gas Gaseous fuel is combusted in the fuel mode of operation and liquid fuel is combusted in the liquid fuel mode of operation. In the gaseous fuel mode of operation, a mixture of gaseous fuel and combustion air may be supplied to the combustion chamber through the swirling body. In the liquid fuel mode of operation, the combustion chamber of the gas turbine may be supplied with liquid fuel through the atomizer and combustion air through the swirl.

Combustion chambers of gas turbines configured as dual-fuel combustion chambers until liquid fuels can be effectively burned, particularly in liquid fuel operating modes, i.e. with reduced undesirable exhaust gas emissions such as nitrogen oxide emissions. There is a need to further improve .

Based on this need, the object of the present invention is to provide a novel combustion chamber of a gas turbine, a gas turbine of the combustion chamber and a method for operating the gas turbine.

This task is solved by a gas turbine combustion chamber according to claim 1 . According to the invention, the atomizing device comprises a central atomizing lance with respect to the longitudinal center axis of the combustion chamber or with respect to the longitudinal center axis of the pre-combustion chamber of the combustion chamber with at least one atomizing nozzle. have. The atomizing device further comprises a plurality of atomizing nozzles distributed with respect to the central longitudinal axis of the combustion chamber or with respect to the central longitudinal axis of the precombustion chamber of the combustion chamber.

Through a central atomizing lance containing at least one atomizing nozzle, and through a plurality of distributed atomizing nozzles, in the liquid fuel mode of operation the liquid fuel can be optimally introduced into the combustion chamber, thereby increasing the efficiency of the liquid fuel. good combustion is guaranteed. Through a central atomizing lance, liquid fuel can be introduced directly into a central recirculation zone inside the combustion chamber or pre-combustion chamber of the combustion chamber, whereby stable combustion can be achieved. The introduction of the fuel through the central spray lance is then not homogeneous to the combustion air, and there is no premixing of liquid fuel and combustion air here. Through the dispersed atomizing nozzles, the liquid fuel can be evenly dispersed within the combustion air. In addition, partial premixing of liquid fuel and combustion air is obtained through distributed atomizing nozzles. Distributed atomizing nozzles make it possible to reduce exhaust gas emissions, in particular nitrogen oxide emissions, compared to central atomizing lances.

According to a further development of the invention, the distributed atomizing nozzles are arranged on a circular trajectory extending around the central longitudinal axis of the combustion chamber or the longitudinal central axis of the pre-combustion chamber of the combustion chamber. Preferably, the center point of the circular orbit in which the dispersed atomizing nozzles are arranged lies on the longitudinal center axis of the combustion chamber or on the longitudinal center axis of the pre-combustion chamber of the combustion chamber. Preferably, the radius of the circular orbit in which the distributed spray nozzles are arranged is between 0.4 and 1.1 times the inner radius of the rotating body. Through such distributed atomizing nozzles, the liquid fuel can be introduced into the combustion chamber uniformly distributed with the combustion air and optimally with regard to premixing of the liquid fuel and the combustion air, resulting in nitrogen oxidation. Exhaust gas emissions, such as material emissions, are reduced as much as possible.

According to a further development of the invention, the central spray lance has at least two, preferably two spray nozzles, which individually and together each have a maximum injection of 60°. Provide a spray cone with a maximum injection angle of angle, preferably 55°. Each of the distributed spray nozzles respectively supplies a spray cone with a maximum injection angle of 40°, preferably a maximum injection angle of 30°. Wetting of the walls of the combustion chamber and the precombustion chamber of the combustion chamber with liquid fuel can thereby be avoided. In particular, this helps to effectively burn liquid fuels while reducing exhaust gas emissions.

According to a further development of the invention, the central spray lance is at least partially surrounded on the radial outside by adjoining elements forming a radial gap, and the combustion chamber is provided with a radial gap through the radial gap. , the combustion air can be supplied while bypassing the swirling body. This also results in effective combustion of liquid fuel in the liquid fuel operating mode, especially when a central atomizing lance is used to introduce the liquid fuel into the combustion chamber or precombustion chamber of the combustion chamber. can be guaranteed while reducing

A gas turbine according to the invention is defined in claim 9 and a method for operating a gas turbine according to the invention is defined in claim 10 .

