Gas turbine burner

Abstract

Gas turbine burner (1) with an inner air duct (3) with a first air swirl generator (3a) and at least one outer air duct (5) with at least one second air swirl generator (5a), with a fuel supply (7) and with a burner outlet opening area (9) which opens into a combustion zone (13) via a burner outlet opening (11), wherein the inner air duct (3), the at least one outer air duct (5) and the fuel supply (7) open into the burner outlet opening area (9), wherein the fuel supply (7) opens into the burner outlet opening area (9) between the inner and the at least one outer air duct (3, 5), wherein the fuel supply (7) has at least one first and one second fuel supply channel (7a, b), wherein the first fuel supply channel (7a) has a first fuel swirl generator (8a) and the second fuel supply channel (7b) has a second fuel swirl generator (8b) exhibitswherein the fuel volume flow in the first and second fuel supply channels (7a,b) is individually adjustable to adjust the swirl of a resulting fuel flow entering the burner outlet opening area (9).

Description

[0001] The present invention relates to a gas turbine burner according to the preamble of claim 1.

[0002] Gas turbine burners are used, for example, in gas turbines for aircraft engines. Due to new emission regulations and the desire for more efficient combustion, it is necessary to optimize the combustion process in gas turbine burners with regard to efficiency and emissions.

[0003] Gas turbines are based on continuous combustion under high pressure, where the intake air is compressed and the oxygen it contains is used as a reactant for the combustion process in a combustion chamber. The hot, pressurized combustion products are passed through the turbine to drive the compressor and generate usable net energy. Heat is produced by the combustion of a typically gaseous or liquid fuel in the combustion chamber. The combustion chamber itself must ensure efficient operation, so that heat release within it is rapid and emissions are minimal. However, operational safety, such as preventing combustion failure, must also be guaranteed, which imposes limitations during operation.Swirl-stabilized combustion has proven to be a compelling concept for ensuring rapid mixing and flame stabilization, resulting in low emissions and favorable flame characteristics. Typically, a swirl is imparted to the airflow, leading to a widening of the fluid flow after the burner exit and creating a stable recirculation and combustion zone. Such a swirl burner is known, for example, from DE 10 2012 217 263 A1 of the applicant.

[0004] The swirl intensity is determined by the alignment of the swirl device and burner arranged in the air duct and is usually a fixed value for a specific combustion chamber, always seeking a compromise for all requirements and operating conditions.

[0005] In gas turbine burners with a predetermined geometry, both the air and fuel flow rates are varied at different power levels, which can result in lower efficiency and increased emissions at certain operating points. The flow field present in the combustion chamber is primarily influenced by the swirl number.

[0006] The ability to make adjustments across the entire operating range of the combustion chamber would be advantageous in order to generate flow fields suitable for different operating conditions. However, the difficulty lies in the fact that moving parts are difficult or impossible to implement, or would be considered unacceptable, due to safety and reliability requirements in the prevailing high-pressure and high-temperature environment of the burner and combustion chamber.

[0007] The object of the present invention is to create a gas turbine burner that allows improved adaptation to different operating conditions.

[0008] A first embodiment of a gas turbine burner according to the invention is defined by the features of claim 1. A second embodiment of a gas turbine burner according to the invention is defined by the features of claim 11.

[0009] A first embodiment of a gas turbine burner according to the invention comprises an inner air duct with a first air swirl generator and at least one outer air duct with at least one second air swirl generator, as well as a fuel supply. Furthermore, the gas turbine burner has a burner outlet area that opens into a combustion zone via a burner outlet opening. The inner air duct, the at least one outer air duct, and the fuel supply open into the burner outlet area. The fuel supply opens into the burner outlet area between the inner and the at least one outer air duct.The invention is characterized in that the fuel supply has at least a first and a second fuel supply channel, wherein the first fuel supply channel has a first fuel swirl generator and the second fuel supply channel has a second fuel swirl generator, wherein the fuel volume flow in the first and the second fuel supply channel is individually adjustable to adjust the swirl of a resulting fuel flow entering the burner outlet opening area.

[0010] Within the scope of the invention, the fuel supply opening between the inner and at least one outer air duct into the burner outlet area means that, in the case of multiple outer air ducts, the fuel supply is located between the inner air duct and one of the outer air ducts, whereby the fuel supply does not necessarily have to be directly adjacent to the inner air duct. For example, with two outer air ducts, the fuel supply can be located directly adjacent to the inner air duct and the first of the outer air ducts, or it can be arranged between the outer air ducts and directly adjacent to them, in which case the fuel supply remains located between the second of the outer air ducts and the inner air duct.

