KR20190108126A - A burner tip having an air channel structure and a fuel channel structure for a burner and a method for manufacturing the burner tip - Google Patents

Abstract

The present invention is a burner tip 19 for installation in the burner 11, which burner tip 19 is followed by a surface OF facing the combustion chamber BR, a surface OF and forming an air channel 20. Air channel structure 21 and a fuel channel structure 32 that follows the surface OF, which fuel flows through the fuel channel 33 when the burner tip 19 is in operation. Extends in the surface area OFB of the burner tip 19 along a first direction parallel to the surface OF, in order to cool the surface area OFB of the burner tip 19 by The fuel channel 33 extends rearwardly in the surface area OFB along a second direction 2R different from the first direction 1R.

Description

A burner tip having an air channel structure and a fuel channel structure for a burner and a method for manufacturing the burner tip

The present invention preferably relates to a burner tip having an air channel structure and a fuel channel structure, for a burner in a gas turbine. Moreover, a method, preferably an additive method, for producing a burner tip is described.

The burner tip is preferably provided for use in a hot machine path of a flow machine, preferably a gas turbine. The component further preferably comprises a nickel-based alloy and / or a superalloy, in particular a nickel- or cobalt-based superalloy. The alloy may be precipitation-cured or precipitation-curable.

Burner tips of the structure shown above are known, for example, from EP 2 196 733 A1. The burner tips described therein can be used, for example, in gas turbines, where the burner tips form a downstream end of a burner lance arranged in a main channel for combustion air. The burner tip has a double wall design where the outer wall creates a heat shield intended to keep the generated heat of combustion away from the inner wall. Thus an annular cavity, in other words an annular space, is arranged between the outer wall and the inner wall, which cavity can flow through the air through the opening for the purpose of cooling. In the described embodiment, the heat shield must be designed to withstand the thermal stresses caused by combustion occurring in the downstream combustion chambers. Thus, the outer wall of the burner tip represents a limiting factor on the service life of the burner tip.

The object of the present invention is to develop a burner tip of the kind mentioned in the introduction in such a way that an improvement in the service life of the component is caused. In particular, the present invention should allow for improved cooling of the burner tip. It is also an object of the present invention to specify a method for producing burner tips of this kind.

Manufacturing can be carried out, for example, by lost-core casting. However, according to the solution of the aforementioned problem, it is particularly advantageous for the additive manufacturing method to be used for the production. In this case, the burner tip may preferably be produced in one piece and in particular with a complex and / or optimized design with respect to the cooling effect, and the additive manufacturing is particularly complex with geometrically advantageously large surfaces for heat transfer. Allow structure.

Within the meaning of the present application, a method of additive manufacturing is to be understood as referring to the way in which the material from which the component is to be manufactured is added to the component during production. In this case, the component is already created in its final form or at least close to it. The constituent material or primary material is preferably in powder form, and through the additive manufacturing process, the material used to manufacture the component is physically strengthened under the application of energy.

Data describing the component (CAD model) is prepared for the selected additive manufacturing process so that the component can be manufactured. In order to generate an indication for the production plant, the data is converted into component data adapted to the manufacturing process so that a suitable process stage can be carried out at the production plant for the continuous manufacture of the component. The data is prepared for this in such a way that the geometric data for the layer (slice) of the component to be produced in each case is provided, which is also referred to as slicing.

Selective laser sintering (or selective laser sintering), selective laser melting (or selective laser melting), electron beam melting (or electron beam melting), laser metal deposition (or laser metal deposition) or gas dynamic Cold rolled steel (or gas dynamic cold spray) may be provided as an example of additive manufacturing. These methods are particularly suitable for the processing of metallic materials in powder form from which structural components can be produced.

In the case of SLM, SLS and EBM, the components are made layer-by-layer in the powder bed. Thus, this method is also referred to as a powder bed-based additive manufacturing method. A layer of powder is in each case produced in the powder bed, which layer is then locally melted or sintered by an energy source (laser or electron beam) in these areas where the component is produced. Thus, the components are continuously layered and can be removed from the powder bed after completion.

