Irradiation Strategies for Structures for Coolable Additive Manufacturing

Abstract

A method for providing manufacturing instructions for powder bed-based additive manufacturing of a component (10) is described. The method includes: providing a first irradiation vector (V1) for a layer (n) to be additively manufactured, which, in the case of corresponding irradiation by an energy beam (5), in particular a laser or an electron beam, causes a porous structure of the layer, and providing a first irradiation vector (V1) for a layer (n + 1) to be additively manufactured following the layer (n), such that the paths (11) of the porous structures (12) of the layer (n) and the following layer (n + 1) at least partially overlap in order to achieve a through-flow of the manufactured component along the build direction (Z). A corresponding additive manufacturing method, a correspondingly manufactured component, and a computer program or computer program product are also proposed.

Description

Field of the Invention

[0001] The present invention relates to a method for providing manufacturing instructions, in particular instructions for selective irradiation in additive manufacturing, and to a corresponding additive manufacturing method. The method for providing manufacturing instructions may relate to a computer-aided manufacturing method (CAM: "Computer-Aided-Manufacturing").

[0002] Furthermore, an additively manufactured or additively manufacturable component and a computer program or computer program product are also described. Background Art

[0003] The component is preferably provided for use in the hot gas path of a gas turbine, such as a stationary gas turbine. Particularly preferably, the component structure relates to a component of a combustion chamber or a resonator component, such as a Helmholtz resonator or a part thereof. Alternatively, the component may relate to another coolable or partially porous component, for example a component used in the automotive or aerospace fields.

[0004] Preferably, the component is a component to be cooled, for example, which can be cooled by fluid cooling. For this purpose, the component preferably has a customized penetrability or permeability for a corresponding cooling fluid, such as cooling air.

[0005] Modern gas turbines are the subject of continuous improvement in order to increase the efficiency of the gas turbines. However, in addition, this leads to increasingly high temperatures in the hot gas path. In particular in the first stage, the metallic materials for the rotor blades are continuously improved in terms of the strength, creep load and thermo-mechanical fatigue of the metallic materials at high temperatures.

[0006] Generative or additive production is becoming increasingly interesting for the serial production of the turbine components mentioned above due to its disruptive potential for industry.

[0007] Additive manufacturing methods include, for example, selective laser melting (SLM) or laser sintering (SLS) or electron beam melting (EBM) as powder bed methods. Other additive methods are, for example, "Directed Energy Deposition (DED)" methods, in particular laser cladding, electron beam welding or plasma powder welding, wire welding, metal powder injection molding, the so-called "sheet lamination" method, or thermal spraying methods (VPS LPPS, GDCS).

[0008] The method for selective laser melting is known, for example, from EP 2 601 006 B1.

[0009] In addition, additive manufacturing methods (English: “additive manufacturing”) have proven to be particularly advantageous for complex or finely designed components, such as labyrinth structures, cooling structures, and / or lightweight structures. In particular, additive manufacturing is advantageous due to a particularly short process step chain, since the manufacturing steps or production steps of a component can be carried out largely based on the selection of a corresponding CAD file and corresponding production parameters and / or irradiation parameters.

[0010] The CAD file or corresponding computer program or computer program product can be provided or included, for example, as a (volatile or non-volatile) storage medium, such as a memory card, USB stick, CD-ROM, or DVD, or also in the form of a file that can be downloaded from a server and / or in a network. The provision can also be carried out, for example, in a wireless communication network by transmitting a corresponding file with the computer program. The computer program (product) can generally contain program code, machine code, or numerical control instructions, such as G-code and / or other executable program instructions.

[0011] Manufacturing gas turbine blades by means of the described powder bed-based method (English “LPBF” stands for “Laser Powder Bed Fusion”) can advantageously enable the implementation of new geometries, concepts, solutions, and / or designs, which can reduce manufacturing costs or construction and production times, optimize the manufacturing process, and, for example, improve the thermo-mechanical design or durability of the component.