[0011] If there are multiple external air ducts, it is not necessarily the case that each of the external air ducts has to have an air swirl generator.

[0012] The ability to individually adjust the flow rates in the first and second fuel feed channels allows, for example, fuel to be directed only through the first fuel feed channel and thus only through the first fuel swirl generator, only through the second fuel feed channel and thus only through the second fuel swirl generator, or in any desired ratio between the first and second fuel feed channels. This allows the resulting swirl of the fuel flow entering the burner outlet area to be modified.The fuel flow entering the burner outlet area consists of fuel that is guided through the first fuel feed channel and thus has a swirl imparted by the first fuel swirl generator, fuel that is guided through the second fuel feed channel and thus has a swirl imparted by the second fuel swirl generator, or a mixture of fuel guided through the first and second fuel feed channels, which thus has a swirl imparted partly by the first fuel swirl generator and partly by the second fuel swirl generator and therefore has a swirl resulting from the mixing.

[0013] With the gas turbine burner according to the invention, it is thus possible to easily change the swirl of the fuel flow by varying the fuel volume flow through the first and second fuel supply channels, thereby eliminating the need for any moving parts in the hot, high-pressure section of the gas turbine burner. This adjusted swirl of the fuel volume flow, as a result of the mixing with air, specifically influences the swirl of the air-fuel volume flow. Therefore, the gas turbine burner according to the invention can be used more effectively in various operating situations, since the swirl of the fuel flow can be easily adjusted.

[0014] The gas turbine burner according to the invention is particularly advantageous for gas turbine burners that are operated with large volume flows of fuel, such as hydrogen gas turbines, since the fuel volume flow, which is supplied with swirl, then has a particularly large influence on the flow field of the air that passes through the inner air channel and the outer air channel in the burner outlet opening area.

[0015] The first and second fuel supply channels can be arranged concentrically.

[0016] Preferably, the first and second fuel supply channels share a common outlet opening that leads into the burner outlet area. The first and second fuel supply channels are thus joined before the common outlet opening, so that the fuel conveyed through the first and second fuel supply channels mixes at least partially before exiting into the burner outlet area.

[0017] Alternatively, the first and second fuel supply channels can each have an outlet opening, with the outlet openings leading into the burner outlet area. In this embodiment, the fuel supplied through the first and second fuel supply channels is only mixed in the burner outlet area.

[0018] Depending on the design of the gas turbine burner and the inner and at least one outer air duct, the option of a common outlet opening or separate outlet openings may be advantageous.

[0019] In one embodiment of the invention, it is provided that the first and the second fuel swirl generators are designed as radial swirl generators.

[0020] Alternatively, it can be provided that the first and second fuel swirl generators are designed as axial swirl generators.

[0021] In another alternative configuration, the first fuel swirl generator can be designed as an axial swirl generator and the second fuel swirl generator as a radial swirl generator. In this configuration, the first fuel feed channel can be the innermost one, with the second fuel feed channel surrounding the first, or the second fuel feed channel can be the innermost one, with the first fuel feed channel surrounding the second.

[0022] The corresponding designs of the fuel supply channels and fuel swirl generators offer various possibilities for constructive adaptation to different requirement profiles of a gas turbine burner.

[0023] The first and second fuel swirl generators can be configured to align, with the first generating a flow with a different swirl number than the flow generated by the second. Alignment of the first and second fuel swirl generators means that they each produce a flow with a swirl directed in the same direction, although in this case, the resulting flows have different swirl numbers. This allows the swirl of the resulting fuel flow to be advantageously adjusted by appropriately controlling the volumetric flow rate of fuel passing through the first and / or second fuel feed channel.

[0024] It is also possible for the first and second fuel swirl generators to be configured in opposite directions. The flows generated by the first and second fuel swirl generators thus exhibit a swirl opposite to that of the other flow. It is also possible for the first fuel swirl generator to produce a flow with a different swirl number than the flow generated by the second fuel swirl generator.