In the case of LMD and GDCS, the powder particles are fed directly to the surface on which the material is deposited. In the case of LMD, the powder particles melt directly by the laser at the target point on the surface, in which case they form a layer of the component to be produced. In the case of GDCS, the powder particles are significantly accelerated and, therefore, mainly due to their kinetic energy, they remain attached to the surface of the component upon simultaneous deformation.

GDCS and SLS have the feature that powder particles do not melt completely during these processes. This also, among other things, facilitates the manufacture of porous structures when the gaps between the particles are maintained. In the case of GDCS, melting occurs only at the periphery of the powder particles, which may melt due to severe deformation of their surface. For SLS, when choosing the sintering temperature, it is important to ensure that it is below the melting temperature of the powder particles. On the other hand, in the case of SLM, EBM and LMD, the energy application is intentionally high enough for the powder particles to melt completely.

The problems mentioned above are solved by the subject of the independent patent claims. Advantageous embodiments are the subject of the dependent claims.

One aspect of the invention relates to a burner tip for installation in a burner, the burner tip having a surface facing the combustion chamber and an air channel structure leading to and forming an air channel and a fuel channel structure leading to the surface. The fuel channel structure extends in the surface area of the burner tip along a first direction parallel to the surface for cooling the surface area of the burner tip by fuel flowing through the fuel channel when the burner tip is in operation, and then at least In part, it forms a fuel channel that extends backward, curves, or deflects in the surface area along a second direction different from the first direction.

The "rear extension" or curved course of the fuel channel is such that the cooling action (e.g. during the operation of the burner tip during use of the gas turbine) is particularly effective in the surface area of the burner tip via the fuel. It means that can occur. This means that combustion of compressor air, which is valuable for the efficiency of the flow machine, is no longer dependent upon cooling the surface or surface area of the burner tip. In addition, the conveying system for this compressor air can be saved, and the corresponding components are advantageously simplified.

In one embodiment, the fuel channel extends in the surface area with a number of turns parallel to the surface. In other words, the fuel channel is preferably diverted multiple times parallel to the surface, or extends in accordance with the transition.

In one embodiment, the fuel channel extends at least partially along the axis of symmetry or main flow of the burner tip during operation of the burner tip.

In one embodiment, the fuel channel extends into the burner tip starting from its course along the first direction. According to this embodiment, the area of the surface (surface area) spaced from the surface may also advantageously be cooled during operation of the burner tip. This then advantageously affects the service life of the entire structural component.

In one embodiment, the first direction is at an angle of 160 ° to 200 °, preferably 180 ° with respect to the second direction. This embodiment allows for particularly effective recycling or switching of the fuel channel, as described above.

The term "surface area" preferably describes the structural area of the burner tip proximate to the surface described above.

In one embodiment, the fuel channel opens later into the surface via at least one further direction change, for example 70 ° to 110 ° deflection, ie after its conversion into the interior of the burner tip. This embodiment enables efficient cooling when the burner tip is in use, while at the same time an advantageous design of the burner tip is realized, which is to be efficiently cooled by fuel when the burner tip is used, and at the same time to be supplied into the combustion chamber correspondingly. This is because the fuel can be preheated.

In one embodiment, the fuel channel has an area with an expanded cross section, in particular an interaction space or a collection space, after its course along the first direction and advantageously before opening into the surface. According to this embodiment, heat transfer from the surface area to the fuel located in the collection space or flowing through the collection space when the burner tip is in operation can be particularly advantageously facilitated. In particular, the expanded cross section means that the expanded volume is available for interaction and for the described heat transfer, so that the heat capacity (to absorb heat acting on the surface during operation of the burner tip) is Can be effectively increased.

In one embodiment, the air channel structure includes a central air channel leading to a central outlet opening in the burner tip. In particular, the air channel structure may represent or form the central air channel described above.

In one embodiment, the burner tip has an inlet area. The fuel channel as well as the air channel preferably extend coaxially in the inlet region. In other words, the air channel structure and the fuel channel structure are correspondingly designed.

In one embodiment, the fuel channel extends radially out of the air channel in the inlet region. In other words, the fuel channel structure and the air channel structure may be configured correspondingly.

In one embodiment, the burner tip preferably has an outlet region which is arranged offset (axially) along the axis of symmetry. Preferably, the outlet region, in which not only the air flow but also the fuel flow, may preferably appear from it, comprises the described surface or surface area.

