JP2020506356A - Burner chip having air flow path structure and fuel flow path structure for burner and method for manufacturing the burner chip - Google Patents

Abstract

The invention relates to a burner tip (19) for installation on a burner (11), the burner tip (19) being connected to a surface (OF) facing the combustion chamber (BR) and to a surface (OF). And an air flow path structure (21) defining an air flow path (20), and a fuel flow path structure (21) leading to a surface (OF). A flow path (33) is defined, and the fuel flow path (33) cools a surface area (OFB) of the burner tip (19) by fuel flowing through the fuel flow path (33) during operation of the burner tip (19). To extend in a first direction (1R) parallel to the surface (OF) at a surface region (OFB) of the burner chip (19) and subsequently at least partially within the surface region (OFB). What is the first direction (1R) Consisting extending back to the second direction (2R).

Description

  The present invention relates to a burner chip having an air flow path structure and a fuel flow path structure, preferably for a burner in a gas turbine. Furthermore, a method, preferably an additional method, for producing burner chips is described.

  The burner tip is provided for use in a flow machine, preferably in the hot gas path of a gas turbine. The component furthermore preferably comprises a nickel-based alloy and / or superalloy, especially a nickel-based or cobalt-based superalloy. The alloy may be a precipitation hardened or precipitation hardenable alloy.

  A burner chip of the type described above is known, for example, from US Pat. The burner tip described in US Pat. No. 6,037,097 can be used in gas turbines, for example, which forms the downstream end of a burner lance located in a main flow path for the combustion air. The burner tip has a double wall design, with the outer wall creating a heat shield intended to keep the heat of combustion generated 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 have air flowing through the cavity through an opening for cooling purposes. In the described embodiment, the heat shield must be designed to withstand the thermal stresses caused by combustion occurring in the downstream combustion chamber. Thus, the outer wall of the burner chip represents a factor that limits the useful life of the burner chip.

EP-A-2196733

  The problem addressed by the present invention is to develop a burner chip of the type described above in a manner that results in an improved service life of the component. In particular, the present invention may facilitate improved cooling of the burner tip. Furthermore, the problem addressed by the present invention is to embody a method for producing such types of burner chips.

  Manufacture may be performed, for example, by lost core casting. According to the solution to the above-mentioned problem, it is particularly advantageous to use additive manufacturing (additional manufacturing method) for manufacturing. In this case, the burner chip may preferably be produced in one piece and with a design which is particularly complex and / or optimized with respect to the cooling effect, and the additive manufacturing advantageously creates a large surface, especially for heat transfer. A geometrically complex structure can be realized.

  Additive manufacturing within the meaning of the present application is to be understood as indicating the way in which the material making the component is added to the component during its development. This means that the component evolves in its final form or at least in a form close to its final form. The component material or primary material is preferably in powder form, where the additive manufacturing process means that the material used to manufacture the component is physically consolidated by applying energy. I do.

  Data describing the components (CAD models) is prepared for the selected additive manufacturing process so that the components can be manufactured. To generate instructions for the production plant, the data is converted to component data that is compatible with the manufacturing process, so that the production plant can follow process steps that are suitable for continuous production of components. it can. The data is prepared for this in such a way that in each case geometric data for the layers (slices) of the component to be produced are provided, which is also referred to as slicing.

  Examples of additive manufacturing methods include selective laser sintering (ie, SLS), selective laser melting (ie, SLM), electron beam melting (ie, EBM), laser metal deposition (ie, LMD), or gas dynamic cold spray. Law (that is, GDCS). These methods are particularly suitable for processing metallic materials in the form of powders from which structural components can be produced.

  In the case of SLM, SLS, and EBM, components are manufactured in layers on a powder bed. Therefore, these methods are also called additive manufacturing based on a powder bed. In each case, a layer of powder is produced in the powder bed, which is subsequently locally melted or sintered by an energy source (laser or electron beam) in the area where the components are to be produced. In this way, the component is made of a continuous layer and can be removed from the powder bed after completion.

  For LMD and GDCS, the powder particles are supplied directly to the surface where the material is to be deposited. In the case of LMD, the powder particles are melted at a target point on the surface by a laser beam, thereby creating a slice of the component being manufactured. In the case of GDCS, the powder particles are greatly accelerated, so that the powder particles remain attached to the surface of the component while simultaneously deforming, mainly due to the kinetic energy of the powder particles.