[0025] In this embodiment as well, the swirl of the resulting fuel flow can be advantageously adjusted by appropriately controlling the volume flow of fuel passing through the first and / or second fuel feed channel. The configuration with a first and second fuel swirl generator that are oriented in opposite directions has the advantage that, particularly with large fuel volume flows, the swirl imparted by one of the fuel swirl generators can be easily influenced by the opposing direction of the other fuel swirl generator.

[0026] A second embodiment of a gas turbine burner according to the invention comprises an inner air channel with a first air swirl generator and at least one outer air channel with at least one second air swirl generator, as well as a fuel supply. Furthermore, the gas turbine burner has a burner outlet area that opens into a combustion zone via a burner outlet opening. The inner air channel, the at least one outer air channel, and the fuel supply open into the burner outlet area.The second embodiment is characterized in that the fuel supply comprises a first fuel supply guide system with several first fuel supply bores and a second fuel supply guide system with several second fuel supply bores, wherein the first fuel supply bores are oriented at a first angle relative to an injection direction and the second fuel supply bores at a second angle relative to the injection direction, the first angle being different from the second angle, and wherein the fuel volume flow rate in the first and the second fuel supply guide systems is individually adjustable to control the swirl of a resulting fuel flow entering the burner outlet area. The first fuel supply bores and the two fuel supply guide systems can each be arranged axially symmetrically about a burner axis.

[0027] Within the scope of the invention, the term injection direction is understood to mean the main direction in which the fuel is supplied, wherein, due to the first and second angles of the first and second fuel supply bores, the supplied fuel has a velocity component that deviates from this injection direction, thereby creating a swirl in the fuel flow.

[0028] If there are multiple external air ducts, it is not necessarily the case that each of the external air ducts has to have an air swirl generator.

[0029] The ability to individually adjust the flow rates in the first and second fuel supply systems allows, for example, fuel to be directed only through the first fuel supply bores (and thus only at the first angle), only through the second fuel supply bores (and thus only at the second angle), or in any desired ratio through the first and second fuel supply bores into the burner outlet area. Since the first and second fuel supply bores, positioned at the first and second angles respectively, generate a resulting fuel flow with a swirl in the burner outlet area, this swirl can be influenced by changing the fuel flow rate through the first and second fuel supply bores.

[0030] The fuel flow entering the burner outlet area consists of fuel supplied through the first fuel feed bores, which is thus introduced at the first angle and has a first swirl; fuel supplied through the second fuel feed bores, which is thus introduced at the second angle and has a second swirl; or a mixture of fuel supplied through the first and second fuel feed bores, which mixes and thus results in a fuel flow with a swirl.

[0031] With the gas turbine burner according to the invention, it is thus possible to easily change the swirl of the fuel flow by varying the fuel volume flow through the first and second fuel supply systems, thereby completely eliminating the need for moving parts in the hot, high-pressure section of the gas turbine burner. Therefore, the gas turbine burner according to the invention can be used more effectively in various operating situations, since the swirl of the fuel flow can be easily adjusted.

[0032] The gas turbine burner according to the second embodiment is also particularly advantageous for gas turbine burners that are operated with large volume flows of fuel, such as hydrogen gas turbines, since the fuel volume flow, which is supplied with swirl, then has a particularly large influence on the flow field of the air that passes through the inner air channel and the outer air channel in the burner outlet opening area.

[0033] The fuel supply can be designed as a jet-in-coflow supply, with the first and second fuel supply bores opening into the burner outlet area between the inner and at least one outer air duct.

[0034] Within the scope of the invention, the opening of the first and second fuel supply bores between the inner and the at least one outer air duct into the burner outlet opening area means that, in the case of multiple outer air ducts, the first and second fuel supply bores are located between the inner air duct and one of the outer air ducts, whereby the first and second fuel supply bores do not necessarily have to be directly adjacent to the inner air duct. For example, in the case of two outer air ducts, one of the first and second fuel supply bores can be directly adjacent to the inner air duct and the other to the first of the outer air ducts. Alternatively, the first and second fuel supply bores can be arranged between the outer air ducts and directly adjacent to them, in which case the first and second fuel supply bores are still located between the second of the outer air ducts and the inner air duct.

[0035] The injection direction has a velocity component parallel to the main air supply direction, whereby the air supplied through the inner and outer air channels also has a swirl and thus a similar velocity component, but differing from the main air supply direction.