In one embodiment, the fuel channel extends into the air channel at least partially radially in the outlet region.

In one embodiment, the fuel channel and the air channel extend in an interlocking or entwined manner or interwoven with each other, so that the surface area of the burner tip is advantageously (not only by fuel flow) ) Further cooling by air flow. However, the fuel channel and the air channel preferably extend without being in fluid communication with each other. Alternatively, the air channel and the fuel channel may be at least partially fluidly connected to each other.

In one embodiment, the burner tip is designed to be rotationally symmetrical at least about the described axis of symmetry.

In one embodiment, the air channel and / or fuel channel extend at least partially along the circumferential or tangential direction of the burner tip.

In one embodiment, preferably in the outlet region, the fuel channel structure has vanes that subdivide the fuel channel into (at least partially) a plurality of sub-channels. In this way, the cooling action while the burner tip is operating can likewise be advantageously optimized by improved heat transfer. The vanes described above may represent any form that can be achieved only by additive manufacturing techniques (as with other parts of the fuel channel structure or burner tip) in some cases.

In one embodiment, the fuel channel structure in the inlet region forms an annular chamber.

In one embodiment, the fuel channel structure is formed in such a way that the fuel channel extends through the annular chamber after its course along the second direction and prior to its opening into the surface.

In one embodiment, the fuel channel structure in the outlet region has a plurality of fuel channels that pass through the surface to the combustion chamber or open into the aforementioned surface. Through this embodiment, improved and / or more homogeneous cooling of the surface can be advantageously achieved.

In one embodiment, the air channel extends at least partially through the fuel channel and vice versa. This embodiment enables a particularly compact and effective design of the burner tip to be achieved.

In one embodiment, the air channel structure has a plurality of air channels that open to the surface or lead into the combustion chamber, for example at different exit angles with respect to the surface or surface normal. Through this embodiment, efficient surface cooling or film cooling of the surface can be particularly advantageously achieved.

In one embodiment, the air channel structure and / or the fuel channel structure form a channel cross section having a cross-sectional shape, for example an oval or star cross section, which is different from the round, in particular circular shape. Through this embodiment, heat transfer from the surface to the fuel or air flow can advantageously be further improved and / or optimized during the operation of the burner tip by an enlarged cross-sectional area (compared to the circular cross section).

In one embodiment, the surface is formed by an open porous wall or wall structure of the burner tip that forms a plurality of air channels through its porosity. Thus, according to the present embodiment, the surface area can be flowed through, for example, by the cooling air, particularly homogeneously, in order to cause effective cooling in the area of the burner tip.

In one embodiment, the burner tips are manufactured in a lamination or by a lamination manufacturing process.

In one embodiment, the burner tips are made integrally or in one piece.

Another aspect of the invention relates to a flow machine, for example a gas turbine, comprising the burner tip described.

Another aspect of the invention relates to a method for manufacturing a burner tip, which burner tip may in particular be manufactured or manufactured in a stack and / or integrally.

The configuration, features and / or advantages associated with the burner tip or flow machine in this case may in addition be related to the method or vice versa.

Other details of the invention are described below with the aid of the drawings.
1 shows a schematic cross-sectional view of a burner equipped with an exemplary embodiment of a burner tip according to the invention.
2 shows a schematic cross-sectional view of a burner tip of an embodiment according to the invention.
3 shows a schematic cross sectional view of a portion of a burner tip according to an embodiment of the invention.
4 shows a schematic cross sectional view of a burner tip in another embodiment of the invention.
5 shows a schematic cross-sectional view of a portion of a burner tip in accordance with another embodiment of the present invention.
6 shows in schematic cross-sectional view an exemplary embodiment of a method according to the invention.

In the exemplary embodiments and the drawings, the same elements or elements having the same effects are each provided with the same reference numerals. The elements shown and the ratios between them should not be regarded as being basically drawn to scale, but instead individual elements may be drawn as unbalanced thick or large for improved illustration and / or for a better understanding. There may be.

A burner 11 with a jacket 12 in which the main channel 13 of air is formed is shown in FIG. 1. The jacket 12 is constructed symmetrically about the longitudinal axis and / or the axis of symmetry 14 and has a burner lance 15 in the center of the main channel 13. Burner lance 15 is secured to main channel 13 with web 16. Furthermore, guide vanes 17 extend between burner lance 15 and jacket 12, causing air to vortex about axis of symmetry 14, as can be inferred from the indicated air arrow 18.