[0012] Blade components manufactured in a traditional way, for example by casting techniques, are significantly inferior to additive manufacturing processes, for example in terms of their design freedom, as well as with regard to the required production times and the high costs associated with production times and production technology expenditures.

[0013] In particular, powder bed-based methods such as selective laser melting or electron beam melting also offer the feasibility of specifically manufacturing porous structures by parameter setting or parameter variation. As is well known, in the case of regional (selective) irradiation or exposure of a powder layer by an energy beam such as a laser or electron beam, the so-called “hatching distance” (English: “hatching distance”) is an important parameter that particularly affects the structure or porosity obtained for the layer or component.

[0014] Technically, setting a specific porosity in the material also results in a controllable permeability, for example, which can be used for particularly effective cooling of the resulting structure or component. The penetrability, flow-through property, or permeability of the cooling fluid can also vary depending on the construction direction and the flow-through direction of the structure. The permeability is especially strongly parameter-dependent. In addition to the scan spacing, the irradiation power, scan speed, beam focus, and layer thickness can all, in certain cases, have an impact on the resulting structure or its porosity. The laser power is especially strongly correlated with the melt pool depth, which is a measure of how far the initially liquid and then solidified structure extends downward into the powder bed during powder consolidation.

[0015] A change in the scan spacing has a decisive influence on the flow-through property or porosity of the structure along its construction direction, usually the vertical line (z-direction). Conversely, if the energy input is reduced, for example, a flat melt pool is formed, which results in a relatively large lateral porosity.

[0016] An additive manufacturing method and a corresponding system including a circular irradiation path are known, for example, from EP 3406 370A1.

[0017] A method for manufacturing a three-dimensional object and a corresponding component with specifically tailored porosity are known, for example, from WO2014 / 202352 A1.

[0018] In particular, in gas turbine components in the hot gas path that are subject to strong mechanical and thermal loads, additively manufactured porous structures can be used to specifically create a favorable permeability, thereby achieving a controllable and significantly more efficient cooling effect. Summary of the Invention

[0019] Therefore, the object of the present invention is to expand the field of use of additive production technologies to the described components, or to use the materials or manufacturing features of additive technologies for the structural advantages and design optimization of the components. Thereby, not only can the traditionally known advantages of additive technologies be advantageously utilized. Contrary to the common view in the art, according to which additively realized structures are weaker and not similar to components manufactured conventionally, it is now even possible to reproducibly achieve improved structures.

[0020] The above object is achieved by the subject matter of the embodiments according to the present invention. Advantageous design solutions are the subject matter of the embodiments according to the present invention.

[0021] One aspect of the present invention relates to a method for providing manufacturing instructions for powder bed-based additive manufacturing of a component. Preferably, the manufacturing instructions relate to the process preparation of the actual manufacturing process, especially the so-called "Computer-Aided-Manufacturing" (CAM) devices.

[0022] The method includes providing a first irradiation vector for a layer to be additively manufactured, which, in the case of corresponding irradiation by an energy beam, in particular a laser or electron beam, causes a (at least partially) porous structure of the layer along the corresponding vector or path. The mentioned irradiation vectors are preferably selected to be the same or of the same type and can form a first irradiation pattern.

[0023] Preferably, the mentioned irradiation vectors are so-called scanning vectors (Schraffurvektoren). Alternatively, the irradiation vectors can also relate to contour vectors.

[0024] The mentioned layer to be additively manufactured preferably relates to a raw material layer previously prepared from powder in accordance with standards, and the selective irradiation of the raw material layer results in forming part of the cross-section of the component.

[0025] The method further includes: providing the mentioned or the same type of first irradiation vector for the (next) layer to be additively manufactured following this layer, such that the path of the porous structure of this layer and the path of the porous structure of the following layer at least partially or slightly overlap in the layer plane, in order to achieve the flow-through of the (completed) manufactured component along its construction direction or at an angle to its construction direction.