  GDCS and SLS have in common that the powder particles do not completely melt during these processes. This also facilitates the production of porous structures, especially when gaps between particles are maintained. In the case of GDCS, melting occurs at most in the region around the powder particles, which can be melted due to severe deformation of their surface. In the case of SLS, when selecting the sintering temperature, it is important to ensure that the sintering temperature is lower than the melting temperature of the powder particles. On the other hand, in the case of SLM, EBM and LMD, the application of energy is intentionally high enough for the powder particles to completely melt.

  The problem mentioned above is solved by the subject matter of the independent claims. Advantageous embodiments are subject matter of the dependent claims.

  One embodiment of the present invention relates to a burner chip for mounting on a burner, wherein the burner chip has a surface facing a combustion chamber, an air flow path structure connected to the surface and defining an air flow path, and And a fuel flow path structure connected to the surface. The fuel flow path structure defines a fuel flow path that is parallel to the surface for cooling the surface area of the burner tip by fuel flowing through the fuel flow path when the burner tip is in operation. Extending in the surface area of the burner tip in a first direction, and subsequently extending or curving or bending back at least partially in a second direction different from the first direction.

  The "extending back" or curved path of the fuel flow path is such that during operation of the burner tip, for example during use of the gas turbine, the cooling action is particularly effective in the surface area of the burner tip through the fuel. Means that it can be advantageously implemented. This means that the consumption of compressor air, which is valuable for the efficiency of the flow machine, is no longer dependent on cooling the surface or surface area of the burner chip. In addition, this compressor air delivery system can be omitted and the corresponding components can be advantageously simplified.

  In one embodiment, the fuel flow path extends within the surface area with a plurality of turns parallel to the surface. In other words, the fuel flow path preferably turns multiple times parallel to the surface or extends according to its turn.

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

  In one embodiment, the fuel flow path extends from the path to the inside of the burner tip along a first direction. According to this embodiment, the area of the surface remote from the surface (surface area) may also be advantageously cooled during operation of the burner chip. This likewise advantageously affects the service life of the entire structural component.

  In one embodiment, the first direction comprises an angle between 160 ° and 200 °, preferably 180 °, with respect to the second direction. This embodiment allows for a particularly effective recirculation or diversion of the fuel flow path, as described above.

  The term "surface area" preferably refers to the structural area of the burner tip close to the surface described above.

  In one embodiment, the fuel flow path is surfaced via at least one further change of direction, for example, via a bend between 70 ° and 110 °, afterwards, ie after turning inward of the burner tip. Open to This embodiment allows for efficient cooling when the burner tip is used, while at the same time enabling an advantageous design of the burner tip, because of the efficient use of fuel when the burner tip is used. This is because, simultaneously with the cooling, a corresponding preheating of the fuel fed to the combustion chamber is possible.

  In one embodiment, the fuel flow path follows its path along the first direction, advantageously before the opening to the surface, an area with an enlarged cross section, in particular an interaction space or collection space. Having. According to this embodiment, the transfer of heat from the surface area to the fuel located in the collecting space or to the fuel flowing through the collecting space during the operation of the burner tip can be particularly advantageously promoted. In particular, the enlarged cross section means that the enlarged volume is available for interaction or for the above-mentioned heat transfer, and as a result (acting on the surface during operation of the burner tip Heat capacity (to absorb the heat generated) can be effectively increased.

  In one embodiment, the air passage structure comprises a central air passage leading to a central outlet opening in the burner tip. In particular, the air flow path structure may represent or define a central air flow path as described above.

  In one embodiment, the burner tip has an inlet area. Both the air flow path and the fuel flow path preferably extend coaxially in the inlet area. In other words, the air channel structure and the fuel channel structure are designed to correspond.

  In one embodiment, the fuel flow path extends in a radially outer inlet region of the air flow path. In other words, the fuel channel structure and the air channel structure may be appropriately configured.

  In one embodiment, the burner tip has an outlet area which is preferably arranged offset (axially) along the axis of symmetry. From the outlet region preferably both air and fuel flows can emerge, the outlet region advantageously comprising a surface or a surface region as described above.

  In one embodiment, the fuel flow path extends at least partially radially within the outlet area within the air flow path.