The burner lance 15 has a burner tip 19 at a downstream end, the burner tip being fueled via an annular channel 22 which is supplied with air through a central air channel 20 and arranged around the air channel 20. 23 is supplied.

The fuel 23 may be in gas or liquid form. The fuel may in particular be a natural gas, a gas containing hydrogen or a fluid or other fuel.

Air (see air flow or air channel 20) and fuel 23 are discharged through an opening in the burner tip, not shown in more detail, thereby mixing with the air flow from main channel 13. Air 21 typically cools burner tip 19 during this process (see below). Burner 11 follows the functional principle of the pilot burner. The burner may, for example, be mounted in the combustion chamber BR of the gas turbine, where the combustion chamber BR in this case creates a peripheral region 30 of the burner tip 19.

2 shows a schematic cross-sectional view of burner tip 19 as described above. In particular, a cross section along the axis of symmetry 14 is shown. The axis of symmetry 14 may likewise represent the rotational symmetry of the burner tip 19.

Burner tip 19 has an inlet region EB. Moreover, burner tip 19 has an outlet area AB. The outlet region AB is attached to the inlet region EB along the axis of symmetry 14 or arranged axially offset with respect to the inlet region EB.

Also shown in FIG. 2 is a central air channel 20 extending along the axis of symmetry 14. The air channel 20 leads to the outlet opening 24 of the burner tip 19. Another burner lance may be received in this air channel during operation (see below). During operation of the burner tip 19, for example in a gas turbine, the burner tip 19 in the air channel 20 is flowed by air, in particular compressor air, which air is in the air channel in the inlet region EB. Enter 20 and leave the air channel again at exit region AB. The air channel 20 is formed by the air channel structure 21.

During operation of the burner tip 19 of FIG. 2, the air flow is indicated by the dashed arrows in the air channel 20.

Burner tip 19 also has a fuel channel structure 32. The fuel channel structure 32 forms the fuel channel 33.

During operation of burner tip 19 in FIG. 2, fuel flow is indicated by a solid arrow in fuel channel 33.

The fuel channel 33 is arranged radially outside of the air channel 20, so that the fuel 23 can be radially guided out of the described air flow (when the burner tip 19 is in operation) ( Along the direction of air flow).

The fuel channel structure 32 may comprise or form an outer wall 28 of the burner tip 19.

The fuel channel structure 21 may comprise or form an inner wall 29 of the burner tip 19.

Burner tip 19 or air channel structure 21 is preferably configured in such a way that air channel 20 tapers from inlet region EB to outlet region AB. After the corresponding conical or tapered course, the air channel structure 21 once again forms an air channel 20 parallel to the axis of symmetry 14.

In the drawings, in particular in FIGS. 2 and 4, no other components are shown in the central air channel 20 (for ease of reference). When using burner tip 19, for example during operation of a gas turbine correspondingly comprising a burner tip (not explicitly identified), other components such as, for example, other ignition lances and / or oil lances may Advantageously it is arranged in this central area of the burner tip 19. The above-mentioned components are important to the function of the burner 11 and preferably in such a way that an air gap is formed during the operation of the burner tip which creates an effective cooling action of the above-described components and / or of the burner tip. Seal the channels at the same time.

In FIG. 2 it can also be seen that the outer wall likewise extends in the axis of symmetry 14 tapered or centrally arranged in the outlet area AB. In the outlet area AB, the fuel channel structure 32 is configured in such a way that the fuel channel 33 first extends parallel to the outer surface OF of the burner tip 19 or parallel to the surface OF. do. In particular, during operation of the burner tip 19, the fuel flow extends along a first direction 1R parallel to the surface OF.

Surface areas with a surface OF are identified using the reference OFB in this case. In particular, this surface area OFB, preferably at the outlet area AB of the burner tip 19, is directed to the fuel 23 which is guided through the fuel channel structure 32 during operation of the burner tip 19. Should be cooled effectively.