[0026] The mentioned following (first-mentioned layer) or next layer preferably relates to the immediately following layer.

[0027] The mentioned path is to represent the orientation of the irradiation vector to establish a porous structure in at least some regions of the component. In other words, by correspondingly selecting the irradiation vector or path, the component can be traversed by a porous structure profile.

[0028] With the described device, a permeable or flow-through component structure can be advantageously manufactured along and also inclined to the construction direction of the component (see the vertical Z direction). During process preparation, component characteristics can already be determined in this way: the component characteristics allow subsequent flow-through of the component for efficient cooling during its normal operation. The degree of freedom obtained in this way can decisively improve the cooling effect of the entire component and can also expand its thermal application range. In the case of turbine components, this also allows the use of higher combustion temperatures and higher energy efficiency of the entire fluid machine.

[0029] In one design, the method is or includes a CAM method.

[0030] In one design, the irradiation vector of this layer and the irradiation vector of the following layer overlap in the layer plane by an amount less than the measure of the lateral extension of the path. Thereby, a sufficient permeability for the cooling effect of paths that are diagonally or slightly inclined in the component can be particularly advantageously achieved.

[0031] In one design, the irradiation vector of this layer and the irradiation vector of the following layer are completely overlapped in the layer plane. Through this design, it is possible to advantageously achieve as steep a parallel extension as possible of the fluid path along the construction direction of the component, for example its longitudinal direction.

[0032] In one design, the first irradiation vector of the following layer is preferably linearly or translationally offset relative to the first irradiation vector of the (previous) layer.

[0033] On the premise that the provision of vectors or other manufacturing parameters has been prepared for the process, the corresponding first irradiation vector of this layer can also be offset relative to the following layer. This offset can be adapted and customized individually according to the design requirements of the component and the thermal load situation, and advantageously allows even customized cooling of individual regions of the component.

[0034] In one design, the first irradiation vector of the following layer is twisted or rotated relative to the first irradiation vector of the (previous) layer. This is particularly purposeful and / or advantageous in the case of rotationally symmetric or columnar components when selecting a curved or circular irradiation profile.

[0035] In one design, the irradiation power or irradiation power density of the first irradiation vector - for example, relative to a standard parameter set for forming a solid material structure - is reduced. Through this measure, it is possible to particularly advantageously cause, generate or induce a porous structure of this layer or the corresponding component cross-section.

[0036] In one design, the irradiation speed of the first irradiation vector is increased relative to the standard parameters for forming a solid material structure. Through this measure, it is also possible to particularly advantageously cause a porous structure of this layer of the component or the corresponding component cross-section.

[0037] In one design, a second irradiation vector is provided for the layer to be additively manufactured and / or in the following layer to be additively manufactured, and the second irradiation vector causes a dense structure in the corresponding layer or the corresponding component region. The dense structure should preferably represent a substantially pore-free structure, especially solid material. The component is advantageously provided with sufficient mechanical stability or correspondingly exactly non-permeable structural properties through this design.

[0038] In one design, the first irradiation vector is a plurality of parallel irradiation vectors for each layer of the component, and the irradiation vectors should be exactly equipped with porous characteristics according to the design requirements.

[0039] In one design, the first irradiation vector is a plurality of radially or radially symmetrically extending irradiation vectors of the corresponding component layer, and the first irradiation vector of the following layer is particularly twisted or rotated relative to the first irradiation vector of this layer.

[0040] In one design, additional irradiation vectors are provided and / or applied, the additional irradiation vectors being a plurality of in particular substantially concentric irradiation vectors for a corresponding layer of the component, and wherein the additional irradiation vectors cause at least a partially porous structure. With respect to the first irradiation vector, for the additional irradiation vectors, additional irradiation parameters can preferably be selected, but the additional irradiation parameters still equally meet the requirements suitable for forming a porous structure. Through this design, the structure of the component can be further varied within a specific range and, correspondingly, adapted to the corresponding thermo-mechanical loading conditions.