According to a first variant of the method according to the invention, in the liquid fuel operating mode, not only the central atomizing lance, but also the distributed atomizing nozzles are in the combustion chamber over the entire operating range between no load and full load. used to supply liquid fuel to This operating variant of the invention is suitable when the gas turbine to be operated is to perform a rapid load change. This is because there is no need to activate or deactivate each injection nozzle. It is therefore possible to avoid the cleaning procedure that would be required if each spray nozzle were shut down in this way. Exhaust gas emissions can be reduced compared to gas turbines whose combustion chambers only have central spray lances.

According to a second variant of the method according to the invention, in the liquid fuel operating mode, not only the central spray lance, but also the distributed spray nozzles supply liquid fuel to the combustion chamber in the operating range below a given load limit. However, in operating regions above a given load limit, the dispersed atomizing nozzles are used exclusively to supply liquid fuel to the combustion chamber. This operating variant of the invention serves to further reduce exhaust gas emissions, in particular nitrogen oxide emissions. In the higher load range, the central atomizing lance is no longer used for the introduction of the liquid fuel; rather, in the larger load range, the liquid fuel is introduced exclusively using distributed atomizing nozzles. Exhaust gas emissions, such as nitrogen oxide emissions, can thereby be further reduced in the high-load operating range.

Preferred further developments of the invention emerge from the dependent claims and the following description. Exemplary embodiments of the invention will now be described in detail with reference to the drawings, but are not limited thereto. Shown is the following figure.

1 is a highly schematic representation of part of a combustion chamber according to the invention of a gas turbine according to the invention; FIG. It is the figure which showed the part of II of FIG. 1 in detail. 2 shows a detail of FIG. 1, viewed in direction III; FIG. 1 is a graphical illustration for clarifying a first method according to the invention for operating a gas turbine according to the invention; FIG. FIG. 5 is a graphical illustration for clarifying a second method according to the invention for operating a gas turbine according to the invention;

The present invention relates to a combustion chamber of a gas turbine, a gas turbine having the combustion chamber and a method for operating the gas turbine.

FIG. 1 shows a schematic illustration of a part of a gas turbine in the region of a combustion chamber 1. FIG. A combustion chamber 1 is delimited by walls 2, in which fuel is combusted. The exhaust gases produced during the combustion of fuel in the combustion chamber 1 can be fed to a turbine (not shown) of the gas turbine, so that the exhaust gases are expanded in the turbine and energy is obtained in the process.

The combustion chamber 1 is configured as a dual-fuel combustion chamber and can be operated on the one hand in a gaseous fuel operating mode and on the other hand in a liquid fuel operating mode.

In the gaseous fuel operating mode of combustion chamber 1, in combustion chamber 1, gaseous fuel is combusted and the mixture of gaseous fuel and combustion air is fed into combustion chamber 1, in FIG. It is fed through the revolving body 3 .

The swirl 3 is preferably designed as a radial swirl and generates a defined swirl of the mixture of combustion air and gaseous fuel entering the precombustion chamber 9 of the combustion chamber 1 . A mixture of gaseous fuel and combustion air is ignited in the gaseous fuel operating mode using an electrical ignition device, not shown.

In the liquid fuel operating mode of the combustion chamber 1, in the combustion chamber 1 a liquid fuel is burned, which is supplied to the combustion chamber 1, in FIG. be done.

The atomizing device 4 has a central spray lance 17 which is for example approximately in the middle of the precombustion chamber 9 of the combustion chamber 1 or in the longitudinal direction of the precombustion chamber 9 of the combustion chamber 1 . located on the central axis 20 or on the longitudinal central axis 20 of the combustion chamber 1, the liquid fuel in the direction of the longitudinal central axis 20 forming a spray cone or injection cone 8a in the combustion chamber 1 is injected into the precombustion chamber 9 of

In addition to this central spray lance 17 relative to the longitudinal center axis 20 of the combustion chamber 1 or pre-combustion chamber 9 , the atomizing device 4 has a It has a plurality of distributed atomizing nozzles 18, which are likewise capable of injecting liquid fuel into the precombustion chamber 9 of the combustion chamber 1, each forming an injection cone 8b. .

The spray device 4 thus comprises a central spray lance 17 and a plurality of distributed spray nozzles 18 . The central spray lance 17 has at least one spray nozzle, preferably a plurality of spray nozzles 15, 16 (see FIG. 2).