After the fuel (see arrow shown in fuel channel 33) extends by a certain length along a first direction parallel to the surface OF, the fuel channel is formed along the geometry of the fuel channel structure 32 along the second direction. Switched by the structure, it extends or switches backwards at least partially opposite the first direction and then leaves the surface area OFB of the burner tip 19.

In other words, through switching of the fuel channels in the surface area OFB, the area can be efficiently cooled by the fuel during the operation of the burner tip 19, which fuel is first induced close to the surface inside the component, , Which can then be switched and subsequently transferred into the combustion chamber BR at the provided plurality of fuel outlets (not explicitly identified in the drawing) (in some cases guided through itself) 3). Accordingly, the course of the fuel channel 33 or the geometry of the fuel channel structure 32 may correspond to or be similar to the design of a so-called “Klein bottle”.

The first direction may at least partially or partially describe the direction along the axis of symmetry (in the flow direction) or along the corresponding main flow direction. The second direction preferably represents a direction different from the first direction, preferably exactly opposite. The fuel channel 33 is preferably switched from the first direction to the second direction in a manner that first extends into the burner tip or corresponding surface area OFB after its course parallel to the first direction. In this way, the substructure of the surface area can also be cooled effectively.

The second direction is likewise parallel to the surface, but may preferably describe a direction opposite to the main flow direction. The second direction may alternatively or additionally extend inclined also by 90 ° or another angle with respect to the first direction.

Burner tip 19 may be configured in rotational symmetry or approximately rotational symmetry about its axis of symmetry 14. The second direction may for example extend correspondingly along the circumferential direction of the burner tip 19.

Along the circumferential direction (not explicitly identified in the figure), the burner tip 19 may correspondingly have a plurality of fuel channels 33 in the outlet region AB, which ( For example in a circumferentially arranged manner at equal intervals and into the combustion chamber BR over the surface OF (see FIG. 3). Accordingly, the position of the correspondingly produced fuel outlet through the opening of the fuel channel 33 to the surface OF may correspond to the conventional design of the fuel tip.

For example, through the aforementioned transition or rearward extension of an angle of about 160 to 220 °, preferably approximately 180 °, advantageously the cooling effect of the surface area (OFB) (compressor air commonly used for cooling By comparatively cold fuel). In other words, to cool the outer surface of the component, compressed air no longer needs to be forcibly taken instead, but instead from the compressor portion of a much cooler combustion gas (gas turbine (not explicitly shown)) For compressed cooling air used as approximately 50 [deg.] C. instead of 400 [deg.] C. may be directed directly below the component surface for cooling in the surface area OFB.

Following the rearward extension, the fuel channel 33 preferably experiences further deflection such as, for example, a deflection of 70 ° to 110 °, so that the fuel channel can then be opened to the surface OF or the combustion chamber You can leave the surface in the direction of (BR). In other words, the fuel can be retained or collected in the surface area OFB by the geometry of the fuel channel structure 32 for improved cooling action, and then again leaked and combusted into the combustion chamber BR under a given exit angle. .

The burner tips 19 described are preferably manufactured by a additive manufacturing process, preferably by selective laser melting (SLM) or electron beam melting (EBM). Additive manufacturing in particular allows components with integrated functionality to be manufactured. In particular, it is possible for the described burner tip 19 having the complexity of its channel structure as described to be manufactured in one piece without the heat shields normally required by the lamination means.

Since the burner tip 19 only needs to induce only a single fluid for cooling purposes, in some cases fewer connections may be advantageously required, as a result of which the manufacture and function of the component can be simplified.

Region B is also shown in FIG. 2, in which the fuel channel 33 has a larger cross section. This embodiment makes it possible for the larger volume of fuel 23 to be advantageously "collected" in the area B in order to bring about an effective cooling action.

3 shows in detail a cross section of the burner tip 19, preferably a cross section through the surface area OFB (see FIG. 2). The external fuel opening identified by reference numeral 34 defines the shape of the fuel channel 33 (see FIG. 2).

The arrows shown in FIG. 3 again indicate the course of fuel channel 33 or fuel 23. In particular, there are shown a plurality of fuel channels (indicated by the arrows), preferably provided but not visible in FIGS. 2 and 4, distributed over the circumference of the burner tip 19. In other words, the fuel channel 33 is preferably divided into a plurality of individual fuel sub-channels by one or a plurality of vanes 39 in the circumferential direction. These plurality of fuel channels, or sub-channels identified using reference numeral 34, are preferably spaced apart from one another in the circumferential direction (by vanes 39).