[0041] In one design, additional irradiation vectors are provided for the layer and the following layer, wherein the additional irradiation vectors of the following layer are radially offset with respect to the additional irradiation vectors of the layer. Through this design, the degree of freedom of the structural deformation scheme or its permeability characteristics of the component can also be advantageously increased.

[0042] Another aspect of the invention relates to a method for additive manufacturing of a component by selective laser melting, selective laser sintering or electron beam melting.

[0043] In one design, the manufacturing instructions for the layer to be additively manufactured are determined in a first component region of the component, and wherein different additional manufacturing instructions are defined in a second component region different from the first component region.

[0044] Another aspect of the invention relates to a component which is manufacturable or has been manufactured as described above, wherein the component is a component to be cooled in the hot gas path of a fluid machine, such as a turbine blade, a thermal shielding component of a combustion chamber and / or a resonator component.

[0045] Another aspect of the invention relates to a computer program or computer program product comprising the manufacturing instructions as described above, wherein, when the corresponding program is executed by a computer, for example for controlling and / or programming a build processor and / or an irradiation device of an additive manufacturing device, the computer program product causes the mechanism to manufacture the component as described above.

[0046] Currently, the designs, features and / or advantages related to the method or computer program product for providing manufacturing instructions can also directly relate to the additive manufacturing method or component, or to an application having such an additive manufacturing method or component, such as a fluid machine, and vice versa.

[0047] When using the expression "and / or" as used herein in a series of two or more elements, the expression "and / or" means that any of the listed elements can be used alone, or any combination of two or more of the listed elements can be used. Description of the Drawings

[0048] Other details of the present invention are described below with reference to the drawings.

[0049] Figure 1 A powder bed-based additive manufacturing method is illustrated by a schematic diagram.

[0050] Figure 2 A schematic perspective view showing the flow direction of the cooling fluid in the component, and the respective layers to be solidified of the component.

[0051] Figure 3 A schematic top view showing the irradiation vectors for the layer to be additively manufactured.

[0052] Figure 4 A schematic top view showing the irradiation vectors for the layer to be additively manufactured that follows.

[0053] Figure 5 On the left - similar to Figure 2 - a schematic side view or cross-sectional view (XZ plane) showing the flow direction in the component. The right part of this illustration shows the layer profile and the offset of the irradiation path.

[0054] Figure 6 Similar to Figure 5 - a schematic side view or cross-sectional view (YZ plane) showing the flow direction in the component.

[0055] Figure 7 A schematic top view showing the radially extending irradiation vectors.

[0056] Figure 8 A schematic top view showing the radially and concentrically extending irradiation vectors.

[0057] Figure 9 Similar to Figure 8 - a schematic top view showing the irradiation vectors for the layer to be additively manufactured.

[0058] Figure 10 A schematic top view showing the irradiation vectors for the layer to be additively manufactured that follows the layer mentioned.

[0059] Figure 11 A schematic perspective view showing a rotationally symmetric component section having a flow path with partial longitudinal and circumferential extensions.

[0060] Figure 12 andFigure 13 And Figure 9 and Figure 10 Similarly show a radial offset of the irradiation direction of the concentric extensions of the layers to be additively manufactured following one another.

[0061] Figure 14 And Figure 11 Similarly show corresponding perspective views of the component sections according to Figure 12 and Figure 13 of the component.

[0062] Figure 15 Show a radial section of the component according to the embodiment shown in Figures 12 to 14 In. Detailed Description

[0063] In the examples and figures, identical or functionally identical elements may be provided with the same reference numerals, respectively. The elements shown and their size relationships to one another should not be considered to be to scale in principle. Rather, for better visibility and / or for better understanding, individual elements may be shown with an overly thick or large size.

[0064] Figure 1 The steps of the additive manufacturing process of the component 10 are shown with reference to the simplified manufacturing device 100.