FIG. 2 shows details of the central spray lance 17 of the spray device 4 . A spray lance 17 received in the mounting wall 12 of the combustion chamber 1 and an adjacent member 5 likewise received in the mounting wall 12, which is connected radially outwardly to the spray lance 17 of the atomizing device 4 and which sprays the atomization. A radial gap 6 is formed between the adjacent member 5 which at least partially surrounds the spray lance 17 of the device 4 radially outwardly, through which the combustion air likewise passes. , the combustion chamber 1 , i.e. the precombustion chamber 9 , can be supplied bypassing the swirling body 3 . For example, arrows 13 (see FIG. 1) indicate the combustion air flow through the swirl 3 and arrows 14 (see FIG. 2) indicate the radial gap 6 between the spray lance 17 and the member 5. The combustion air flow is fed through this radial gap 6 and past the swirl 25 .

The special member 5 which defines the radial gap 6 together with the spray lance 17 of the spray device 4 is preferably constructed as a separate sleeve, which is connected with the spray lance 17 . Alternatively, it is also possible for the mounting wall 12 itself to define a member 5 radially outwardly adjoining the spray lance 17 , which together with the spray lance 17 defines a radial gap 6 .

The atomizing nozzles 18 of the atomizing device 4, distributed with respect to the longitudinal central axis 20 of the combustion chamber 1 or the precombustion chamber 9, are preferably arranged on a circular orbit 19 (see FIG. 3), the circular orbit 19 being , extends around the longitudinal center axis 20 of the combustion chamber 1 or around the longitudinal center axis 20 of the precombustion chamber 9 of the combustion chamber 1 .

The center point of this circular path 19 , on which the distributed spray nozzles 18 are arranged, lies on the central longitudinal axis 20 . The distributed spray nozzles 18 surround the central spray lance 17, preferably concentrically.

FIG. 3 shows the radius d ₁₈ of the circular orbit 19 on which the distributed spray nozzles 18 are arranged. In particular, it is specified here that the radius d ₁₈ of the circular orbit 19 in which the dispersed spray nozzles 18 are located is between 0.4 and 1.1 times the inner radius d ₃ of the swirling body 3 . there is Therefore, if the radius d18 of the circular orbit 19 on which the dispersed spray nozzles ₁₈ are located is between 1.0 and 1.1 times the inner radius d3 of the rotating body ₃ , the dispersed spray nozzles 18 at least partially covers the swirling body 3 in its outflow area.

Distributed spray nozzles 18 may be arranged on a plurality of preferably concentric circular orbits, or on elliptical orbits, or on polygons.

As mentioned above, the central spray lance 17 of the spray device 4 preferably comprises a plurality of spray nozzles, in the embodiment of FIG. 2 two spray nozzles 15, 16, which are , preferably a swirl atomizing nozzle. The two atomizing nozzles 15, 16 of the central atomizing lance 17 can be supplied with liquid fuel from a common liquid fuel supply 21 in the liquid fuel operating mode. The fuel directed by the liquid fuel supply 21 can be split into two liquid fuel partial supplies 21a, 21b, whereby both atomizing nozzles 15, 16 of the central atomizing lance 17 are supplied with liquid fuel.

The central spray lance 17, with its two spray nozzles 15, 16, injects the liquid fuel towards the combustion chamber 1 with an injection angle α of max. 60°, preferably max. 55°. Whether both spray nozzles 15, 16 of the spray lance 17 are operated together or one of these spray nozzles 15, 16 is operated alone, the injection angle α is respectively max 60°, preferably max 55°. °. Thereby it is ensured that neither the walls 2a of the pre-combustion chamber 9 nor the walls 2 of the combustion chamber 1 are wetted by the liquid fuel, whereby a more effective combustion of the liquid fuel can be provided.

Through the gap 6, combustion air can be supplied to the combustion chamber 1, in particular the precombustion chamber 9, as described above. The air flow 14 through the radial gap 6 is used, on the one hand, for cooling the central spray lances 17 of the spray device 4 , and on the other hand, the air flow 14 is at least partially external to the spray lances 17 . It surrounds the liquid fuel injection cone 8a and envelops the injection cone 8a.

A special combustion air 14, which can be supplied to the combustion chamber 1, in FIG. is in particular between 1% and 10%.

The combustion air stream 14 can then not only be supplied to the combustion chamber 1 through the radial gap 6 in the liquid fuel operating mode, but can also be supplied to the combustion chamber 1 through the radial gap 6 in the gaseous fuel operating mode. Yes, in the gaseous fuel operating mode the atomizer 4, and in particular its atomizing lance 17, is not in operation, so that in the gaseous fuel operating mode no fuel is introduced by the atomizer 4, but only through the swirl 3. be introduced.

