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WO2018184725A1 - Procédé de fabrication additive d'un composant tridimensionnel et procédé pour calculer une stratégie de balayage pour permettre la commande correspondante d'une installation de fabrication additive d'un composant tridimensionnel - Google Patents

Procédé de fabrication additive d'un composant tridimensionnel et procédé pour calculer une stratégie de balayage pour permettre la commande correspondante d'une installation de fabrication additive d'un composant tridimensionnel Download PDF

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Publication number
WO2018184725A1
WO2018184725A1 PCT/EP2018/000157 EP2018000157W WO2018184725A1 WO 2018184725 A1 WO2018184725 A1 WO 2018184725A1 EP 2018000157 W EP2018000157 W EP 2018000157W WO 2018184725 A1 WO2018184725 A1 WO 2018184725A1
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WIPO (PCT)
Prior art keywords
heat dissipation
trajectories
dissipation capability
component
isolines
Prior art date
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Ceased
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PCT/EP2018/000157
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German (de)
English (en)
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WO2018184725A8 (fr
Inventor
Vasily Ploshikhin
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AMSIS GMBH
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AMSIS GMBH
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Publication of WO2018184725A1 publication Critical patent/WO2018184725A1/fr
Publication of WO2018184725A8 publication Critical patent/WO2018184725A8/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • B29C64/10—Processes of additive manufacturing
    • B29C64/141—Processes of additive manufacturing using only solid materials
    • B29C64/153—Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
    • 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
    • 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
    • B29C64/20—Apparatus for additive manufacturing; Details thereof or accessories therefor
    • B29C64/264—Arrangements for irradiation
    • B29C64/277—Arrangements for irradiation using multiple radiation means, e.g. micromirrors or multiple light-emitting diodes [LED]
    • B29C64/282—Arrangements for irradiation using multiple radiation means, e.g. micromirrors or multiple light-emitting diodes [LED] of the same type, e.g. using different energy levels
    • 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
    • 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
    • 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
    • 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
    • B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
    • 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
    • B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
    • B22F12/40—Radiation means
    • B22F12/41—Radiation means characterised by the type, e.g. laser or electron beam
    • 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
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • 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
    • B33Y30/00—Apparatus for additive manufacturing; Details thereof or accessories therefor
    • 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
    • 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
    • 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 the additive production of a three-dimensional component from a plurality of component layers by multiple incremental, in particular layer by layer, adding powder, wire or tape, in particular metallic, component starting material and, in particular incremental, shaping solidification by each selective melting and / or Sintering of the component starting material by means of a heat quantity introduced by at least one energy source, in particular locally, in accordance with a scanning strategy, and a method for calculating a scanning strategy for the purpose of corresponding activation of a system for the additive production of a three-dimensional component.
  • component is also intended to mean a component including a building board (base plate) and a support structure (s).
  • base plate building board
  • s support structure
  • B. a manufactured in a construction job in a space construct, the e.g. of several, e.g. identical, individual components may consist.
  • the energy source for example, an arc, a plasma jet, a laser beam, electron beam or the like may be used.
  • CONFIRMATION COPY Additive manufacturing processes may be, in particular, a jet-based additive manufacturing process, such as selective laser melting or selective electron beam melting.
  • the component starting material can be made of metal, plastic or ceramic. It can also be, for example, a powder, a powder cored wire or filler band.
  • the additive manufacturing process which is also referred to as a generative manufacturing process, may be, for example, arc, plasma, laser and electron beam deposition welding and general build-up welding, in particular powder coating, laser and electron beam melting, laser sintering and all other processes in which material is selectively applied in the melt to generate a component.
  • the trajectories of the energy input in particular the heat input, designed mainly purely geometrically.
  • a subdivision of the layer geometry to be generated into individual, usually rectangular segments takes place.
  • equidistant rectilinear trajectories (called exposure vectors or scan vectors) are laid out parallel to the segment boundaries.
  • the actual energy or heat input takes place, for example, by a laser along an exposure vector.
  • several exposure vectors within a segment are generated one after the other. In other words, the amount of energy or heat is introduced by means of a scanning strategy.
  • scan strategy is intended here primarily to describe the consolidation of a defined area in a layer of a component starting material with the already generieten (consolidated) part of the component by fusion, welding, sintering or solidification by means of at least one moving (in particular punctiform) Energy source under consideration of deflection paths or exposure paths (scan pattern) and beam parameters and the time dependence of Deflection paths and directional dependence of the deflection to produce desired component and structural properties to be meant.
  • the scan strategy includes a scan pattern. This is the geometric description of the deflection paths or connecting lines of successive energy inputs, for example when pulsing, for solidifying the component contour and / or the component cross section by means of at least one beam or another heat source.
