METHOD FOR PRODUCING A SUPPORT STRUCTURE IN ADDITIVE MANUFACTURING

Abstract

A method for producing a support structure in the additive manufacturing of a component, includes: a) providing a geometry for the component having a region to be supported, b) providing a support structure for the region of the component, c) defining an irradiation pattern for an irradiation of layers of a raw material for the support structure, wherein surface vectors for an irradiation for a structure of the component extend into a region of the support structure, wherein common surface vectors are defined for the component and for the support structure, and d) selective irradiation of layers of the raw material for the component and the provided support structure according to the defined irradiation pattern.

Claims

1. A method for manufacturing a support structure in additive manufacturing of a component, comprising: a) providing a geometry for the component having a region to be supported), b) providing a support structure for the region of the component, c) defining an irradiation pattern for an irradiation of layers of a raw material for the support structure, wherein area vectors for an irradiation for a structure of the component extend into a region of the support structure, wherein common area vectors are defined for the component and for the support structure, and d) selectively irradiating layers of the raw material for the component and the provided support structure in accordance with the defined irradiation pattern.

2. The method as claimed in claim 1, wherein the region to be supported or a tangent to this region forms an angle of less than 40° with respect to a build platform for the additive manufacturing.

3. The method as claimed in claim 1, wherein the support structure is a so-called “volume support”, which is free of lattices or toothings.

4. The method as claimed in claim 1, wherein an irradiation for the layers of the support structure is carried out in a manner free of contour vectors.

5. The method as claimed in claim 1, wherein the support structure is manufactured in such a way that one or more layers in a layer sequence are omitted.

6. The method as claimed in claim 1, wherein the support structure, in contrast to the structure of the component, is irradiated with altered irradiation parameters.

7. The method as claimed in claim 1, wherein the layers for the support structure are irradiated with an increased irradiation speed.

8. The method as claimed in claim 1, wherein the layers for the support structure are irradiated with an adapted irradiation power.

9. The method as claimed in claim 1, wherein the component geometry has overhangs.

10. The method as claimed in claim 1, wherein the additive manufacturing method is a powder-bed-based method, or selective laser melting or electron beam melting.

11. A non-transitory computer readable medium, comprising: instructions stored thereon which, when executed by a computer, cause the computer to carry out the method as claimed in claim 1.

12. An apparatus adapted to perform the method of claim 1, comprising: at least one irradiation device, which is configured to irradiate layers for the component and the support structure in accordance with the irradiation pattern.

13. An apparatus adapted to perform the method of claim 1, comprising: a controller configured to control an irradiation device for selectively irradiating layers of a raw material in accordance with the irradiation pattern.

14. An apparatus for manufacturing a support structure in the additive manufacturing of a component, the apparatus adapted to perform the method of claim 1, comprising: a build platform; a coating device for distributing powder layer by layer; an irradiation device configured to irradiate layers for the component and the support structure; and a controller configured to control the irradiation device for selectively irradiating layers in accordance with the irradiation pattern.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Further details of the invention are described below with reference to the figures.

[0044] FIG. 1 shows a schematic sectional or side view of a component during the additive manufacturing thereof from a powder bed.

[0045] FIG. 2 shows, in the left-hand part of the illustration, a schematic sectional or side view of a geometry of a component to be additively manufactured. In the right-hand part, irradiation patterns for the manufacture of the component and/or of a support structure are indicated in a manner associated with indicated cross sections of the additive build-up.

[0046] FIG. 3 schematically indicates one exemplary embodiment of an irradiation strategy for the component and the support structure.

[0047] FIG. 4 shows a schematic flow diagram, indicating method steps according to the invention.

DETAILED DESCRIPTION OF INVENTION

[0048] In the exemplary embodiments and figures, identical or identically acting elements may each be provided with the same reference signs. The illustrated elements and their size relationships among one another should not be regarded as true to scale, in principle; rather, individual elements may be illustrated with exaggerated thickness or size dimensions in order to enable better illustration and/or in order to afford a better understanding.

[0049] FIG. 1 shows an additive manufacturing installation or manufacturing apparatus 100. The manufacturing apparatus 100 is advantageously configured as an LPBF installation and for the additive manufacturing of components from a powder bed. The installation 100 may especially also be an installation for electron beam melting. Accordingly, the apparatus comprises a build platform 1. On the build platform 1, a component 10′ to be additively manufactured is manufactured layer by layer from a powder bed. The latter is formed by a powder P, which can be distributed layer by layer on the build platform 1 by means of a coating device 30.

[0050] After the application of each powder layer Ln (cf. layer thickness L), in accordance with the predefined geometry of the component 10′ regions of the corresponding layer are selectively melted by an energy beam 21, for example a laser or electron beam, from an irradiation device 20 and/or a corresponding controller (cf. reference sign 50), and are subsequently solidified.

