EP3713697A1 - Method for selectively irradiating a material layer, production method, and computer program product - Google Patents
Method for selectively irradiating a material layer, production method, and computer program productInfo
- Publication number
- EP3713697A1 EP3713697A1 EP19701979.7A EP19701979A EP3713697A1 EP 3713697 A1 EP3713697 A1 EP 3713697A1 EP 19701979 A EP19701979 A EP 19701979A EP 3713697 A1 EP3713697 A1 EP 3713697A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- irradiation
- layer
- area
- vectors
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 title claims abstract description 50
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 41
- 239000000463 material Substances 0.000 title claims abstract description 20
- 230000001678 irradiating effect Effects 0.000 title claims abstract description 4
- 238000004590 computer program Methods 0.000 title claims description 7
- 239000013598 vector Substances 0.000 claims abstract description 54
- 239000000654 additive Substances 0.000 claims abstract description 29
- 230000000996 additive effect Effects 0.000 claims abstract description 29
- 239000000843 powder Substances 0.000 claims description 18
- 238000010276 construction Methods 0.000 claims description 12
- 238000013021 overheating Methods 0.000 claims description 11
- 238000010894 electron beam technology Methods 0.000 claims description 8
- 229910000601 superalloy Inorganic materials 0.000 claims description 4
- 229910017052 cobalt Inorganic materials 0.000 claims description 3
- 239000010941 cobalt Substances 0.000 claims description 3
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 3
- 238000011161 development Methods 0.000 claims description 2
- 230000008569 process Effects 0.000 description 8
- 230000005855 radiation Effects 0.000 description 6
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 5
- 230000007847 structural defect Effects 0.000 description 5
- 238000012545 processing Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000000149 argon plasma sintering Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 229940000425 combination drug Drugs 0.000 description 1
- 238000007596 consolidation process Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000029142 excretion Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012761 high-performance material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000010309 melting process Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000013519 translation Methods 0.000 description 1
- 230000014616 translation Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/36—Process control of energy beam parameters
- B22F10/366—Scanning parameters, e.g. hatch distance or scanning strategy
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
- B29C64/30—Auxiliary operations or equipment
- B29C64/386—Data acquisition or data processing for additive manufacturing
- B29C64/393—Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y50/00—Data acquisition or data processing for additive manufacturing
- B33Y50/02—Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2203/00—Controlling
- B22F2203/11—Controlling temperature, temperature profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2301/00—Metallic composition of the powder or its coating
- B22F2301/15—Nickel or cobalt
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y70/00—Materials specially adapted for additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/172—Copper alloys
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Definitions
- the present invention relates to a method for selec tive irradiation of a material layer in the additive Her position, a corresponding additive manufacturing process, a manufactured with this manufacturing process component and a corresponding computer program product.
- the method of selective irradiation may represent or include a method of computer-aided manufacturing (CAM).
- CAM computer-aided manufacturing
- the component preferably designates a component intended for use in a turbomachine, preferably in the hot gas path of a gas turbine.
- the construction part preferably consists of a nickel- or cobalt-based Su perleg réelle, or includes these.
- the alloy may be further precipitation or dispersion hardened.
- suitable generative or aditive manufacturing processes include, for example, as a powder-hardening method selective laser melting (SLM) or laser sintering (SLS), or electron beam melting (EBM).
- SLM powder-hardening method selective laser melting
- SLS laser sintering
- EBM electron beam melting
- a method for selective laser melting is crizoswei se known from EP 2 601 006 Bl.
- Additive manufacturing processes (English: “additive manufacturing”) have proven to be particularly advantageous for complex or complicated or filigree designed compo le, such as labyrinthine structures, cooling structures and / or lightweight structures.
- the additive manufacturing by a particularly short chain of processing steps is advantageous because a Manufacturing or manufacturing step of a component based on a corresponding CAD file can be done.