  • thermal build-up and, in particular, local overheating can occur due to the layered structure and the local energy input, in particular close to component edges, which can impair the component quality and in particular the surface of the component due to sintering effects lead to undesirable local deformations (delay).
  • the present invention is therefore based on the object to provide a method for the additive production of a three-dimensional component with which components can be manufactured in a better quality.
  • this object is achieved in the generic method in that the design of the trajectories and / or the order and / or direction of the trajectories of heat input on the basis of, in particular simulation-based, local heat dissipation capability or based on a function thereof in a respective component layer ,
  • the determination of the local heat dissipation capability is described in DE 102016120998.8 Ai, the disclosure of which is incorporated herein by reference in its entirety.
  • the local heat dissipation capability characterizes the ability of a device area to carry heat to the interior of the device.
  • At least a portion of the trajectories of the heat input along isolines or quasi-isolines of the determined local heat dissipation capability is designed. Quasi-isolines are intended to mean lines that are quite close to isolines. The resulting traces of consolidation will be cooled more evenly, which will lead to a reduction in local residual stress and local distortion. The expected same thermal conditions along the entire trajectory ensure better local process stability (e.g., maintenance of the constant melt pool in selective laser melting).
  • a trajectory represents a consolidation trace such as a fuse track / weld path in selective laser melting of metallic materials or a solidified wire trace in the fused deposition modeling of thermoplastics.
  • This track has a certain width, which depends on the process parameters (eg power of the beam and its speed).
  • the individual traces of consolidation are advantageously designed so that they touch or overlap, so that the entire consolidated component layer is completely sealed. Therefore, advantageously, the trajectories representing a center line of these tracks should be designed with a distance such that the corresponding tracks intersect at a predetermined degree. In particular, it may be provided that the trajectories are self-contained lines. The trajectories are advantageously designed along the isolines.
  • the isolines when they are completely inside the component, are always self-contained.
  • the trajectories along these isolines may be self-contained, but need not.
  • the isolines that come to a component boundary are not self-contained. Accordingly, the trajectories along these isolines are not self-contained.
  • the trajectories are designed such that at least a portion of the heat input trajectory begins at one isoline having a particular value of local heat sink capability and ends at another isoline with a different local heat sink capability value.
  • the trajectories of the heat input are scanned from isolines having a low value of local heat dissipation capability to isolines having a higher value of local heat dissipation capability.
  • the time interval between successive trajectories is reduced.
  • the heat input is increased in the transition to the next consecutive trajectory by increasing the power of the power source and / or reducing the speed of the power source.
  • the trajectories of heat input are scanned from isolines having a higher value of local heat dissipation capability to isolines having a lower value of local heat dissipation capability.
  • the time interval between successive trajectories is increased.
  • the heat input is reduced in the transition to the next successive trajectory by reducing the power of the power source and / or increasing the speed of the power source.
  • the direction of scanning of individual trajectories of the heat input is determined based on the values of the local gradient of the heat dissipation capability.
  • the trajectories of the heat input are generated in the direction of a higher value of the gradient of the local heat dissipation capability.
  • the component layer is produced by means of a plurality of energy sources acting simultaneously in different locations of the component layer, in particular with a plurality of lasers or with a locally split light source.
  • At least one pair of consecutively following trajectories is generated simultaneously from the sequence for generating the trajectories with the aid of two different energy sources.
  • the present invention also provides a method for the calculation of a scanning strategy for the corresponding control of a system for additive manufacturing of a three-dimensional component, wherein the design and / or the order and / or the direction of the trajectories (TT 2 ; T c ) of the heat input based on a , in particular simulation-based, determined local heat dissipation capability or based on a function of the same takes place in a respective component layer.
  • the trajectories of the heat input along isolines or quasi-isolines of the determined local heat dissipation capability is designed.
  • the trajectories are designed such that at least a portion of the heat input trajectory begins at one isoline having a particular value of local heat sink capability and ends at another isoline with a different local heat sink capability value.
  • a component layer is segmented on the basis of a local heat dissipation capability and a trajectory is applied within the boundaries of one of the segments of this component layer.
  • isolines or quasi-isolines or points are selected at an isoline of local heat dissipation capability to confine a segment.
  • At least part of the segment boundaries is aligned in the direction of the gradient of the heat dissipation capability or substantially perpendicular to the isolines or quasi isolines of the local heat dissipation capability.
  • a trajectory of the heat input is assigned an area around this trajectory as a consolidation area.
  • the consolidation range is defined based on a calculation of the thermal field from a moving energy source along the trajectory of the heat input.
  • the consolidation range of a trajectory is defined as an area in which the temperatures have reached a certain predetermined value, in particular the value of the melting temperature of the consolidated material.
  • the consolidation areas of the adjacent trajectories overlap.
  • the consolidation areas of all trajectories in the respective component layer cover the area of these component layers without gaps.