The sub-channels 34 are joined radially inwardly (as shown in FIG. 3), preferably extending into a single fuel channel 33 of the fuel tip 19. In this way, during operation of the burner tip 19, heat transfer from the structure of the burner tip to the fuel flow induced through the fuel channel 33, and thus cooling of the burner tip, can also be advantageously improved.

The geometry of the vanes as described is in particular not attainable using conventional manufacturing methods, and accordingly, according to the teachings described, are produced in a lamination and preferably integrally, for example in selective laser melting.

By way of example, a fuel channel 34 or opening having a rectangular cross section is identified in FIG. 3. Alternatively, however, other cross-sectional shapes may also be used, for example oval or star cross-sections, to achieve an improved cooling effect due to the extended surface and correspondingly improved heat exchange during operation of the burner tip 19. have.

The fuel channel structure 32 may also form an annular chamber (complexly formed), in particular according to the rotationally symmetrical embodiment of the burner tip 19 around its axis of symmetry. The fuel channel structure 32 is in the outlet region AB through the annular chamber, after its course along the second direction 2R and before its opening into the surface OF. It is also preferably formed in such a way as to extend (see arrow pointing to fuel 23 in FIG. 2).

In particular, the course of the arrows in FIG. 3 is in the fuel channel 33 due to the geometry of the fuel channel structure 32 in order to be able to effectively cool the surface area OFB of the burner tip 19 during operation. Indicates the conversion of fuel.

4 shows a sectional view (vertical section) of an alternative embodiment of a burner tip according to the invention. Unlike FIG. 2, the fuel channel 33 extends at least partially radially in the outlet region AB in the air channel 20. In addition, the fuel channel 33 and the air channel 20 additionally extend at least partially in an interlocking manner, in order to cool the surface area OFB of the burner tip 19 via air flow, This leads to a further improved cooling effect.

The air channel structure 21 has an opening 25 in the inlet region EB in an annular space that annularly surrounds the air channel or in a side wall which flow-connects the (central) air channel 20 to a plurality of individual air channels. .

The individual air channels 20 described above preferably cross at least partly with the course of the fuel channel structure 33 according to the embodiment of the air channel structure 21.

The aforementioned air channel according to the drawing of FIG. 4 may also lead into the combustion chamber BR at different exit angles, for example from 60 ° to 120 ° with respect to the surface OF or the corresponding surface normal. The aforementioned exit angle of the fuel channel 33 may vary, for example, along the axis of symmetry of the burner tip 19. As the exit angle becomes smaller (eg less than 90 °), film cooling on the surface OF of the burner tip 19 may be stronger or weaker.

In addition, the air channel structure 21 and the fuel channel structure 32 may form a channel cross section having a cross-sectional shape deviating from a round shape, in particular a circular shape. In particular, the aforementioned channel structures may be star and / or elliptical. All these geometries can be manufactured in a simple manner using the described additive manufacturing methods, thus allowing the inventive advantages of the present invention to be utilized.

In another embodiment, the surface OF may be formed by an open porous wall structure (not explicitly identified) that forms a plurality of air channels 20. This geometry may likewise be advantageously realized by additive manufacturing techniques and may contribute to improved cooling of the burner tip during operation.

FIG. 5 shows a cross-sectional view (section perpendicular to the symmetry axis) of the burner tip according to the embodiment of the burner tip described in FIG. 4 (similar to the representation in FIG. 3). In contrast to the representation of FIG. 3, it can be seen in FIG. 5 that an additional circular air opening 35 is provided which causes a cooling effect for the burner tip 19 via air cooling (in addition to fuel cooling). (See Figure 4). The dashed arrow comes from the opening 35 and is intended to indicate the air flow, while the solid arrow indicates the change of fuel flow according to the invention (similar to the figure of FIG. 3).

FIG. 6 shows in detail how the component 19 according to FIG. 2 or 4 can be produced by laser melting with a laser beam 37. Details of the powder bed 36 from which the air channel structure 21 and / or portions of the fuel channel structure 32 are made are shown. The fuel channel structure 32 is similar in design to, for example, the drawing of FIG. 2, and above all, preferably has the vanes described above (not shown in FIG. 6) and likewise defines the conversion of the fuel channel of the invention. do.