  In one embodiment, the fuel flow path and the air flow path extend or interweave in an interlocking or intertwined manner, whereby the surface area of the burner tip can be additionally advantageously cooled by the air flow. And-it can also be cooled by a fuel flow. The fuel flow path and the air flow path preferably extend without fluid communication with each other. Alternatively, the air flow path and the fuel flow path may be at least partially fluidly connected to each other.

  In one embodiment, the burner tip is designed, at least in large part, to be rotationally symmetric about the axis of symmetry described above.

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

  In one embodiment, preferably in the outlet region, the fuel flow path structure has vanes that subdivide the fuel flow path-at least in sections-into a plurality of sub-flow paths. In this way, the cooling effect during operation of the burner chip can likewise be advantageously optimized by improved heat transfer. The vanes described above-as well as other parts of the fuel flow path structure or burner tip-may take on any form achievable under certain circumstances exclusively by additive manufacturing techniques.

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

  In one embodiment, the fuel flow path structure is formed such that the fuel flow path extends through the annular chamber behind the path of the fuel flow path in the second direction and shortly before the fuel flow path opens to the surface. ing.

  In one embodiment, the fuel flow path structure in the outlet region has a plurality of fuel flow paths leading to the combustion chamber through the surface or opening into the aforementioned surface. Through this embodiment, an improved and / or more uniform cooling of the surface can advantageously be achieved.

  In one embodiment, the air flow path extends at least partially through the fuel flow path, or vice versa, and the fuel flow path extends at least partially through the air flow path. This embodiment makes it possible to achieve a particularly compact and effective design of the burner tip.

  In one embodiment, the air flow path structure has a plurality of air flow paths, the plurality of air flow paths opening at the surface at different exit angles, e.g., relative to the surface or surface normal, i.e., the combustion chamber. Is connected to Through this embodiment, efficient surface cooling or surface film cooling can be particularly advantageously achieved.

  In one embodiment, the air flow path structure and / or the fuel flow path structure define a flow path cross-section having a cross-sectional shape different from a round shape, especially a circular shape, for example, an elliptical or star-shaped cross-section. Through this embodiment, the heat transfer from the operating surface of the burner tip to the fuel or air flow can advantageously be further improved and / or improved due to the enlarged cross-sectional area compared to the circular cross-section.

  In one embodiment, the surface is formed by an open, porous wall, i.e., a wall structure of a burner tip whose perforations define a plurality of air flow paths. Thus, according to this embodiment, it is possible for the cooling air to flow particularly uniformly through the surface area, for example to provide effective cooling in the area of the burner tip.

  In one embodiment, the burner chips are additionally or produced by an additive manufacturing process.

  In one embodiment, the burner chip is manufactured in one piece, ie in one piece.

  A further aspect of the invention relates to a flow machine, for example a gas turbine, comprising a burner tip as described above.

  A further aspect of the invention relates to a method for manufacturing a burner chip, the burner chip being, inter alia, additionally and / or integrally manufactured or manufacturable.

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

  Further details of the invention are described below with the aid of the drawings.

1 is a schematic cross-sectional view of a burner to which a burner tip of an exemplary embodiment according to the present invention is fitted. 1 is a schematic sectional view of a burner tip according to an embodiment of the present invention. It is a schematic sectional drawing of a part of burner tip based on an embodiment of the present invention. FIG. 4 is a schematic sectional view of a burner tip according to a further embodiment of the present invention. FIG. 4 is a schematic sectional view of a part of a burner tip according to a further embodiment of the present invention. 1 is a schematic sectional view of an exemplary embodiment of the method according to the invention.

  In the exemplary embodiments and figures, identical elements or elements having the same effect are each provided with the same reference signs. The depicted elements and their proportions should not, in principle, be construed as to scale; instead, the individual elements may be disproportionately thick for improved illustration and / or better understanding. Or it may be large.

  FIG. 1 shows a burner 11, which has a jacket 12 in which a main channel 13 for air is formed. The jacket 12 is configured symmetrically about a longitudinal axis and / or an axis of symmetry 14 and has a burner lance 15 in the center of the main channel 13. The burner lance 15 is fixed in the main flow path 13 using a web 16. Further, a guide vane 17 extends between the burner lance 15 and the jacket 12, thereby swirling the air around the axis of symmetry 14 as can be inferred from the air arrow 18 shown.