- a component geometry is defined or provided, and these are subdivided into individual layers in the context of computer-aided manufacturing methods ("slicing") for the selective consolidation of these layers, which are used for the final (physical) production
- the component may for example consist of a powdery base material, subsequently defining an irradiation pattern with individual irradiation vectors for each component layer to be solidified, which is preferably likewise computer-aided, for example by means of a CAM method.
- the layer thicknesses in which the construction model of the construction part is subdivided in this way, in the subsequent production depending on the desired geometric resolution less than 100 ym, for example, 40 ym to 60 ym, amount. Accordingly high is the number of layers and also the number of irradiation patterns or irradiation paths to be determined. Expediently, a pattern of irradiation is determined only in the areas or areas of a layer to be consolidated, which are actually to be consolidated.
- the surface areas can be
- the irradiation can be carried out selectively, for example by means of an electron beam or a laser beam corresponding to the desired geometry of the component, wherein the powder is first melted in the surface areas to be solidified and solidified or solidified for the production of the structure of the component.
- the irradiation paths are preferably arranged such that the powder layer, for example, nationwide, geras tert and can be remelted.
- the layer to be finished is preferably subdivided into the mentioned surface elements or surface regions, for example strips or checkerboard-like surfaces or surface segments.
- the irradiation pattern is preferably determined in such a way that an energy beam (electron beam or laser) can be guided meandering over the layer after a meandering time or can be scored.
- Meander-shaped irradiation vectors which form, for example, the irradiation pattern, are thus defined for such irradiation.
- the radiation pattern is usually ver rotates relative to the structural panel to prevent structural defects in the component, which can be, for example, by directly stacked laser paths, and to generate a more homogeneous structure in the component.
- a problem which increasingly arises due to this situation is local overheating, which is caused by too short irradiation vectors (scan vectors). These overheating preferably occurs at layer edges or edges, or at other areas of the layer in which the contour of the layer is strongly curved.
- One aspect of the present invention relates to a method for selective irradiation of a material layer in the addi tive production or manufacture of a component.
- the Materi al Anlagen can consist of a powdery or liquid base material.
- the method comprises providing or reading in a predetermined component geometry, for example a construction file (CAD) or a "3D scan" of the component Component geometry contains geometry information of individual layers of the component to be produced additively.
- a predetermined component geometry for example a construction file (CAD) or a "3D scan" of the component Component geometry contains geometry information of individual layers of the component to be produced additively.
- the method further comprises layering an irradiation pattern in area areas (for example strips or checkerboard areas) of a layer for the component, wherein the irradiation pattern in each area area comprises irradiation vectors and wherein - if a (pre) defined irradiation vector length in a first area area, for example is exceeded by a given or actual irradiation vector, lengthening of irradiation vectors in a second area region adjacent to the first area region of the layer up to a component contour.
- area areas for example strips or checkerboard areas
- the irradiation vectors in said second area region are preferably extended into the first area area "at the expense" of the length of the irradiation vectors.
- the reason why the length of said irradiation vector in the first area region is below the predefined irradiation vector length is that this first area area designates an edge or an edge of the component layer.
- the component contour may accordingly indicate, for example, an edge of the geometry of the component or an edge of the layer.
- the predefined irradiation vector length may be a minimum irradiation vector length, namely one below which excessive, destructive overheating of the layer during the process is to be expected.
- the irradiation vectors of the adjacent second area area are preferably extended into the original first area area if, for example, a vector currently being determined (actual vector) falls below the value of the predefined irradiation vector length.
- the extension of the irradiation vectors takes place in the context of the present invention on a computer-aided basis, so that finally during the manufacture of the component the irradiation vectors are no longer dimensioned too short and lead to overheating.
- the method may describe an adaptive, computer-aided measure in the context of the CAM, which sets the irradiation vectors such that the irradiation vectors have a minimum length, for example empirically or based on estimated, calculated and / or simulated results, which is then used in the actual production process circumvents described problems.
- the measure indicated by the present invention means a significant improvement, wel che, especially in the preparation of a construction process, leads to significantly improved material and structural properties of the component.