[0036] Alternatively, the fuel supply can be configured as a jet-in-crossflow system, with the first and second fuel supply bores directed onto a section of the burner outlet area upstream of the inner air duct, or onto a section of the burner outlet area upstream of at least one outer air duct, or upstream of one of the outer air ducts. The injection direction of the first and second fuel supply bores is thus arranged transversely to the main air outlet direction, resulting in advantageous mixing of the supplied fuel and air.

[0037] It is also possible that the first fuel supply system is designed as a jet-in coflow system and the second fuel supply system as a jet-in crossflow system. Accordingly, the fuel flow exiting the first fuel supply bores has a velocity component parallel to the burner axis, whereas the fuel flow exiting the second fuel supply bores has a velocity component perpendicular to the burner axis.

[0038] The invention will be explained in more detail below with reference to the following figures. These show: Fig. 1a a schematic representation of a first embodiment of a gas turbine burner according to the invention, Fig. 1b-e variants of the fuel supply of the in Fig. 1a illustrated embodiment, Fig. 2a a second embodiment of a gas turbine burner according to the invention, Fig. 2b a top view of the fuel supply of the in Fig. 2a illustrated embodiment, Fig. 2c a schematic cross-sectional view through a section of the fuel supply of the in Fig. 2a illustrated embodiment of the gas turbine burner according to the invention, and Fig. 2d-h different variants of the fuel supply of the in Fig. 2a illustrated embodiment of a gas turbine burner according to the invention.

[0039] In the Fig. Figure 1a-1e is a schematic representation of a first embodiment of a gas turbine burner 1 according to the invention.

[0040] The gas turbine burner 1 has an inner air duct 3 and an outer air duct 5. A first air swirl generator 3a is arranged in the inner air duct 3, and a second air swirl generator 5a is arranged in the outer air duct 5. A fuel supply 7 is arranged between the inner air duct 3 and the outer air duct 5. The inner air duct 3, the outer air duct 5, and the fuel supply 7 open into a burner outlet area 9, which opens into a combustion zone 13 via a burner outlet opening 11 or directly into the combustion zone 13.

[0041] The fuel supply 7 has at least one first fuel supply channel 7a and one second fuel supply channel 7b. The first fuel supply channel 7a has a first fuel swirl generator 8a, and the second fuel supply channel 7b has a second fuel swirl generator 8b. The fuel flow rate in the first and second fuel supply channels 7a, 7b can be individually adjusted so that the fuel flow rate passing through the first and second fuel swirl generators 8a, 8b, respectively, can be varied, thereby adjusting the swirl of the resulting fuel flow entering the burner outlet area 9.

[0042] The first and second fuel swirl generators 8a, 8b can, as in Fig. The one shown in 1a is designed as a radial swirl generator. In the case of the one shown in Fig. In the embodiment shown in Figure 1a, the first and second fuel supply channels 7a, 7b have a common outlet opening 7c that leads into the burner outlet area 9. The fuel volume flows that are guided through the first and second fuel supply channels 7a, 7b are thus at least partially mixed together before exiting into the burner outlet area 9 and enter the burner outlet area 9 through the common outlet opening 7c.

[0043] As in Fig. As shown in 1 b, the fuel supply channels 7a, 7b can each also have an outlet opening 7c which leads into the burner outlet opening area 9.

[0044] In the burner outlet opening area 9, the resulting fuel flow is mixed with the swirled air of the inner air channel 3 and the outer air channel 5, before the fuel-air mixture then enters the combustion zone 13.

[0045] In the variant according to Fig. 1b are the first and second fuel swirl generators 8a, 8b just as in the one in Fig. The embodiment shown in 1a is designed as a radial swirl generator.

[0046] In Fig. Figure 1c shows a variant in which the first and second fuel swirl generators 8a, 8b are designed as axial swirl generators, with the first and second fuel supply channels 7a, 7b having a common outlet opening 7c.

[0047] In Fig. Figure 1d shows the variant in which the first and second fuel swirl generators 8a, 8b are represented as axial swirl generators, with the first and second fuel supply channels 7a, 7b each having an outlet opening 7c.

[0048] In Fig. Figure 1e shows an embodiment in which the first fuel swirl generator 8a in the first fuel supply channel 7a is designed as a radial swirl generator and the second fuel swirl generator 8b in the second fuel supply channel 7b is designed as an axial swirl generator, wherein the first and the second fuel supply channels 7a, 7b each have an outlet opening 7c.