  • the trajectories of the heat input are designed starting from isolines with a low value of the local heat dissipation capability to isolines with a higher value of the local heat dissipation capability.
  • the trajectories of heat input are laid out from isolines having a higher value of local heat dissipation capability to isolines having a lower value of local heat dissipation capability.
  • the direction of scanning of individual trajectories of the heat input is determined based on the values of the local gradient of the heat dissipation capability.
  • the trajectories of the heat input are designed in the direction of a higher value of the gradient of the local heat dissipation capability.
  • the present invention provides a system for additive production of a three-dimensional component of several component layers by multiple incremental, especially layer by layer, adding powdered, wire or strip, in particular metallic, component starting material and, in particular incremental, shaping consolidating the component starting material by each selective melting and / or sintering by means of an amount of heat introduced by at least one energy source, in particular locally, in accordance with a scanning strategy a construction space housing with a construction platform for supporting one or more powder-bed-based additive to be manufactured component / components,
  • a layer preparation device for preparing respective powder layers on the build platform
  • an irradiation device for irradiating the respectively last-prepared powder layer on the building platform
  • control device for controlling the irradiation device according to a method according to one of claims 1 to 28.
  • the present invention also provides one or more computer-readable media that includes computer-executable instructions that, when executed by a computer, cause the computer to perform the method of any one of claims 1 to 28 to perform.
  • the present invention is based on the surprising finding that, by designing the trajectories and / or the chronological sequence of the heat input of the scanning strategy on the basis of a local, in particular simulation-based, localized heat dissipation capability in a respective component layer, the component quality is better compensated by the temperature field within the component can be improved, overheated areas and / or component distortion can be avoided and the total time can be reduced for the construction process and the productivity of additive plants can be increased.
  • the invention focuses on a rapid dissipation of the introduced energy within the component, which at the same time can lead to at least one of the following advantages:
  • Fig. L is a schematic representation for explaining the definition of the local
  • Fig. 2 is a schematic representation for explaining the term "trajectory"
  • Fig. 3 is a schematic representation for explaining a method for additive
  • Fig. 5 is a plan view of the component of Fig. 4;
  • Fig. 6 is an exemplary local distribution Di of the heat dissipation capability D loc in a device layer Li of the device of Fig. 4; Isolines Ii, I 2 and I 3 of the local distribution D, the heat dissipation capability in a device layer Li of FIG. 6;
  • Fig. Ii an example of a segment S of a component layer
  • FIG. 12 shows a segment S q resulting from modification of the segment S of FIG.
  • Fig. 17 is a plan view of a device layer L;
  • Fig. 19 shows a layout of trajectories according to a particular one
  • the heat dissipation capability D (dissipation) of the component layer is defined as the integral of the heat flow q [W / m 2 ] over the surface s [m 2 ] (see FIG.
  • the local heat dissipation capability can be calculated from the heat equation:
  • the local heat dissipation capability depends not only on the material properties (heat conduction, heat capacity, density) and heat input. It is also affected by the boundary conditions, such. As the local component geometry, strongly influenced.
  • the local component geometry is also taken into account.
  • This representation of local heat dissipation capability allows for easy determination of the ability of a particular point to dissipate the heat in a given one Time. The higher the cooling rate at the point under consideration at a certain time, the higher the local heat dissipation capability.
  • AH is the change in enthalpy, J, in the time interval from & to t 2 .
  • the local heat dissipation capability can be characterized by the change in temperature:
  • the heat in an additive manufacturing process is normally transported primarily downwardly from a generated device layer to the interior of the device.
  • the value of a local heat dissipation capability is indirectly indicative of the amount of mass of the "cold" consolidated material below the particular point of the device layer, the more "cold" material mass is below a particular point of a device layer, the higher the value of a local one heat dissipation capability.
  • the determination of the local heat dissipation capabilities can be made much faster.
  • the entire component is calculated without thermal activation of individual component layers / segments.
  • Such a simplified simulation will drastically reduce the computation time required (the larger the component, the greater the savings in computation time).
  • an "artificial" temperature distribution with ascending temperature in the direction of construction is used as an initial condition.
  • the initial temperature gradients T in the x and y directions are used as zero:
  • Such a temperature distribution as an initial condition mimics the temperature distribution in the real building process. For each component layer, this distribution ensures that the heat flow at the beginning of the calculation takes place exclusively downwards.
  • the constant initial temperature gradient in the assembly direction predefined for each point of the component and thus also for each component layer, has the same zero value of the local heat dissipation capability:
  • the initial temperature distribution is simply assumed.
  • simplified solutions such as a fast one- or two-dimensional calculation of the temperature field in the build process, as well as experimental measurements can be used.
  • boundary conditions can also be defined. Some particularly advantageous boundary conditions should be mentioned separately:
  • the heat flow at the upper edge is qcoben; English: top) and at the lower edge C [(bottom: English: bottom) constant and corresponds to the given initial constant temperature gradients (T (x, y, z, o)) in the component:
  • the other edges of the component are thermally insulated, which means that the temporal heat flow always has a zero value.