- the irradiation vectors in the second area area are extended over the entire area of the component contour in order to prevent simulated, estimated and / or calculated local overheating due to irradiation vectors that are too short in the first area area.
- the above estimate or calculation can be made, for example, by means of a simulation which takes into account the heat input into the powder bed or into the component and / or structural properties of the component.
- the layered setting is computer-assisted by means of a CAM method.
- the irradiation pattern for all layers of the component to be produced in an additive form is determined and stored. This refinement advantageously enables the development of structural defects in the component to be subsequently dragged from conclusions to the selected or determined irradiation strategy (irradiation pattern). This design can also be helpful in generating or developing a "digital twin" of the part.
- the information of the irradiation pattern for the component is provided in layers and with the geometry information of individual layers of the component in a common data record and / or linked.
- the common data record can be, for example, an xml format, an amf file (.amf), a comparable format or another CAM data set which, in addition to the geometry information (construction information), for example, information about the selected irradiation parameters, such as the scan or irradiation speed, laser power, track, stripe or hatch spacing, and / or stripe width.
- the radiation power or radiant energy introduced into the powder material and / or the consolidated layer per time interval can also be set and be stored within the scope of the described embodiment.
- Another aspect of the present invention relates to an additive manufacturing method comprising the described method of selective irradiation, wherein the selective irradiation takes place by means of a laser or an electron beam.
- the material layer is a powder layer.
- the material of the powder layer is made of a, in particular hardened, nickel- or cobalt-based superalloy.
- the component is a component to be used in the hot gas path of a turbomachine.
- a further aspect of the present invention relates to a component which is manufactured or can be produced according to the described additive manufacturing method, furthermore comprising a dimensional stability which is improved by, for example, 50% to 100% compared with a component produced according to the prior art.
- Dimensional accuracy or dimensional tolerance may mean, for example, a difference or distance between a maximum allowable and a minimum allowable amount (measured along any extension) of the component; a tolerance improved to a given dimensional accuracy in this sense, for example, a reduction of the tolerance distance.
- An improvement of the dimensional accuracy or dimensional stability tolerance by 100% is intended in the present case to mean, for example, a halving of the tolerance distance.
- the component preferably has a structure which is more homogeneous in comparison to a known component and / or be subject to structural defects, such as hot cracks, improved material structure, and correspondingly improved mechanical properties.
- a further aspect of the present invention relates to a computer program or a computer program product comprising instructions which, during the execution of the program by a computer or a data processing device, cause it to carry out the layering of the irradiation pattern.
- Embodiments, features and / or advantages that vorlie lowing the method for selective irradiation and / or the Comprehensive computer program product may also relate to the additive manufacturing process and / or the component and vice versa.
- Figure 1 shows a schematic plan view of a material layer of an additive to be constructed component and a subdivision of the material layer in strip-like surface areas.
- FIG. 2 shows a detailed section of FIG. 1 and an exemplary irradiation pattern.
- Figure 3 shows a similar to Figure 1 or Figure 2 Dar position with further marked information NEN.
- FIG. 4 indicates, based on a representation similar to the previous figures, a solution according to the invention of the problem described here.
- FIG. 5 indicates, on the basis of a schematic flowchart, method steps according to the invention.
- FIG. 6 shows a schematic sectional view of an additive manufacturing process of a component.
- FIG. 1 shows a component or a part thereof in a view.
- the component or a design model (CAD file) of the component is identified by the reference symbol B.
- the part of the component B which is shown in a round shape can furthermore designate a cross-sectional view of the component-for example during its additive production or a modeled layer thereof.
- the component is preferably a component which is used in the hot gas path of a turbomachine, for example a gas turbine.
- the component may designate a rotor or vane segment, a segment or ring segment, a burner part or a burner tip, a frame, a shield, a nozzle, a gasket, a filter, a Mün or lance, a resonator, stamp or a swirler , or a corresponding transition, use, or a corresponding retrofit part.