[0065] The manufacturing device 100 is preferably designed as an LPBF device and is used for additively constructing components or parts from a powder bed, in particular for selective laser melting. In particular, the device 100 may also relate to a device for selective laser sintering or electron beam melting. Correspondingly, the device has a construction platform 1. On the construction platform 1, the component 10 to be additively manufactured is produced layer by layer from the powder bed. The latter is formed by the powder P, which can be distributed layer by layer on the construction platform 1 by means of a coating device 3.

[0066] After each layer L has been coated with the powder P to a certain layer thickness, the selective areas of the layer L are melted and then solidified using an energy beam 5, such as a laser or an electron beam, from the irradiation device 2 according to the preset geometry of the component 10.

[0067] For irradiating the powder layer L with the energy beam 5, the device 100 preferably has an irradiation device 2.

[0068] After each layer L, the construction platform 1 is preferably lowered by an amount corresponding to the layer thickness L (see the downward-pointing arrow in Figure 1 ). The thickness L is usually only between 20 μm and 40 μm, such that the entire process easily requires a number of layers in the thousands to tens of thousands.

[0069] The geometry of the component 10 is typically determined by a CAD file ("Computer-Aided-Design"). After such a file has been read into the manufacturing device 100, the process then first requires, for example, determining a suitable irradiation strategy with the aid of CAM ("Computer-Aided-Manufacturing"), which also results in dividing the component geometry into individual layers. This can be carried out or implemented by means of a corresponding build processor 4 via a computer program.

[0070] The component 10 is preferably a coolable and to-be-cooled component of the hot gas path of a fluid machine, such as a turbine blade, a thermal screen component of a combustion chamber, and / or a resonator component such as a Helmholtz resonator.

[0071] Alternatively, the component 10 can relate to an annular segment, a burner component or burner tip, a frame, a shield, a thermal screen, a nozzle, a seal, a filter, a port or a spray gun, a punch or a swirler, or a corresponding transition piece, insert, or corresponding retrofit piece.

[0072] To implement or process manufacturing instructions (see below) for constructing a component starting from a preset CAD geometry of the component, the build processor 4 or a corresponding circuit mentioned is provided, which can be programmed, for example, with corresponding CAM information or manufacturing instructions and / or can correspondingly cause the irradiation device 2 to construct the component layer by layer according to the manufacturing instructions described below. The build processor circuit 4 preferably serves as an interface between the software preparing the actual construction process and the corresponding hardware of the manufacturing device 100. The build processor can be set up, for example, to execute a computer program with corresponding manufacturing instructions (see computer program product CPP).

[0073] According to the invention, a method for providing manufacturing instructions for powder bed-based additive manufacturing of a component 10 includes providing a first irradiation vector V1 (see the following figure) for the layer n to be additively manufactured, which, in the case of corresponding irradiation by an energy beam 5, causes a porous structure of the layer n. Furthermore, the method also includes providing the first irradiation vector V1 for the layer n + 1 to be additively manufactured following the layer n, such that the paths 11 of the porous structure 12 of the layer n and the paths 11 of the porous structure 12 of the following layer n + 1 overlap at least partially in the layer plane, in order to enable flow-through of the manufactured component along and / or inclined to its construction direction Z.

[0074] Figure 2The three-dimensional view shows a component or component section that can be additively constructed layer by layer. The individual component layers are distinguished by dashed lines. The diagonally or obliquely extending arrows indicated by the reference symbol F are intended to indicate the corresponding flow direction, according to which the component section can be purposefully flowed through by a cooling fluid that is used for cooling in normal operation.

[0075] According to this illustration, the flow direction F extends at least partially in the XZ plane and is slightly inclined to the construction direction Z. In order to ensure such a flow permeability or permeability of the component, the scanning or irradiation strategy according to the invention must already be defined in advance.

[0076] Such functions with porosity or permeability extending diagonally or obliquely to the building direction Z can in particular no longer be achieved by irradiation parameters that are identical or set identically layer by layer, but preferably require a shifting of the irradiation vector with correspondingly selected or varied irradiation parameters.