As mentioned above, the atomizing lances 17 are centrally located with respect to the central longitudinal axis 20, and through the atomizing lances 17 liquid fuel can be introduced into the central recirculation zone in the liquid fuel operating mode. A very stable combustion can thereby be ensured. The introduction of the liquid fuel through the central spray lance 17 with reference to the central longitudinal axis 20 takes place locally, i.e. not homogeneously into the combustion air, so that premixing of the liquid fuel with the combustion air is not performed.

As mentioned above, the combustion chamber 1 contains, in addition to the central atomizing lance 17, a plurality of distributed atomizing nozzles 18, which are preferably arranged on a circular orbit 19. These dispersed atomizing nozzles 18 can be supplied with liquid fuel through a separate liquid fuel supply 22 (see FIG. 1), and like the central atomizing lance 17, the dispersed atomizing nozzles 18 generally have the same In the direction the liquid fuel is introduced into the precombustion chamber 9 or into the combustion chamber 1, the injection angle β being smaller than the injection angle α, the injection angle β of the dispersed atomizing nozzles 18 preferably being at most 40°. °, preferably at most 30°.

By means of atomizing nozzles 18 which are preferably evenly distributed over a circular orbit 19, the fuel is introduced into the combustion chamber 1, in particular into the precombustion chamber 9, while forming a uniform distribution with the combustion air and at the same time the combustion air and the liquid Partial premixing with the fuel is provided, especially aided by the distributed atomizing nozzles 18 being arranged adjacent to the outlet of the swirling body 3 . This partial premixing can be improved if radius _d18 is greater than radius _d3 . Radius _d18 can thus be between 1.0 and 1.1 times radius _d3 .

A double-jet nozzle or a so-called plane jet is preferably used as the distributed spray nozzle 18 . The distributed atomizing nozzles 18 provide a uniform supply of liquid fuel to the combustion air and also provide partial premixing of the liquid fuel and combustion air.

In particular, if the combustion chamber 1 is to operate in gaseous fuel operating mode, the combustion chamber 1 is supplied with a mixture of gas and combustion air through the swirling body 3 .

Similarly, combustion air may be supplied through the annular gap 6 also in the gaseous fuel operating mode. A combustion air stream 14 directed through the annular gap 6 branches off upstream of the swirling body 3 in the region of the gap, the so-called plenum 10 .

FIG. 1 shows an air conduit 11 through which the combustion air can branch from the plenum 10 , the combustion air 14 branching from the plenum 10 through the air conduit 11 being constituted by the wall 12 . from the air chamber 7, through the annular gap 6 formed between the atomizing lance 17 of the atomizing device 4 and the adjacent member 5, into the precombustion chamber 9 of the combustion chamber 1. can be introduced into

In particular, when the combustion chamber 1 is operated in the liquid fuel operating mode with the atomizer 4 activated, the combustion chamber 1 or pre-combustion chamber 9 is supplied with liquid fuel through the atomizer 4 and the combustion air is It is fed through the swirling body 3 and preferably through the annular gap 6 between the central spray lance 17 and the member 5 .

In a first advantageous operating state, in the liquid fuel operating mode, not only the central atomizing lance 17 of the atomizing device 4, but also the distributed atomizing nozzles 18 have combustion over the entire operating range between no load and full load. It is provided that it is used to supply the chamber 1 with liquid fuel.

For this first operating state, FIG. 4 shows a plurality of curves 21, 22, 23 and 24 for the load L of the gas turbine, curve 21 passing through the central spray lance 17. 21 corresponds to the liquid fuel supply 21, curve 22 corresponds to the liquid fuel supply 22 through the distributed atomizing nozzles 18 and curve 23 is introduced through the central atomizing lance 17, which contributes to the total load L. The curve 24 shows the percentage of the load that can be supplied by combustion of liquid fuel, curve 24 showing the percentage of the total load L that can be supplied by combustion of fuel introduced into the combustion chamber through the distributed atomizing nozzles 18. ing.