- component B is shown in the drawings described mostly round or cylindrical, it may have any predefined geometry, in particular even a particularly complicated or filigree geometry.
- selective laser melting or electron beam melting is often used among the additive methods, with an energy beam selectively guided over a powder bed from a predetermined irradiation pattern so as to provide the desired structure of the component B according to the predetermined geometry.
- the component B is finally built up on a building platform 20 by selective irradiation from a powder bed P after the preparatory CAM process steps.
- the irradiation takes place by means of a light emitted by an irradiation device 30 Laser or electron beam preferably in layers (see layer S in Figure 6).
- the component B has a component contour 10.
- the component contour 10 denotes only one edge of the component. At the but as shown in the figures, however, this edge or contour can be an internal contour, for example the contour of a cavity.
- the layer of the component B is superimposed with a stripe pattern (vertical straight dividing lines of the strips not explicitly marked), which has a stripe width 1.
- Each strip of the strip pattern preferably designates a surface area (ver equal to FIGS. 3 and 4) in which an irradiation pattern for the additive manufacture of the component can be determined (see FIG. 2).
- a strip width is present before lying with the reference numeral 1.
- a checkerboard-like subdivision of areas can be provided (compare also solid and dashed lines in FIGS. 1 and 2).
- Said subdivision into surface sections or surface areas takes place, for example, computer-aided and on a data basis by means of the CAM method.
- a whole strip for example from top to bottom, is irradiated according to the predetermined irradiation pattern, before changing to the next strip.
- individual checkerboard surfaces for the irradiation can, for example, be set at random one after the other.
- Figure 2 shows an enlarged view of the lower left Be rich of Figure 1. Top right in Figure 2, the construction part B is shown and the component contour 10th
- strips with strip spacing 1 are drawn from the side of component B, which in the present case represent the surface regions FB in which the irradiation pattern BM is defined or defined (compare FIGS. 3 and 4).
- the dashed lines indicate that the surface to be irradiated, instead of stripes like, also checkerboard-like with an energy beam (ver same Figure 6) can be irradiated or screened.
- a powder bed is not shown in FIGS. 1 to 4 for the sake of simplicity.
- the area of the component B may be that region of the powder bed which is irradiated for the additive production of the component.
- an irradiation pattern BM preferably composed of meander-shaped irradiation vectors V, is composed.
- the "meander geometry" of the superordinate irradiation direction can be modulated.
- Figure 3 is similar to Figures 1 and 2, two Bauteilbe rich or layers B, which in the shown view is not on usammen Struktur to the layer to be solidified Z. Both geometries are shown only by way of example with round contours 10 Kon.
- FIGS. 1 to 3 may preferably describe a situation of the prior art in which the solutions according to the invention are not yet implemented.
- the component layer B projects only slightly beyond the strip boundaries on the left and on the right edge.
- these areas are identified by the reference numeral 1FB as the first surface area.
- the irradiation vectors V are now also compiled and defined by a computer-aided method (CAM method) preparatory to the additive manufacturing process to the corresponding irradiation pattern BM (see enlarged section of the first surface area in the upper right in FIG. 3).
- CAM method computer-aided method
- these first surface regions 1FB are arranged adjacent to second surface regions 2FB of component B.
- radiation vectors V preferably mean any section of the irradiation pattern BM which extends directly perpendicular to the strips, that is to say along the direct strip spacing 1.
- Each individual irradiation vector V at all and also of the first surface area 1FB is expediently determined only within the component contour 10.
- Each irradiation vector V of the first surface area 1FB furthermore has only vectors V with an irradiation vector length of maximum L m , which is smaller than the strip spacing 1. Ver same also the enlarged section in the upper right in FIG. 3, in which a meandering Be radiation pattern with vectors V can be seen.
- the predefined and / or minimal irradiation vector length L d which can be estimated, simulated and / or calculated, for example by means of the described CAM method, and preferably corresponds to that irradiation vector length, is also indicated in the enlarged section on the top right in FIG of which the component B must be at least rasterized or irradiated, so that the energy inputs in the structure of the component B are not too large.