[0049] The first and second fuel swirl generators 8a, 8b can, for example, be configured to be oriented in the same direction, so that they each generate a flow exhibiting swirl in the same direction. The first fuel swirl generator 8a can generate a flow with a different swirl number than the flow generated by the second fuel swirl generator 8b.

[0050] However, the first and second fuel swirl generators 8a, 8b can also be configured in opposite directions.

[0051] In the Fig. Figures 2a to 2h show a second embodiment of a gas turbine burner 1 according to the invention.

[0052] In the Fig. Figures 2a to 2c depict a first variant of the gas turbine burner 1. The gas turbine burner 1 has an inner air duct 3 with a first air swirl generator 3a and an outer air duct 5 with a second air swirl generator 5a. A burner outlet opening 9 leads via a burner outlet opening 11 into a combustion zone 13 or directly into the combustion zone 13. Furthermore, a fuel supply 7 is provided, which also leads into the burner outlet opening 9.

[0053] The fuel supply 7 has a first fuel supply guide system 10a with several first fuel supply bores 12a and a second fuel supply guide system 10b with several second fuel supply bores 12b. As can be seen from Fig. As can be seen in 2b, the fuel supply bores 12a, 12b are arranged alternately and open between the inner and outer air ducts 3, 5 into the burner outlet opening area 9.

[0054] Fuel inlet 7 is located in the Fig. In the embodiment shown in 2a to 2c, the fuel flow is configured as a jet-in-coflow feed, such that a velocity component of the fuel flow 4a runs parallel to the burner axis 1a. As shown in Figures 2a to 2c, the fuel flow is designed as a jet-in-coflow feed, such that a velocity component of the fuel flow 4a runs parallel to the burner axis 1a. Fig. As can be seen in Figure 2c, where the fuel supply bores 12a, 12b are shown schematically in a sectional view, the fuel supply bores 12a, 12b are aligned at a first and second angle relative to the direction vector of the burner axis 1a, so that fuel which is directed through the fuel supply bores 12a, 12b into the burner outlet opening area 9 is given a swirl. In the Fig. In the embodiment shown in 2c, the first and second fuel supply bores 12a, 12b are arranged in opposite directions, so that the fuel flow coming from the first and second fuel supply bores 12a, 12b receives a differently directed swirl.

[0055] The fuel volume flow in the first and second fuel supply systems 10a, 10b can be individually adjusted so that the swirl of the resulting fuel flow entering the burner outlet opening area 9 can be changed.

[0056] In Fig. 2d shows a second variant, which differs from the variant of Fig. 2a to 2c differ in that the fuel supply bores 12a, 12b are arranged next to each other in the radial direction of the gas turbine burner 1 and thus on two different radii.

[0057] In the Fig. Figures 2e to 2g show variants in which the fuel supply 7 is designed as a jet-in-crossflow supply, such that the injection direction 4 lies in the orthogonal plane of the burner axis 1a. Fig. 2e The fuel volume flow is fed into a section 9a of the burner outlet opening area 9 at the end of the inner air duct 3. In the Fig. 2f and Fig. 2g, the fuel volume flow is fed into a section 9b of the burner outlet opening area 9 at the end of the outer air duct 5. In this process, Fig. 2f the injection direction 4 is directed outwards from the burner axis 1a, whereas in the embodiment according to Fig. 2g the injection direction 4 is directed towards the burner axis 1a. In the Fig. 2d to 2g, the fuel supply bores are again aligned at the first and second angles relative to the injection direction 4 in order to generate flow with a corresponding swirl.

[0058] In Fig. Figure 2h shows an embodiment in which the fuel supply bores 12a are designed in a jet-in coflow supply, whereas the fuel supply bores 12b are designed as a jet-in crossflow supply.

[0059] Depending on the requirements profile for the gas turbine burner 1, a design can be created by varying the arrangement of the fuel supply 7, in which, during operation, a corresponding adjustment of the swirl of the resulting fuel flow can be achieved by varying the fuel volume flows in the first and second fuel supply channel 7a, 7b or in the first and second fuel supply guide system 10a, 10b. Reference symbol list 1 gas turbine burner 1a Brenner axis 3 inner air duct 3a first air swirl generator 4. Fuel injection direction 4a Velocity component of the fuel flow 5 outer air duct 5a second air swirl generator 7 Fuel supply 7a first fuel supply channel 7b second fuel supply channel 7c Exit opening 8a first fuel swirl generator 8b second fuel swirl generator 9 Burner outlet opening area 9a Section of the burner outlet opening area 9b Section of the burner outlet opening area 10a First fuel supply system 10b second fuel supply system 11 Burner outlet opening 12a first fuel supply boreholes 12b second fuel supply boreholes 13 Combustion zone QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] DE 10 2012 217 263 A1