  The burner lance 15 has a burner tip 19 at a downstream end. The burner tip is supplied with air through a central air flow path 20 and has an annular flow path arranged around the air flow path 20. Fuel 23 is supplied via the passage 22.

  Fuel 23 may be in the form of a gas or a liquid. The fuel may be a gas or fluid containing natural gas, hydrogen or another fuel, among others.

  Air (see airflow or airflow path 20) and fuel 23 are discharged through openings in the burner tip, not shown in more detail, thereby mixing with the airflow from main flow path 13. During this process, the air 21 conventionally cools the burner tip 19 (see below). The burner 11 follows the functional principle of a pilot burner. The burner can, for example, fit into a combustion chamber BR of a gas turbine, where the combustion chamber BR creates a peripheral area 30 of the burner tip 19.

  FIG. 2 shows a schematic sectional view of the 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.

  The burner tip 19 has an entrance area EB. Furthermore, the burner tip 19 has an outlet area AB. The exit area AB is attached to the entrance area EB along the axis of symmetry 14 or is arranged axially offset with respect to the entrance area EB.

  FIG. 2 further illustrates a central air flow path 20 extending along the axis of symmetry 14. The air passage 20 leads to an outlet opening 24 of the burner tip 19. During operation, this air flow path can accommodate additional burner lances (see below). For example, when used in a gas turbine, during operation of the burner tip 19, the burner tip 19 in the air flow path 20 contains air, in particular compressor air, which in the inlet area EB has an air flow The air flows through the air passage 20 so as to enter the passage 20 and leave the air passage again at the outlet area AB. The air passage 20 is defined by an air passage structure 21. The flow of air in the air flow path 20 during operation of the burner chip 19 is indicated by a dotted arrow in FIG.

  The burner chip 19 further has a fuel flow path structure 32. The fuel passage structure 32 defines a fuel passage 33.

  The flow of fuel in the fuel flow path 33 during operation of the burner chip 19 is indicated by a solid arrow in FIG.

  The fuel flow path 33 is arranged radially outward of the air flow path 20, so that when the burner tip 19 is operated, the fuel 23 is moved radially outward of the illustrated air flow (along the air flow direction). I can guide you.

  The fuel passage structure 32 may include or define an outer wall 28 of the burner tip 19.

  The fuel flow path structure 32 may include or define the inner wall 29 of the burner tip 19.

  The burner tip 19 or the air channel structure 21 is preferably configured in such a way that the air channel 20 tapers from the inlet area EB to the outlet area AB. Following the corresponding conical or tapered path, the air flow path structure 21 again defines an air flow path 20 parallel to the axis of symmetry 14.

  In the drawings, especially FIGS. 2 and 4, no further components are shown in the central air flow path 20 for ease of reference. During use of the burner tip 19, for example during operation of the corresponding gas turbine showing the burner tip (not explicitly identified), further components, for example further igniters and / or oil lances, are advantageous in this central region of the burner tip 19. Placed in The above-mentioned components are crucial for the function of the burner 11 and preferably in such a way as to create voids which provide an effective cooling action of the above-mentioned components and / or the burner chip during operation of the burner chip, At the same time, seal the central air flow path.

  As further seen in FIG. 2, the outer wall is likewise tapered in the outlet area AB, ie extends towards the centrally located axis of symmetry 14. In the outlet area AB, the fuel flow channel structure 32 is configured in such a way that the fuel flow channel 33 initially extends parallel to the outer surface OF of the burner tip 19, ie parallel to the surface OF. In particular, during operation of the burner tip 19, the flow of fuel proceeds in a first direction 1R parallel to the surface OF.

  In this case, the surface area having the surface OF is identified using the reference symbol OFB. More precisely, this surface region OFB should be effectively cooled, preferably in the outlet region AB of the burner tip 19 by the fuel 23 guided through the fuel flow channel structure 32 during operation of the burner tip 19. is there.

  When the fuel (see arrows shown in fuel flow path 33) has traveled to a certain length in a first direction parallel to surface OF, the fuel flow path is reduced by the geometry of fuel flow path structure 32. 2 so that the fuel flow path extends back, that is, at least partially deflects in a direction opposite to the first direction, and subsequently the surface area OFB of the burner tip 19 Leave.