- the irradiation vector length L d may, for example, be between 50 and 200 ⁇ m.
- Figure 4 shows how the fiction, contemporary method described in this case the local overheating in the second surface areas by a corresponding assembly of the irradiation vectors V of the irradiation pattern BM vermei det.
- first surface areas 1FB of the component B are no longer marked in Figure 4 in overlap with the component contour B, 10 marked.
- the figure 4 indicates by the round curve of the strip boundaries or dividing lines that the second surface areas 2FB have been enlarged at the expense of the first area areas 1FB to which the irradiation vectors V of the irradiation pattern BM extend to a length L v (see double arrow) were.
- the component which was built on the basis of the above-described in Figure 4 be prescribed irradiation pattern BM additive, for example, by a selective laser melting process (see Figure 6), now includes in example a manufactured compared to one according to the prior art Component improved material structure, in particular an improved hardness, strength or susceptibility to hot cracking, and / or a more homogeneous or more favorable phase structure, for example, in terms of g or g 'excretions in superalloys.
- FIG. 5 shows the method according to the invention on the basis of a schematic flow chart. Said method is preferably a method for selectively irradiating a material layer in the additive manufacturing.
- method step a) it comprises the provision of a predetermined component geometry B, which geometry information N of the individual layers S (see Figure 6) of an additive to be produced component B contains. This can be done, for example, by reading in a CAD file, for example, into an appropriate additive manufacturing facility or a corresponding data processing facility or computer.
- the method further comprises, in method step b), layer-wise fixing of the irradiation pattern BM (as described above) into surface areas of a layer S to be built up for the production of the component B, wherein the irradiation pattern BM in each area comprises irradiation vectors V.
- Method step aa) indicates that irradiation vectors of length L m in the second surface area or areas 2FB of layer S are extended up to the component contour 10 (see FIG. 4) if the (pre) defined irradiation vector length L d of a given vector in the first surface area 1FB is exceeded.
- the method further includes in step c) setting and storing the irradiation pattern BM for all layers S of the component B or all layers of the construction part B, which conditions, for example, by their desired and de-defined geometry to structural defects or overheating conditions.
- the method further comprises in method step d), the layer-wise linking and / or providing the information of the irradiation pattern BM for the component B together with the geometry information (CAD) of individual layers of the component in a common data set, for example in an STL, AMF or G Code format.
- CAD geometry information
- the invention is not limited by the description based on the embodiments of these, but includes each new feature and any combination of features. This In particular, includes any combination of features in the claims, even if this feature or this combi nation itself is not explicitly stated in the claims or exemplary embodiments.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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EP18155290.2A EP3520929A1 (en) | 2018-02-06 | 2018-02-06 | Method for selectively irradiating a material layer, manufacturing method and computer program product |
PCT/EP2019/050309 WO2019154572A1 (en) | 2018-02-06 | 2019-01-08 | Method for selectively irradiating a material layer, production method, and computer program product |
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EP3713697A1 true EP3713697A1 (en) | 2020-09-30 |
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Family Applications (2)
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EP18155290.2A Withdrawn EP3520929A1 (en) | 2018-02-06 | 2018-02-06 | Method for selectively irradiating a material layer, manufacturing method and computer program product |
EP19701979.7A Withdrawn EP3713697A1 (en) | 2018-02-06 | 2019-01-08 | Method for selectively irradiating a material layer, production method, and computer program product |