[0077] In order to realize a porous structure in the described cooling lines or channels, for example, the irradiation power P of the first irradiation vector V1 can be reduced and / or the irradiation speed v of the first irradiation vector V1 can be increased relative to standard parameters for forming a solid material structure. Figure 3 and as shown in the figure below.

[0078] Figure 3 A first illumination vector V1 (vertical) is shown, which causes functional porosity. These are only exemplary grid-like arrangements. Figure 3 , a first illumination vector V1 includes multiple parallel illumination vectors for a given layer n of component 10. Layer n may refer to any layer in the layer construction of the component.

[0079] Furthermore, it is possible to perform additive manufacturing for the layer n to be produced and / or in the subsequent layer n+1 to be produced additively (see below). Figure 4 ) provides a second irradiation vector V2, which causes a dense structure of the corresponding layer, in particular a solid material. Figure 3 Such a dense structure is usually useful for reasons of stability or for the dimensional strength of the component 10 .

[0080] Furthermore, a further third irradiation vector V3 (horizontal) can be arranged in a grid-like or grid-like manner. Said vector V3 can also bring about a porous structure in the component section of the corresponding layer, for example another type of porous structure with porosities of different sizes.

[0081] The illumination according to the first illumination vector V1 and the further illumination vector V3 can, for example, each be a porosity of between 5% and 40%, preferably approximately 20%.

[0082] Figure 4 —— Similar to Figure 3 —— Schematically shows a top view of the component layer n+1 or the corresponding original powder layer following the one shown in Figure 3 . Depending on the setting of the first irradiation vector V1, it is recognized that the irradiation vector has a linear offset with respect to layer n (see Figure 5 ).

[0083] This offset allows for the formation of a permeability profile inclined to the construction direction (also see Figure 5 ) as shown in Figure 2 . Figure 5 In the left part of this illustration, a side view of a component section in the XZ plane is shown, where there is a diagonally extending path 11 in the structure of the component, and the path 11 is to indicate a cooling path or a flow path.

[0084] In Figure 5 the right part of the view, an enlarged view of three successive layers n, n+1, and n+2 is shown. It can be seen that the structural path 11 cured during the additive manufacturing process by the first irradiation vector V1 is offset by a measure d layer by layer in order to produce a diagonal or slanted profile.

[0085] In other words, the proposed scanning strategy is based on moving the irradiation vector along a preferred direction in order to facilitate the formation of a cavity or flow path to be traversed. For example, if the flow occurs at an angle greater than or less than 90° with respect to the XY or layer plane, i.e., at least partially along the Z direction as shown in the example, then the vector V1 in layer n+1 is translated by a magnitude d along the positive X direction or the positive Y direction. Here, the magnitude d determines the desired angle that the flow path should form with respect to the construction direction Z.

[0086] Alternatively to the said arrangement, the offset can also be completely omitted in order to achieve a completely vertical run of the path 11 (not explicitly marked).

[0087] Figure 6 Similar to Figure 5 shows the situation for another lateral direction with respect to the construction direction Z, i.e., the Y direction.

[0088] Again, on the left, a side view of a component section with a diagonally extending path 11 in the structure of the component in the YZ plane is shown, and the path 11 is to indicate traversal.

[0089] In Figure 6 the right part of the view, this situation is again shown in a layer cross-section. Without limiting generality, an offset d similar to the view in Figure 5 is shown here, such that an evenly diagonally inclined run of the path 11 is obtained for the component 10 overall.

[0090] Figure 7 A top view showing a circular manufacturing surface or a circular layer region. The radial direction starts from the central region and is indicated by an arrow and the reference sign R. Along R - currently only exemplary radially symmetrically arranged - a first irradiation vector V1 of a corresponding irradiation pattern is arranged or provided in order to form a porous layer structure. After manufacturing, this again advantageously allows for radial flow-through with the fluid F and corresponding cooling achievable in the component.