After manufacture of the finished structure, the powder 36 must be removed from the corresponding cavity forming the air channel system or fuel channel system or corresponding channel structure. This can be achieved, for example, by suction, shaking or blowing out.

The present invention is not limited to the exemplary embodiments by the description based on the exemplary embodiments, but includes each novel feature and each combination of features. This particularly includes each combination of features of the claims, even if this feature or combination thereof is not explicitly indicated by itself in the claims or the exemplary embodiments.

Claims (17)

A burner tip 19 for installation in the burner 11, the burner tip 19 being connected to the surface OF and the surface OF facing the combustion chamber BR and to the air forming the air channel 20. Having a channel structure 21 and a fuel channel structure 32 that is subsequent to the surface OF, the fuel channel structure 32 flowing through the fuel channel 33 when the burner tip 19 is in operation. Extending from the surface area OFB of the burner tip 19 along a first direction parallel to the surface OF, in order to cool the surface area OFB of the burner tip 19 by fuel, and then At least partly, a burner tip (19) forming a fuel channel (33) extending rearward in the surface area (OFB) along a second direction (2R) different from the first direction (1R). 2. The fuel channel 33 according to claim 1, wherein the fuel channel 33 extends into the burner tip 19 starting from its course along a first direction 1R and then at least one further direction change, eg Burner tip (19), for example, which opens into the surface (OF) via a deflection of 70 ° to 110 °. The burner tip (19) of claim 1 or 2, wherein the first direction (1R) forms an angle of 160 ° to 200 ° with respect to the second direction (1R). The fuel channel 33 according to any one of the preceding claims, wherein the fuel channel 33 has an expanded cross section after its course along the first direction 1R and before opening into the surface OF. Burner tip 19 having region B having. 5. The burner tip as claimed in claim 1, wherein the air channel structure 21 comprises a central air channel 20 leading to a central outlet opening 24 in the burner tip 10. 6. (19). 6. The burner tip (10) according to any one of the preceding claims, wherein the burner tip (10) has an inlet region (EB) and an axis of symmetry (14) extending coaxially with the fuel channel (33) as well as with the air channel (20). Burner tip (19) with an outlet area (AB) offset along the inlet area (EB) along. The burner tip (19) of claim 6, wherein the fuel channel (33) extends radially out of the air channel (20) in the inlet region (EB). 8. Burner tip (19) according to claim 6 or 7, wherein the fuel channel (33) extends into the air channel (20) at least partially radially in the outlet region (AB). The fuel channel 33 and the air channel 20 extend in an interlocking manner so that the surface area OFB of the burner tip BS is additionally air. Burner tip 19, which may be cooled by flow. The burner tip of claim 1, wherein the fuel channel structure 32 has vanes 39 that subdivide the fuel channel 33 into a plurality of sub-channels 34. (19). The fuel channel structure 32 according to any one of the preceding claims, wherein the fuel channel structure 32 of the inlet region EB forms an annular chamber, wherein the fuel channel structure 32 comprises Burner tip (19) formed in a manner extending through the annular chamber after its course along a second direction (2R) and before opening into the surface (OF). 12. The air channel (20) according to any one of the preceding claims, wherein the air channel (20) extends at least partially through the fuel channel (33) and the air channel structure (21) with respect to the surface (OF). Burner tip (19) with a plurality of air channels (20) leading into the combustion chamber (BR) at different exit angles. The burner according to claim 1, wherein the air channel structure 21 and the fuel channel structure 32 form a channel cross section having a cross-sectional shape which is different from a rounded shape, in particular a circular shape. Tip (19). The burner tip (19) according to any one of the preceding claims, wherein the surface (OF) is formed by an open porous wall structure (40) forming a plurality of air channels (20). 15. Burner tip (19) according to any of the preceding claims, wherein the burner tip (19) is made in a stack and in a single piece. Gas turbine, comprising a burner tip (19) according to any of the preceding claims. A method for producing a burner tip (19) according to any of the preceding claims, wherein the burner tip (19) is made in a stack and in a single piece.

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