FIG. 4 shows that fuel is delivered to the combustion chamber 1 via both the central atomizing lance 17 and the distributed atomizing nozzles 18 throughout the entire load range, in particular between 0% (no load) and 100% (full load). preferably a constant amount of liquid fuel through the central spray lance 17 (see curve 21) in all operating regions between 0% (no load) and 100% (full load) when supplied to , are supplied to the combustion chamber 1 . The adjustment of the output is done by changing the liquid fuel introduced into the combustion chamber 1 through the distributed atomizing nozzles 18 (see curve 22), so that with increasing load demand L the load rate 23 of the central atomizing lance 17 becomes , decreases with respect to the load rate of the dispersed spray nozzles 18, or the corresponding load rate 24 of the dispersed spray nozzles 18 increases.

Over the entire load range, or in the operating range between no load and full load, not only the central atomizing lance 17 but also the distributed atomizing nozzles 18 are used to supply liquid fuel to the combustion chamber. In the operating concept, fuel is introduced into the combustion chamber 1 through exclusively one of the two spray nozzles 15, 16 of the spray lance 17, in particular during acceleration of the gas turbine of combustion in the combustion chamber 1. that both spray nozzles 15, 16 of the spray lance 17 introduce fuel into the combustion chamber 1 through the spray lance 17 after acceleration and after reaching a predetermined rotational speed of the gas turbine. is specified to be used.

As mentioned above, according to the operating concept of FIG. 4, over the entire operating range and over the load range of the gas turbine, the amount of fuel supplied through the central spray lance 17 is constant, and the power regulation is exclusively This is done by varying the amount of fuel supplied through the distributed atomizing nozzles 18 . This operating concept is particularly suitable for fast load switching in gas turbines. This is because, except for the ignition process, there is no need to activate or deactivate the atomizing nozzle. Also, there is no need to clean the spray nozzle after stopping the spray nozzle. This operating concept lends itself to very reliable and stable combustion of liquid fuels. Additionally, fuel emissions can be reduced. In particular, nitrogen oxide emissions can be less than 150 vppm for 15% oxygen.

FIG. 5 reveals a second operating concept of a combustion chamber according to the invention or a gas turbine according to the invention comprising a combustion chamber according to the invention. FIG. 5 shows that the load range L between no load (0%) and full load (100%) is divided into two load ranges. a load range between no load (0%) and limit value GW and a load range between limit value GW and full load (100%).

According to a second operating concept according to the invention in FIG. Not only lances 17 but also distributed spray nozzles 18 are used. Preferably, in this load range the amount of fuel introduced through the central spray lance 17 (see curve 21) is then constant and the power regulation is again exclusively introduced by the distributed spray nozzles 18. by changing the amount of liquid fuel applied (see curve 22).

In the load range above a given limit value GW, the central spray lance 17 is switched off, so that fuel is no longer supplied through the spray lance 17 and the load between the load limit GW and full load (100%). In the higher load range, liquid fuel is supplied to the combustion chamber 1 exclusively through distributed atomizing nozzles 18 .

The advantage of this second operating concept according to the invention is that when the load exceeds a given load limit GW, the liquid fuel is not introduced centrally into the recirculation zone of the combustion chamber 1, but exclusively distributed. uniform introduction into the combustion air and partial premixing with the combustion air is ensured for all liquid fuels introduced, thereby reducing exhaust gas emissions, in particular nitrogen oxide emissions. can be further reduced with respect to the operating concept of FIG. In particular, nitrogen oxide emissions of less than 90 vppm are achievable for 15% oxygen.

REFERENCE SIGNS LIST 1 combustion chamber 2 wall 2a wall 3 swirl body 4 atomizer 5 member 6 radial gap 7 air gap 8a spray cone 8b spray cone 9 precombustion chamber 10 air gap/plenum 11 air conduit 12 wall 13 combustion air flow 14 combustion air flow 15 atomization Nozzle 16 atomizing nozzle 17 atomizing lance 18 atomizing nozzle 19 circular track 20 longitudinal center axis 21 liquid fuel supply 21a liquid fuel partial supply 21b liquid fuel partial supply 22 liquid fuel supply 23 load ratio 24 load ratio 25 valve

Claims (13)