  In other words, through the diversion of the fuel flow path in the surface area OFB, this surface area can be efficiently cooled by the fuel during the operation of the burner tip 19, since the fuel is initially Guided near the surface and subsequently turned, then-possibly guided by itself-it is possible to feed the combustion chamber BR at a plurality of provided fuel outlets (not explicitly shown in the figure). (See FIG. 3). Therefore, the path of the fuel flow path 33 or the geometric shape of the fuel flow path structure 32 may correspond to the design of a so-called “Klein bottle” or may have a common feature.

  The first direction may at least partially or partially indicate a direction along the axis of symmetry (in the flow direction) or along a corresponding main flow direction. The second direction preferably means a direction different from the first direction, exactly the opposite direction. The fuel flow path 33 preferably extends from the first direction to the second direction in a manner that the fuel flow path initially extends inside the burner tip or the corresponding surface area OFB after a path parallel to the first direction. Turned in the direction. In this way, the structure below the surface area can be effectively cooled.

  The second direction may likewise represent a direction parallel to the surface but preferably opposite the main flow direction. The second direction may further or alternatively be inclined at 90 ° or another angle with respect to the first direction.

  The burner tip 19 may be configured to be rotationally symmetric or nearly rotationally symmetric with respect to its axis of symmetry 14. The second direction may correspondingly extend, for example, in the circumferential direction of the burner tip 19.

  In the circumferential direction (not explicitly shown in the drawing), the burner tip 19 may show a plurality of fuel passages 33 so as to correspond in the outlet area AB, and the fuel passages are, for example, equally spaced in the circumferential direction. To the combustion chamber BR over the surface OF (see FIG. 3). Accordingly, the position of the fuel outlet created by the outlet of the opening of the fuel passage 33 in the surface OF may correspond to the conventional design of the burner tip.

  The cooling effect of the surface area OFB is customarily used for cooling, for example via the above-mentioned turning or returning part at an angle of about 160 to 220 °, preferably about 180 °. Advantageously improved with a somewhat cooler fuel compared to compressor air. In other words, it is no longer necessary to obtain the compressor air to cool the outer surfaces of the components, but instead (from the compressor section of the gas turbine (not explicitly shown) 400 Much cooler combustion gases (of about 50 ° C. instead of ° C.) can be guided just below the component surface for cooling in the surface area OFB.

  After the portion extending back, the fuel flow path 33 preferably bends further, for example from 70 to 110 °, so that the fuel flow path 33 can open at the surface OF, ie of the combustion chamber BR. In the direction away from the surface OF. In other words, fuel is retained or collected in the surface area OFB by the geometry of the fuel flow path structure 32 for improved cooling, and subsequently, at a predetermined exit angle, again in the combustion chamber BR Can be released and burned.

  The above-mentioned burner chip 19 is manufactured by an additive manufacturing process, preferably by a selective laser melting method (SLM) or an electron beam melting method (EBM). In particular, additive manufacturing allows the manufacture of components with integrated functions. In particular, the burner chip 19 can be manufactured in one piece with its complex channel structure as described above, without the heat shield conventionally required by additional means.

  Since the burner tip 19 only requires the guidance of a single fluid for cooling purposes, under certain circumstances advantageously fewer connections are required, thereby simplifying the manufacture and function of the components. Can be

  Region B is further illustrated in FIG. 2, in which the fuel flow path 33 has a larger cross section. This embodiment advantageously allows a larger amount of fuel 23 to be "collected" in region B to provide effective cooling.

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

  The arrows shown in FIG. 3 also indicate the path of the fuel flow path 33 or the fuel 23. In particular, a plurality of fuel flow paths indicated by arrows, particularly a plurality of fuel flow paths distributed over the outer periphery of the burner tip 19, are shown. These fuel flow paths are preferably provided, but in FIGS. 2 and 4, can not see. In other words, the fuel flow path 33 is divided by the one or more vanes 39 into a plurality of individual fuel sub-flow paths, preferably in the circumferential direction. The plurality of fuel channels, or sub-channels identified using reference numeral 34, are preferably circumferentially spaced from one another (by vanes 39).

  The sub-channels 34 are combined to extend radially inward, preferably towards a single fuel channel 33 of the burner tip 19-as shown in FIG. In this way, during operation of the burner tip 19, the heat transfer from the structure of the burner tip to the flow of fuel conducted through the fuel flow path 33 and thus the cooling of the burner tip can be further advantageously improved.