  • the initial local heat dissipation capability has a zero value at each point in the calculation area (justification given above). For the same upper and lower surface of the calculation area, this constraint ensures a flow of the same amount of energy through the entire computation area. After a certain time for these boundary conditions to reach a stationary state of the temperature field, that is, after a redistribution of the temperature, the "new" temperature remains stable at each point, thus stabilizing also the values of local heat dissipation ability to calculate for this stationary or almost stationary condition.
  • This variant of the boundary conditions is particularly suitable for determining the local heat dissipation capability in local areas of the component.
  • Such local calculations for example, examine the heat build-up in the vicinity of a channel or defect, such as a pore or other undesirable void.
  • the local calculations of this kind can find an application in the context of a monitoring system (see below).
  • a full thermal isolation of the entire calculation area represents a variant of the boundary conditions, which is very well suited for the determination of the local heat dissipation capability in the components (in the context of the so-called global calculations (thermal calculation of the whole component)). It may then be sufficient to calculate up to a first maximum of the temperature change (and not up to a stationary or almost stationary state).
  • the field of local heat dissipation capability can be determined numerically by a thermal computation for a given component (in advance).
  • the component is layered by means of one or more energy sources (as part of a Irradiation device), in the present example by means of a laser (not shown), constructed (see Figure 2).
  • the laser provides a laser beam 50, which in this example is directed by a scanner 60.
  • the consolidation of a component layer Li is carried out with the aid of the laser beam 50 by generating a plurality of trajectories, of which only one is shown and provided with the reference number 30.
  • the point on the trajectory should designate the starting point, while the arrowhead indicates the end point.
  • FIG. 3 shows a system with two energy sources, in each case a laser (not shown), in this example.
  • Each of the two lasers supplies a respective laser beam 51 or 52.
  • two different trajectories 31 and 32 are generated simultaneously with the laser beams 51 and 52, respectively.
  • FIG. 4 shows a side view of an axisymmetric component 1 with an outer surface 2.
  • it is a frusto-conical component.
  • the component 1 has an upper diameter di and a lower diameter d 2 .
  • the construction direction is marked by z.
  • FIG. 5 shows a top view of component 1 of FIG. 4.
  • FIG. 6 shows a local distribution Di of the heat dissipation capability D loc in a component layer Li of the component 1 of FIG.
  • the component layer Li is at a height H ,. Since the component 1 is symmetrical, the field of heat dissipation capability is also symmetrical.
  • Reference numeral 3 denotes the outer edge of the component layer Li which lies on the outer surface 2.
  • the surface 2 forms a barrier to the free flow of heat downwards (against the direction of construction z). The closer to the edge 3 in the device layer Li, the more the heat accumulates and the lower the heat dissipation capability. In the middle area (within the diameter d 2 ) the heat flow downwards is not prevented.
  • FIG. 7 shows associated isolines I 15 5 2 and I 3 of the local heat dissipation capability D, in the component layer Li of FIG. 6 with the edge 3.
  • the values Ci, C 2 and C 3 are constants. Due to the symmetry of the component 1, the isolines are also symmetrical. The isolines I 3 and the outer edge 3 of the device layer Li are identical due to the symmetry.
  • Figure 8 relates to an example showing two trajectories Ti and T 2 which are produced along the contour lines II and I 2nd
  • FIG. 9 shows an example in which the trajectories Ti and T 2 are produced along quasi-isolines, that is, based on the isolines Ii and I 2 .
  • FIG. 10 shows an example of a trajectory Ti with a starting point at an isoline L and an end point on another isoline I 2 of the heat dissipation capability.
  • Figure 11 shows an example of a design of the boundaries of a segment S after the isolines.
  • I a and Ib are the isolines of local heat dissipation ability
  • Pi and P 2 are two points on isoline I a .
  • Gi and G 2 are gradients of heat dissipation capability at these points.
  • the points P 3 and P 4 are obtained by crossing the isoline I e with the directions of the gradients Gi and G 2 .
  • the resulting segment S is also shown in FIG.
  • segment S has been modified into a segment S q .
  • the boundaries of the segment S q are formed on the basis of the points on the isolines I a and Ib.
  • an isoline I c extends in a segment S (see FIG. 13 (a)).
  • a trajectory T c is designed within the segment S (see FIG. 13 (b)).
  • the trajectory does not necessarily have to run along an isoline.
  • it could be a straight line between the start and end points of the isoline, or another line that is substantially parallel to segment boundaries.
  • FIG. 14 now shows a trajectory Ti with a consolidation region Bi with a width bi.
  • FIG. 15 shows two trajectories Ti and T 2 with a respective consolidation region Bi or B 2 , which touch, but do not overlap.
  • FIG. 16 shows a case in which the trajectories Ti and T 2 have consolidation regions Bi and B 2 , respectively, which overlap.
  • the trajectories Tj and T 2 are arranged such that the component layer Li with a surface 3 is completely covered by their respective consolidation regions Bi or B 2 .
  • FIG. 18 shows an example of a distribution of a temperature gradient: the closer the isolines Ii, I 2 and I 3 are, the greater are the temperature gradients. Therefore, the temperature gradient increases with the transition from P 2 to P 3 (or P 4 ) to Pi.
  • BHG is a region with the highest temperature gradients (HG - high gradient) and BLG is a region with the lowest temperature gradients (LG - low gradient) ,
  • FIG. 19 shows an example of the design or alignment of
  • trajectories may look like this: first, the trajectories are generated in areas of lowest values of heat dissipation capability (between isolines I 3 and I 2 ).
  • the trajectories are generated with the help of, for example, two lasers. Then, for example, the trajectories Ti and T 2 are generated simultaneously. This allows a more uniform and particularly symmetrical distribution of the temperature field.
  • the sequence described above may be altered, reduced or supplemented.