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EP18155290.2A Withdrawn EP3520929A1 (en) | 2018-02-06 | 2018-02-06 | Method for selectively irradiating a material layer, manufacturing method and computer program product |
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US (1) | US20210079796A1 (en) |
EP (2) | EP3520929A1 (en) |
CN (1) | CN111712340A (en) |
WO (1) | WO2019154572A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4019164A1 (en) * | 2020-12-22 | 2022-06-29 | Siemens Energy Global GmbH & Co. KG | Radiation strategy in additive production with pulsed irradiation |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
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FR3080306B1 (en) * | 2018-04-19 | 2021-02-19 | Michelin & Cie | ADDITIVE MANUFACTURING PROCESS OF A METAL PART IN THREE DIMENSIONS |
EP3848135A1 (en) * | 2020-01-10 | 2021-07-14 | Siemens Aktiengesellschaft | Scanning strategy for volume support in additive manufacturing |
DE102020210681A1 (en) * | 2020-08-21 | 2022-03-10 | Trumpf Laser- Und Systemtechnik Gmbh | Planning device, production device, method and computer program product for the additive manufacturing of components from a powder material |
EP4005706A1 (en) * | 2020-11-26 | 2022-06-01 | Siemens Aktiengesellschaft | Method for layered production of an object |
DE102021202852A1 (en) | 2021-03-24 | 2022-09-29 | Siemens Energy Global GmbH & Co. KG | Additively manufactured fluid-permeable material structure |
DE102022111750A1 (en) | 2022-05-11 | 2023-11-16 | Trumpf Laser- Und Systemtechnik Gmbh | Method and planning device for planning a locally selective irradiation of a work area with an energy beam, method and manufacturing device for additively manufacturing a component from a powder material, and computer program product for carrying out such a method |
DE102022127241A1 (en) * | 2022-10-18 | 2024-04-18 | Trumpf Laser- Und Systemtechnik Gmbh | Process, control program and planning device for powder bed-based layer-by-layer additive manufacturing |
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SE9403165D0 (en) * | 1994-09-21 | 1994-09-21 | Electrolux Ab | Ways to sinter objects |
DE19606128A1 (en) * | 1996-02-20 | 1997-08-21 | Eos Electro Optical Syst | Device and method for producing a three-dimensional object |
EP2060343B1 (en) * | 2006-08-28 | 2014-11-05 | Panasonic Corporation | Metal powder for metal photofabrication and method of metal photofabrication using the same |
EP2415552A1 (en) | 2010-08-05 | 2012-02-08 | Siemens Aktiengesellschaft | A method for manufacturing a component by selective laser melting |
DE112013003448T5 (en) * | 2012-07-09 | 2015-04-16 | Panasonic Intellectual Property Management Co., Ltd. | A method of manufacturing a three-dimensional molded article |
CN105773967B (en) * | 2016-03-03 | 2018-04-20 | 西安铂力特增材技术股份有限公司 | A kind of strip-type laser beam scan path planing method |
CN105750543B (en) * | 2016-03-03 | 2018-05-18 | 西安铂力特增材技术股份有限公司 | A kind of checkerboard type laser beam scan path planing method |
DE102016203955A1 (en) * | 2016-03-10 | 2017-09-14 | Eos Gmbh Electro Optical Systems | Generative layer construction method with improved detail resolution and apparatus for carrying it out |
CN107470622A (en) * | 2017-08-24 | 2017-12-15 | 南昌航空大学 | It is a kind of that the method without rare earth aeolotropic Mn Al C permanent-magnet alloys is prepared by thermal deformation |
-
2018
- 2018-02-06 EP EP18155290.2A patent/EP3520929A1/en not_active Withdrawn
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2019
- 2019-01-08 US US16/959,701 patent/US20210079796A1/en not_active Abandoned
- 2019-01-08 EP EP19701979.7A patent/EP3713697A1/en not_active Withdrawn
- 2019-01-08 WO PCT/EP2019/050309 patent/WO2019154572A1/en unknown
- 2019-01-08 CN CN201980011804.2A patent/CN111712340A/en active Pending
Cited By (1)
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EP4019164A1 (en) * | 2020-12-22 | 2022-06-29 | Siemens Energy Global GmbH & Co. KG | Radiation strategy in additive production with pulsed irradiation |
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EP3520929A1 (en) | 2019-08-07 |
US20210079796A1 (en) | 2021-03-18 |
CN111712340A (en) | 2020-09-25 |
WO2019154572A1 (en) | 2019-08-15 |
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