  The above-mentioned vane geometries, inter alia, cannot be achieved using conventional manufacturing methods, and are therefore preferably additionally and preferably integrally in accordance with the above disclosure, such as selective laser melting It is manufactured by the method.

  As an example, a fuel passage 34 or opening having a rectangular cross section is shown in FIG. Still alternatively, other cross-sectional shapes, such as elliptical or star-shaped cross-sections, can be used to achieve an improved cooling effect due to the increased surface area and correspondingly to an improved heat exchange during operation of the burner tip 19. Can also be used to

  The fuel flow channel structure 32 may further form a (complexly formed) annular chamber, in particular according to an embodiment with rotational symmetry of the burner tip 19 around the axis of symmetry of the burner tip 19. The fuel flow channel structure 32 further preferably extends the outlet channel AB through the annular chamber after its path in the second direction 2R and shortly before the opening outlet to the surface OF, in the second direction 2R. In this manner, it is formed (see the arrow indicating fuel 23 in FIG. 2).

  In particular, the path of the arrow in FIG. 3 indicates the fuel flow path resulting from the geometry of the fuel flow path structure 32 to enable effective cooling of the surface area OFB of the burner chip 19 during operation of the burner chip 19. 33 shows the change of direction of the fuel in 33.

  FIG. 4 shows a sectional view (longitudinal section) of an alternative embodiment of the burner tip according to the invention. Unlike FIG. 2, the fuel flow path 33 extends at least partially radially in the area of the air flow path 20 through the outlet area AB. Furthermore, the fuel flow path 33 and the air flow path 20 extend at least partially in an interlocking manner in order to additionally cool the surface area OFB of the burner tip 19 by an air flow, thereby being further improved. A cooling effect is obtained.

  The air flow path structure 21 has an opening 25 in a side wall that fluidly connects the (center) air flow path 20 to an annular space or a plurality of individual air flow paths annularly surrounding the air flow path in the inlet area EB. Have.

  The individual air passages 20 described above preferably traverse at least partially the path of the fuel passage structure 32 according to the air passage structure 21 of this embodiment.

  The above-described air flow path based on the depiction in FIG. 4 further leads into the combustion chamber BR at a different exit angle with respect to the surface OF or the corresponding surface normal, for example between 60 ° and 120 °. The aforementioned exit angle of the fuel flow path 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 °), the film cooling at the surface OF of the burner tip 19 may become stronger or weaker.

  Further, the air flow path structure 21 and the fuel flow path structure 32 can define a flow path cross section having a cross section different from a circle, particularly a circular shape. In particular, the above-mentioned channel structure may be star-shaped and / or elliptical. All of these geometries can be manufactured using the described additive manufacturing methods, thus making use of the inventive advantages of the present invention.

  In a further embodiment, the surface OF may be formed by an open porous wall structure (not explicitly shown) defining a plurality of air channels 20. This geometry may likewise be advantageously achieved by additive manufacturing techniques and may contribute to improved cooling of the burner chip during operation.

  FIG. 5 shows a cross-sectional view (cross-sectional view perpendicular to the axis of symmetry) of the burner chip according to the embodiment of the burner chip shown in FIG. 4-similar to the depiction in FIG. Unlike the depiction of FIG. 3, in FIG. 5 (in addition to fuel cooling) (see FIG. 4) an additional circular air opening 35 is provided which provides a cooling effect for the burner tip 19 by air cooling. You can see that. The dashed arrows are intended to show the air flow out of the opening 35, while the solid arrows-similar to the depiction in Fig. 3-indicate the redirection of the fuel flow according to the invention. Is shown.

  FIG. 6 shows in detail how the component 19 according to FIG. 2 or 4 can be produced by laser melting using a laser beam 37. Details of the powder bed 36 from which a part of the air passage structure 21 and / or the fuel passage structure 32 is manufactured are shown. The fuel flow path structure 32 is, for example, similar in design to the depiction of FIG. 2 and preferably has, inter alia, the vanes described above (not shown in FIG. 6), as well as the fuel of the invention. It defines a turning portion of the flow path.

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

  The invention is not limited to the exemplary embodiments described by way of example embodiments, but encompasses each novel feature and combination of these features. Even though this feature or the combination itself is not explicitly set forth in the claims or the exemplary embodiments, this includes, inter alia, each combination of features in the claims.