[0091] The mentioned first irradiation vector V1 extends uniformly at an angular distance in polar coordinates. Of course, the angular distance can also - different from the illustration - vary between the individual vectors V1.

[0092] Furthermore, a second irradiation vector is also shown - for forming a dense material structure of the layer. The vector V2 represents the remaining layer structure and - for the sake of overview - is shown without the individual irradiation paths.

[0093] Especially in the case of rotationally symmetric components or structures, a scanning vector according to Figure 7 can be provided.

[0094] In addition thereto, in Figure 8 a plurality of further concentrically arranged irradiation vectors V3 are shown, which also cause at least a partially porous structure of the layer. If the component should be correspondingly flowed through and cooled during operation, this is for example in order to also be able to cause a cooling effect in the circumferential direction.

[0095] In Figure 8 the mentioned radially extending irradiation vector V1 is supplemented by concentrically extending tracks or profiles V3, which extend away from each other by a radial distance and can form not only closed profiles but also interrupted profiles. This also applies to the other irradiation vectors described. The penetrability for the cooling fluid F can be achieved for example by omitting layers and reducing the energy introduced therein. For example, open sites allowing a corresponding permeability can also be provided in a targeted manner.

[0096] In contrast, for other applications, if the component 10 or a corresponding component region should be cooled only in the Z direction, for example, non-flow-through "walls" can be provided - for example in a sectoral manner.

[0097] If now an adaptation or offset of the vectors from layer to layer is carried out, similar to the embodiment described above, three-dimensional flow-through can also be achieved. This is shown in the following figures.

[0098] Figure 9 For a given layer n, it is shown that it has already been according to Figure 8The described irradiation pattern, which includes a first irradiation vector V1, a second irradiation vector V2, and an additional third irradiation vector V3.

[0099] Figure 10 The situation is again shown for the preferably tightly following layer n+1. It can be seen that the first irradiation vector V1 of the following layer n+1 is twisted by a small angle Δφ clockwise relative to the first irradiation vector V1 of layer n. Through the design solution of the present invention, the flow-through property and the cooling effect can also be customized in an advantageous manner and decisively improved locally.

[0100] Figure 11 A three-dimensional schematic view of a cylindrical or approximately rotationally symmetric component structure is shown, which can be manufactured according to the Figure 9 and Figure 10 irradiation pattern. Here, the first irradiation vector V1 is twisted or rotationally offset layer by layer, so that the shown path 11 of the component 10 that extends obliquely relative to the construction direction Z can be established. According to the Figure 11 illustration, the twist is shown counterclockwise.

[0101] Figures 12 to 14 Furthermore, it is shown that in addition to the twist of the flow-active path (see V1) in the component 10, an eddy effect (see irradiation vector V3) or an eddy-type flow-through and cooling can also be achieved. For this purpose, concentric tracks can be provided with a radial offset (see Δr) layer by layer, so that a correspondingly improved flow-through and cooling can be given over the entire component. This is shown in particular for layer n+1 in Figure 13 .

[0102] It is also possible to set a radial offset without a polarity offset, and vice versa.

[0103] Figure 14 A three-dimensional schematic view of the component 10 showing the radial deflection and polarity offset of the irradiation vectors V1 and V3 caused by porosity is shown.

[0104] With this scanning or irradiation strategy, for example, lubricant is delivered to the component area or bearing in the Z direction and then evenly transferred to the shaft not only on the circumferential side but also over the length and radius of the bearing.

[0105] Figure 14 The radial section or longitudinal section of the structure in Figure 15 is shown in Figure 12 and Figure 13 , where in particular concentric and longitudinally extending flow paths are set in a manner that appears slightly inclined to the Z direction by means of a radial offset layer by layer (see

[0106] The proposed irradiation strategy allows, in an advantageous manner, the customization of the cooling or heat dissipation characteristics of components with a high heat load in general. Of course, the thermal characteristics can also be adapted and improved only for local or individual areas of the component using the proposed solution.