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  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Health & Medical Sciences (AREA)
  • Toxicology (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Powder Metallurgy (AREA)

Abstract

La présente invention concerne un procédé de fabrication additive d'un composant tridimensionnel (1) réalisé en plusieurs couches par apports multiples incrémentiels, notamment sous forme de couches, d'une matière de départ de composant, notamment métallique, se présentant sous forme de poudre, de fil ou de bande, et par consolidation de mise en forme, notamment incrémentielle de la matière de départ de composant par fusion et/ou frittage respectivement sélective/sélectif au moyen d'une quantité de chaleur appliquée par l'intermédiaire d'au moins une source d'énergie, notamment localement, selon une stratégie de balayage, la disposition des trajectoires (30, 31, 32) de l'apport d'énergie s'effectuant en fonction d'une capacité de dissipation thermique locale déterminée notamment sur la base d'une simulation. L'invention concerne par ailleurs un procédé pour calculer la stratégie de balayage pour permettre la commande correspondante d'une installation de fabrication additive d'un composant tridimensionnel, et une installation correspondante.
PCT/EP2018/000157 2017-04-06 2018-04-05 Procédé de fabrication additive d'un composant tridimensionnel et procédé pour calculer une stratégie de balayage pour permettre la commande correspondante d'une installation de fabrication additive d'un composant tridimensionnel Ceased WO2018184725A1 (fr)