Reference Signs List 11 burner 12 jacket 13 main flow path 14 symmetry axis 15 burner lance 16 web 17 guide vane 19 burner chip 20 air flow path 21 air flow path structure 22 annular flow path 23 fuel 24 outlet opening 25 opening 28 outer wall 29 inner wall 32 fuel Flow path structure 33 Fuel flow path 34 Sub flow path 35 Opening 36 Powder bed 37 Laser beam 39 Vane 40 Open type porous wall structure R1 First direction R2 Second direction

Claims (17)

A burner tip (19) for installation on the burner (11),
The burner chip (19) has a surface (OF) facing the combustion chamber (BR), an air flow path structure (21) connected to the surface (OF) and defining an air flow path (20); (OF) leading to a fuel flow path structure (32).
The fuel flow path structure (32) defines a fuel flow path (33);
The fuel flow path (33) is provided for cooling a surface area (OFB) of the burner tip (19) by fuel flowing through the fuel flow path (33) when the burner tip (19) is operated. In the surface area (OFB) of the burner chip (19), it extends in a first direction (1R) parallel to the surface (OF) and subsequently at least partially in the surface area (OFB), A burner tip (19) characterized by extending back in a second direction (2R) different from the first direction (1R).   The fuel flow path (33) extends from the path, along the first direction (1R), inside the burner tip (19), and subsequently provides at least one further diversion. The burner tip (19) according to claim 1, characterized in that the burner tip (19) opens into the surface (OF) via a bend of between 70 ° and 110 °, for example.   The burner tip (19) according to claim 1 or 2, wherein the first direction (1R) has an angle of 160 ° or more and 200 ° or less with respect to the second direction (2R). ).   The fuel flow path (33) has an area (B) with an enlarged cross section behind its path along the first direction (1R) and just before the opening to the surface (OF). Burner chip (19) according to any of the preceding claims, characterized in that:   The air channel structure (21) comprises a central air channel (20) leading to a central outlet opening (24) in the burner tip (19). Burner tip (19) according to one of the preceding claims.   The burner tip (19) includes an inlet area (EB) in which both the air flow path (20) and the fuel flow path (33) extend coaxially, and an inlet area (EB) along a symmetry axis (14). 6. The burner tip (19) according to any one of the preceding claims, characterized in that the burner tip (19) has an outlet area (AB) offset from the burner tip (AB).   Burner tip (19) according to claim 6, characterized in that the fuel channel (33) extends into the inlet area (EB) radially outside the air channel (20).   8. The fuel flow path according to claim 6, wherein the fuel flow path extends at least partially radially into the outlet area within the air flow path. 9. Burner chip (19).   The fuel flow path (33) and the air flow path (20) extend in an interlocking manner so that the surface area (OFB) of the burner chip (BS) can be additionally cooled by an air flow. Burner chip (19) according to any one of the preceding claims, characterized in that:   The fuel passage structure (32) has a vane (39) that subdivides the fuel passage (33) into a plurality of sub-flow passages (34). Burner tip (19) according to one of the preceding claims. The fuel flow path structure (32) defines an annular chamber in the inlet area (EB);
The fuel flow path structure (32) includes:
The fuel flow path (33) extends through an annular chamber behind the path in the second direction (2R) and shortly before the fuel flow path (33) opens into the surface (OF). Burner chip (19) according to any of the preceding claims, characterized in that: The air flow path (20) extends at least partially through the fuel flow path (33);
The air channel structure (21) comprises a plurality of air channels (20) leading to the combustion chamber (BR) at different exit angles with respect to the surface (OF). Item 12. The burner chip (19) according to any one of items 11 to 19.   13. The air flow path structure (21) and the fuel flow path structure (32) define a flow path cross-section having a cross-section that is different from a round shape, in particular a circular shape. Burner chip (19) according to any one of the preceding claims.   The surface (OF) is formed by an open porous wall structure (40) defining a plurality of the air flow paths (20). Burner chip (19).   The burner tip (19) according to any of the preceding claims, wherein the burner tip (19) is additionally and integrally manufactured.   A gas turbine comprising a burner chip (19) according to any one of the preceding claims.   A method for manufacturing a burner chip (19) according to any of the preceding claims, wherein the burner chip (19) is additionally and integrally manufactured.

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