Claims

1. A method for providing manufacturing instructions for powder bed-based additive manufacturing of a component (10), the method comprising: - providing a first irradiation vector (V1) for a layer (n) to be additively manufactured, which, in the case of corresponding irradiation by an energy beam (5), causes a porous structure of the layer, and - providing the first irradiation vector (V1) for a layer (n + 1) following the layer (n) to be additively manufactured such that a path (11) of the porous structure (12) of the layer (n) and a path (11) of the porous structure (12) of the layer (n + 1) following the layer (n) at least partially overlap in order to achieve throughflow of the manufactured component (10) along a build direction (Z) of the component (10), wherein the first irradiation vector (V1) of the layer (n + 1) following the layer (n) is twisted (φ) relative to the first irradiation vector (V1) of the layer (n), wherein the first irradiation vector (V1) of the layer (n) and the first irradiation vector (V1) of the layer (n + 1) following the layer (n) overlap in the layer plane by an amount less than a measure of the lateral extent of the path (11), and wherein a second irradiation vector (V2) is provided for irradiation in the layer (n) to be additively manufactured and / or in the layer (n + 1) following the layer (n) to be additively manufactured, which second irradiation vector causes a dense structure of the corresponding layer, wherein the first irradiation vector (V1) is a plurality of radially or radially symmetrically extending irradiation vectors for each layer of the component (10), and wherein the first irradiation vector (V1) of the layer following the layer (n) is twisted (φ) relative to the first irradiation vector (V1) of the layer (n), and wherein an additional irradiation vector (V3) is provided, which additional irradiation vector (V3) is a plurality of concentric irradiation vectors for each layer of the component (10), and wherein the additional irradiation vector (V3) causes at least a partially porous structure of each layer.

2. The method according to claim 1, wherein, the first irradiation vector (V1) of the layer (n + 1) following the layer (n) is offset (d) relative to the first irradiation vector (V1) of the layer (n).

3. The method according to claim 1 or 2, wherein the irradiation power (P) of the first irradiation vector (V1) is reduced and / or the irradiation speed (v) of the first irradiation vector (V1) is increased relative to standard parameters for forming a solid material structure.

4. The method according to claim 1 or 2, wherein the first irradiation vector (V1) is a plurality of parallel irradiation vectors for each layer of the component (10).

5. The method according to claim 1, wherein the additional irradiation vector (V3) is provided for the layer (n) and for the layer (n + 1) following the layer (n), and wherein, the additional irradiation vector (V3) of the layer following the layer (n) is radially offset relative to the additional irradiation vector (V3) of the layer (n).

6. The method according to claim 1 or 2, the method being a CAM method.

7. The method according to claim 1, wherein the energy beam (5) is a laser beam or an electron beam.

8. A method for additively manufacturing a component (10) by selective laser melting or electron beam melting using manufacturing instructions provided according to any one of claims 1 to 7.

9. The method according to claim 8, wherein manufacturing instructions for a layer to be additively manufactured are determined in a first component region of the component (10), and wherein additional manufacturing instructions different from the manufacturing instructions are defined in a second component region different from the first component region.

10. A component (10) manufactured according to the method according to claim 8 or 9, wherein the component (10) is a component to be cooled in a hot gas path of a fluid machine.

11. The component (10) according to claim 10, wherein the component is a turbine blade, a thermal shielding component of a combustion chamber, and / or a resonator component.

12. A computer program product (CPP) comprising manufacturing instructions according to the method according to any one of claims 1 to 7, which, when the corresponding program is executed by a computer, causes the computer to perform the manufacture of the component (10) according to claim 10 or 11.

13. The computer program product (CPP) according to claim 12, the computer program product (CPP) comprising a program, wherein the program is for controlling and / or programming a build processor (4) and / or an irradiation device (2) of an additive manufacturing device (100).

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