[0051] After each layer L, the build platform 1 is advantageously lowered by an amount corresponding to the layer thickness L (cf. arrow directed downward in FIG. 1). The layer thickness L is usually only between 20 μm and 40 μm, and so the overall process may easily require irradiation of a number of from one thousand to tens of thousands of layers.

[0052] In this case, high temperature gradients, for example of 10.sup.6 K/s or more, may occur as a result of the only very locally acting energy input. It goes without saying that a stress state of the component 10′ is also correspondingly high during the build-up and thereafter, which makes the additive manufacturing processes and/or corresponding post-processing considerably more complicated.

[0053] The geometry of the component is usually provided by a CAD file (cf. FIG. 4 further below).

[0054] After such a file has been read into the installation 100, the process usually requires firstly the definition of a suitable irradiation strategy for example by CAM (computer-aided manufacturing”) means, as a result of which the component geometry is normally also divided into the individual layers Ln.

[0055] The manufacturing complexity of the component is usually not always the same in this case. FIG. 1 illustrates a support structure 11′, for example, which has to support an overhanging region of the component both mechanically and thermally. Such overhanging regions are critical in particular since there a melt pool (not explicitly marked) dimensioned in a manner usually extending over a plurality of, for example 5, layer thicknesses extends downward into a loose powder region.

[0056] FIG. 2 shows, in the left-hand part of the illustration, parts of a component 10 to be additively manufactured, which component is built up and respectively provided with a support structure by means appertaining to the present invention. In other words, a corresponding irradiation of a support structure for the component is effected by way of the present invention.

[0057] The component 10 has a region 10a to be supported. The region 10a can be—as illustrated—a region partly overhanging the build platform 1. In contrast to the illustration, however, said region can also be a region having a vertical or only weakly overhanging wall (so-called “inskin” region), this region requiring an intensified mechanical support during build-up in order for example to avoid a “tearing away” of the component from the build platform 1.

[0058] Preventing such tearing away is conventionally done by a so-called beam offset usually being adapted or enlarged in preparation for the process. As a result, a volume of the support structure can likewise be enlarged and a greater overlap and fusion between layers of a support structure and the actual component occur, under certain circumstances. However, this measure has the disadvantage, inter alia, that the area to be exposed is additionally enlarged and, consequently, more material or volume is required, and the construction or process time is lengthened.

[0059] As an alternative thereto, it would be possible just to dispense with the “reproduction” of the region to be supported, and to build up solid material in the entire volume under the overhang. As a result, a very good mechanical linking is achieved; however, this strategy has the effect that process parameters adapted for a process efficiency cannot be applied to support structures.

[0060] The component 10 advantageously constitutes a component shaped in a complicated way and composed of high-performance materials, for example a component which is subjected to high thermal loading and for example is also used in the automotive sector or in the field of aeronautics.

[0061] Particularly advantageously, the component 10 is a component of the hot gas path of a turbo machine, such as a stationary gas turbine, for example. In this sense, the component may denote a rotor blade or guide vane, a ring segment, a burner part or a burner tip, a shroud, a screen, a heat shield, a nozzle, a seal, a filter, an orifice or lance, a resonator, a piston or a swirler, or a corresponding transition, insert, or a corresponding retrofit part.

[0062] The volume of the described component 10 can for example furthermore occupy at least 10%, 20%, 30% or 40% of the construction space of a corresponding manufacturing apparatus 100.

[0063] FIG. 2 furthermore depicts an overhang angle a, which is advantageously less than 50°, particularly advantageously less than 40°, relative to a surface of the build platform 1 or a horizontal. The advantages according to the invention are particularly clear in this angular range. However, the proposed irradiation strategy for the regions to be supported also has an advantageous effect even in the case of larger angles than that mentioned or structures overhanging to a lesser extent.

[0064] In the present case, therefore, the region 10a to be supported is provided with a support structure 11. The support structure is advantageously a so-called “volume support”, in particular without cavities, lattice structures or toothings.

[0065] It is discernible on the left in FIG. 2 that directly at the transition into the build platform 1 the support structure 11 is not structurally connected to the component 10. With progressive build-up of structure along the vertical build-up direction z, the structures of component 10 and support structure 11 in the example shown converge up to a point along the direction z at which they join together (cf. dashed horizontal line). Starting from this point, in the present case the overhang of the component also extends in accordance with its predefined geometry.

[0066] The dashed line indicating the aforementioned point corresponds here to the thirtieth constructed layer L30, for example. In the example described, the overhang of the region 11 to be supported continues to extend up to a layer L60 corresponding to the sixtieth constructed layer, for example.