[0003]

Claims

[1] Gas turbine burner (1) with an inner air duct (3) with a first air swirl generator (3a) and at least one outer air duct (5) with at least one second air swirl generator (5a), with a fuel supply (7) and with a burner outlet opening area (9) which opens into a combustion zone (13) via a burner outlet opening (11), wherein the inner air duct (3), the at least one outer air duct (5) and the fuel supply (7) open into the burner outlet opening area (9), wherein the fuel supply (7) opens into the burner outlet opening area (9) between the inner and the at least one outer air duct (3, 5), characterized in that the fuel supply (7) has at least one first and one second fuel supply duct (7a, b), wherein the first fuel supply duct (7a) has a first fuel swirl generator (8a) and the second fuel supply duct (7b) has a second fuel swirl generator (8b),wherein the fuel volume flow in the first and second fuel supply channels (7a,b) is individually adjustable to adjust the swirl of a resulting fuel flow entering the burner outlet opening area (9). [2] Gas turbine burner according to claim 1, characterized by , that the first and second fuel supply channels (7a,b) have a common outlet opening (7c) which leads into the burner outlet opening area (9). [3] Gas turbine burner according to claim 1, characterized by , that the first and second fuel supply channels (7a,b) each have an outlet opening (7c), the outlet openings (7c) leading into the burner outlet opening area (9). [4] Gas turbine burner according to any one of claims 1 to 3, characterized by , that the first and the second fuel swirl generators (8a,b) are designed as radial swirl generators. [5] Gas turbine burner according to any one of claims 1 to 3, characterized by, that the first and the second fuel swirl generators (8a,b) are designed as axial swirl generators. [6] Gas turbine burner according to any one of claims 1 to 3, characterized by , that the first fuel swirl generator (8a) is designed as an axial swirl generator and the second fuel swirl generator (8b) is designed as a radial swirl generator. [7] Gas turbine burner according to any one of claims 1 to 6, characterized by , that the first and the second fuel swirl generators (8a,b) are designed to be aligned, wherein the first fuel swirl generator (8a) produces a flow with a swirl number different from the flow produced by the second fuel swirl generator (8b). [8] Gas turbine burner according to any one of claims 1 to 6, characterized by , that the first and the second fuel swirl generators (8a,b) are designed in opposite directions. [9] Gas turbine burner according to claim 8, characterized by, that the first fuel swirl generator (8a) has a flow with a swirl number different from the flow generated by the second fuel swirl generator (8b). [10] Gas turbine burner (1) with an inner air duct (3) with a first air swirl generator (3a) and at least one outer air duct (5) with at least one second air swirl generator (5a), with a fuel supply (7) and with a burner outlet opening area (9) which opens into a combustion zone (13) via a burner outlet opening (11), wherein the inner air duct (3), the at least one outer air duct (5) and the fuel supply (7) open into the burner outlet opening area (9), characterized by, that the fuel supply (7) comprises a first fuel supply guide system (10a) with several first fuel supply bores (12a) and a second fuel supply guide system (10b) with several second fuel supply bores (12b), wherein the first fuel supply bores (12a) are oriented at a first angle relative to an injection direction (4) and the second fuel supply bores (12b) are oriented at a second angle relative to the injection direction (4), wherein the first angle is different from the second angle and wherein the fuel volume flow in the first and the second fuel supply guide system (10a,b) is individually adjustable to adjust the swirl of a resulting fuel flow entering the burner outlet opening area (9). [11] Gas turbine burner according to claim 10, characterized by, that the fuel supply (7) is designed as a jet-in-coflow supply, wherein the first and second fuel supply bores (12a,b) open between the inner and the at least one outer air duct (3,5) into the burner outlet opening area (9). [12] Gas turbine burner according to claim 10, characterized by , that the fuel supply (7) is designed as a jet-in crossflow supply, wherein the first and second fuel supply bores (12a,b) are directed towards a section (9a) of the burner outlet opening area (9) upstream of the inner air duct (3) or towards a section (9b) of the burner outlet opening area (9) upstream of the outer air duct (5).

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