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DE102017107362.0 2017-04-06
DE102017107362.0A DE102017107362A1 (de) 2017-04-06 2017-04-06 Verfahren zur additiven Fertigung eines dreidimensionalen Bauteils und Verfahren zur Berechnung einer Scanstrategie zwecks entsprechender Ansteuerung einer Anlage zur additiven Fertigung eines dreidimensionalen Bauteils

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WO2018184725A8 WO2018184725A8 (fr) 2018-12-27

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019219276A1 (de) * 2019-12-10 2021-06-10 Eos Gmbh Electro Optical Systems Hatchumkehr mit Keyhole-Übergabe
CN119407202A (zh) * 2024-11-08 2025-02-11 沈阳飞机工业（集团）有限公司 一种减缓激光熔化沉积层边缘效应的扫描方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102020003536A1 (de) 2020-06-13 2021-12-16 Laempe Mössner Sinto Gmbh Verfahren zum Erzeugen einer 3D-Struktur
DE102021134379A1 (de) 2021-12-22 2023-06-22 Arburg Gmbh + Co Kg Thermische Prozessführung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001091924A1 (fr) * 2000-06-01 2001-12-06 Board Of Regents, The University Of Texas System Frittage laser direct selectif de metaux
US20150174827A1 (en) * 2013-11-21 2015-06-25 SLM Solutions Group AG Method and device for controlling an irradiation system
CN104190930B (zh) * 2014-08-29 2016-03-02 中国科学院重庆绿色智能技术研究院 一种同质功能梯度材料及结构的激光增材制造方法
US20160059493A1 (en) * 2014-09-02 2016-03-03 Product Innovation and Engineering L.L.C. Additive layering method using improved build description
US20170001243A1 (en) * 2015-07-03 2017-01-05 Aspect Inc. Powder bed fusion apparatus
DE102016120998A1 (de) 2016-11-03 2018-05-03 Universität Bremen Verfahren zur simulationsbasierten Erkennung thermisch kritischer Bauteilbereiche und Verfahren zur bauteilspezifischen Anpassung einer lokalen Wärmegenerierung bei der additiven Herstellung

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10042134C2 (de) 2000-08-28 2003-06-12 Concept Laser Gmbh Verfahren zur Herstellung von dreidimensionalen Sinter-Werkstücken
GB2378150A (en) * 2001-07-31 2003-02-05 Dtm Corp Fabricating a three-dimensional article from powder
US9767224B2 (en) * 2013-05-13 2017-09-19 The Board Of Trustees Of The University Of Alabama Systems and methods for designing and fabricating contact-free support structures for overhang geometries of parts in powder-bed metal additive manufacturing

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001091924A1 (fr) * 2000-06-01 2001-12-06 Board Of Regents, The University Of Texas System Frittage laser direct selectif de metaux
US20150174827A1 (en) * 2013-11-21 2015-06-25 SLM Solutions Group AG Method and device for controlling an irradiation system
CN104190930B (zh) * 2014-08-29 2016-03-02 中国科学院重庆绿色智能技术研究院 一种同质功能梯度材料及结构的激光增材制造方法
US20160059493A1 (en) * 2014-09-02 2016-03-03 Product Innovation and Engineering L.L.C. Additive layering method using improved build description
US20170001243A1 (en) * 2015-07-03 2017-01-05 Aspect Inc. Powder bed fusion apparatus
DE102016120998A1 (de) 2016-11-03 2018-05-03 Universität Bremen Verfahren zur simulationsbasierten Erkennung thermisch kritischer Bauteilbereiche und Verfahren zur bauteilspezifischen Anpassung einer lokalen Wärmegenerierung bei der additiven Herstellung

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019219276A1 (de) * 2019-12-10 2021-06-10 Eos Gmbh Electro Optical Systems Hatchumkehr mit Keyhole-Übergabe
CN119407202A (zh) * 2024-11-08 2025-02-11 沈阳飞机工业（集团）有限公司 一种减缓激光熔化沉积层边缘效应的扫描方法

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