[0067] A plan view of a layer plane of the built-up structures in accordance with the section A-A in the left-hand illustration is shown at the bottom right in FIG. 2. Since the structure of the component in accordance with a predefined geometry is not yet cohesively connected to the support structure at this point in time, two separate layer cross sections or plan views thereof are indicated. Even if the right-hand part of the illustration is merely a schematic indication of a geometry and a corresponding irradiation pattern therefor, the correspondingly shown layers are designated by the reference sign “10” for the component and “11” for the support structure for the sake of simplicity.

[0068] Hatching vectors or area irradiation vectors Vh, for an irradiation or build-up result covering as much area as possible, are indicated on the left in the layer plan view. Contour irradiation vectors Vk are depicted at a contour of the layer or in a manner enclosing the hatching vectors Vh. By way of a corresponding contour irradiation—usually also downstream of the area irradiation—an edge region of the built-up component structure is intended to be improved with regard to its structure and surface.

[0069] A plan view of a layer plane of the built-up structures in accordance with the section B-B in the left-hand illustration is shown at the top right in FIG. 2. This illustration corresponds to an irradiation variant according to the invention in accordance with which advantageously the support structure 11 can be built up in the present case. It is evident (also cf. FIG. 4 further below) that the area irradiation vectors for the structure of the component or a corresponding irradiation pattern M would be defined in such a way that they extend into a region of the support structure (towards the right) or were lengthened into said region or form common area irradiation patterns. The technical advantages according to the invention as described in the present case can be achieved as a result.

[0070] In particular, the support structure 11 at the top right in the illustration in FIG. 2 is indeed advantageously irradiated in the area in the same process step with the correspondingly adjacent layer for the component. However, the irradiation of the support structure is advantageously effected without any contour vectors. Therefore, contour irradiation vectors Vk are also only depicted in the left-hand portion of the plan view shown.

[0071] FIG. 3 shows, in the left-hand part of the illustration, a schematic plan view of a layer to be irradiated, or a digital model thereof, which partly includes a component region (on the left) and also a region of the support structure 11 (on the right). In particular, a single area irradiation vector is indicated as a diagonal arrow. Furthermore, a transition between the component 10 and the support structure 11 is indicated by a vertical line.

[0072] FIG. 3 illustrates in particular that the present invention proposes, by way of example, irradiating the support structure 11—in contrast to the structure of the component 10—with altered irradiation parameters. In particular, layers for the support structure 11 can be irradiated with an increased irradiation speed v. At various points of the area vector Vh, the reference sign v indicates an irradiation speed in each case for the corresponding point. It is evident in particular that the irradiation speed for the corresponding area irradiation in the region of the component on the left and also in the region of the transition (in the center) can be v=600 mm/s, by way of example. By contrast, the irradiation speed in the region of the support structure can be increased relative thereto; as illustrated for example v=800 mm/s.

[0073] Alternatively or additionally, the support structure 11 can be manufactured in such a way that one or more layers Ln in a layer sequence are omitted only for the support region, but are regularly irradiated for example in the region of the component geometry. In accordance with this embodiment, it can be advantageous that those layers for the build-up of the support structure 11 which are actively irradiated are then irradiated with an adapted, in particular increased, irradiation power p in order to melt the underlying pulverulent layer regions which were omitted from the irradiation. As is known, an increased radiation power or power density also causes a deeper melt pool which extends downward over more than five layer thicknesses, for example, and thus also reaches the loose powder regions. As a result the dimensional stability of the support structure is then ultimately ensured—as it were as a massy solid material.

[0074] It goes without saying that further manufacturing parameters or irradiation parameters can be adapted—either in the component region or in the region of the support structure—in the context of this strategy. Said parameters can concern for example the layer thickness L, a melt pool depth, a radiation power introduced, a laser wavelength, a so-called hatching spacing of individual area irradiation vectors, a beam offset, an irradiation speed, a beam focus, an irradiation angle or further parameters, such as, for example, the inert gas used for the irradiation or other ambient conditions, such as an ambient pressure, or the like.

[0075] FIG. 4 shows a schematic flow diagram indicating and summarizing method steps according to the invention. The method described is a method for manufacturing the support structure described, or the specification of a corresponding irradiation strategy therefor.

[0076] The method comprises, a), providing the geometry for the component 10 having the region 10a to be supported.

[0077] The method furthermore comprises, b), providing the support structure 11 for the region 10a of the component 10.

[0078] The method furthermore comprises, c), defining the irradiation pattern M for the irradiation of the powder layers Ln of a raw material P for the support structure 11, wherein area irradiation vectors Vh for an irradiation for a structure of the component 10 extend into the (lateral) region of the support structure 11. In other words, the aforementioned vectors, as described above, concern common area vectors for the component 10 and for the support structure 11.

[0079] The method furthermore comprises, d), selectively irradiating layers Ln for the component 10 and the provided support structure 11 in accordance with the defined irradiation pattern M, as described above.