A combustion chamber (1) of a gas turbine for burning fuel in the presence of combustion air, said combustion chamber (1) being configured as a dual-fuel combustion chamber, said combustion chamber containing gaseous fuel In the operating mode a mixture of gaseous fuel and combustion air can be fed through the swirl (3), said combustion chamber being supplied with liquid fuel through the atomizing device (4) in the liquid fuel operating mode, and In a combustion chamber (1) to which combustion air can be supplied through the swirling body (3),
Said atomizing device (4) has at least one atomizing nozzle (15, 16), with reference to a longitudinal central axis (20) of said combustion chamber (1) or pre-combustion of said combustion chamber (1). having a central spray lance (17) relative to the central longitudinal axis (20) of the chamber (9),
Said atomizing device (4) is positioned relative to said longitudinal central axis (20) of said combustion chamber (1) or said longitudinal central axis ( 20) having a plurality of spray nozzles (18) distributed as a reference ,
Said central spray lance (17) is at least partially surrounded on the radially outer side by adjacent members (5) while forming a radial gap (6), said combustion chamber (1) having , through said radial gap (6), combustion air may be fed around said swirling body (3),
Combustion chamber (1) characterized in that the axial ends of said adjacent members (5) are located closer to said combustion chamber (1) than the axial ends of said central spray lances (17). ). The dispersed atomizing nozzles (18) extend around the central longitudinal axis (20) of the combustion chamber or around the central longitudinal axis (20) of the precombustion chamber of the combustion chamber. 2. Combustion chamber according to claim 1, characterized in that it is arranged on a circular orbit (19). The center point of the circular orbit (19) in which the dispersed atomizing nozzles (18) are arranged is the longitudinal center of the combustion chamber (1) or the precombustion chamber (9) of the combustion chamber (1). 3. Combustion chamber according to claim 2, characterized in that it is located on the axis (20). characterized in that the radius of the circular track (19) in which the dispersed spray nozzles (18) are arranged is between 0.4 and 1.1 times the inner radius of the orbiting body (3). 4. A combustion chamber according to claim 2 or 3, wherein The central spray lance (17) has at least two spray nozzles (15, 16), said spray nozzles individually and together having a maximum injection angle (α) of 60°. each supplying a cone (8a),
5. Any one of claims 1 to 4, characterized in that each of the dispersed spray nozzles (18) supplies a respective spray cone (8b) with a maximum injection angle (β) of 40 °. combustion chamber as described in . In said combustion chamber (1), bypassing said swirl (3), said radial gap (6) between said atomizing lance (17) of said atomizing device (4) and said adjacent member (5) ) is between 1% and 10% of the combustion airflow that can be supplied to the combustion chamber through the swirl ( 3 ). Combustion chamber according to any one of the preceding claims. The combustion chamber contains combustion air, both in the gaseous fuel mode of operation and in the liquid fuel mode of operation, between the atomizing lance (17) of the atomizing device (4) and the adjacent member (5). 7. Combustion chamber according to any one of the preceding claims, characterized in that it can be fed through the radial gap (6) of . a combustion chamber (1) according to any one of claims 1 to 7 for burning a fuel in the presence of combustion air ;
a turbine for expanding the exhaust gases produced during combustion;
gas turbine. A method for operating a gas turbine according to claim 8 , comprising:
the combustion chamber (1) is supplied with a mixture of gaseous fuel and combustion air through a swirling body (3) in the gaseous fuel operating mode;
A method, characterized in that said combustion chamber (1) is supplied with liquid fuel through an atomizer (4) and at least with combustion air through said swirl (3) in a liquid fuel operating mode. In the liquid fuel operating mode, both the central atomizing lance (17) and the distributed atomizing nozzles (18) supply liquid fuel to the combustion chamber (1) throughout the operating range between no load and full load. 10. A method according to claim 9 , characterized in that it is used for Through the central atomizing lance (17), the combustion chamber (1) is supplied with a constant amount of liquid fuel over the entire operating range between no load and full load, and the regulation of power is controlled by the combustion chamber ( 11. A method according to claim 10 , characterized in that 1) is carried out by varying the amount of liquid fuel supplied through said dispersed atomizing nozzles (18). In the liquid fuel operating mode, both the central atomizing lance (17) and the decentralized atomizing nozzles (18) supply liquid fuel to the combustion chamber (1) in the operating region below a predetermined load limit. but in the operating range above the predetermined load limit, the atomizing nozzles (18) which are distributed exclusively are used to supply the combustion chamber (1) with liquid fuel, 10. The method of claim 9 . In the operating region below the given load limit, a constant amount of liquid fuel is supplied through the central atomizing lance (17), and the regulation of power is applied to the combustion chamber (1) by the dispersed atomizing nozzles (18). 13. A method according to claim 12 , characterized in that it is carried out by changing the amount of liquid fuel supplied through ).

Images