SCANNING STRATEGY FOR VOLUME SUPPORT IN ADDITIVE MANUFACTURING

Abstract

A method of additive manufacturing includes a) providing a component geometry with a hole and, b) selectively irradiating a powder bed with an energy beam according to the geometry in a layerwise manner, wherein in layers of the component including the hole, the respective regions which define the hole are irradiated with the energy beam such that a supporting structure is generated in the hole having a lower rigidity than a structure of the component. The supporting structure is used for counteracting stress or distortion during the additive buildup. A computer program product and apparatus correspond to the method.

Claims

1. A method of additive manufacturing of a component comprising: a) providing a component geometry with a hole, b) selectively irradiating a powder bed with an energy beam according to said geometry in a layerwise manner, wherein in layers of the component including the hole, respective regions which define the hole are irradiated with the energy beam such that a supporting structure is generated in the hole having a lower rigidity than a structure of the component, wherein an irradiation pattern for the regions is chosen such that scanning vectors of said pattern overlap with an irradiation pattern for the component by about 100 μm or more.

2. The method according to claim 1, wherein the supporting structure comprises a volume or relative density in a range between 90% and 94%.

3. The method according to claim 1, wherein the hole extends substantially in a direction parallel to a buildup direction of the component.

4. The method according to claim 1, wherein the regions are irradiated at a hatching distance (D) being two to four times a hatching distance (d) chosen for the irradiation of the structure of the component.

5. The method according to claim 1, wherein the regions are irradiated at a scan speed being greater than a scan speed chosen for the irradiation of the structure of the component.

6. The method according to claim 1, wherein an undersize is accounted for the geometry of the hole as compared to an aim geometry thereof.

7. The method according to claim 1, wherein a raw material of the powder bed is a nickel- or cobalt-based superalloy.

8. The method according to claim 1, wherein the regions defining the hole in the as-manufactured and optionally thermally post-treated component are machined.

9. A computer program product stored on a non-transitory computer readable media, comprising: instructions which, when is executed by a computer, cause the computer to carry out the selectively irradiating of the powder bed according to claim 1.

10. An apparatus, comprising: means for carrying out the selective irradiation of the powder bed according to claim 1.

11. The method according to claim 4, wherein the hatching distance (D) chosen for irradiating the regions is three times the hatching distance (d) chosen for irradiating the structure of the component.

12. The method according to claim 5, wherein the scan speed chosen for irradiating the regions is two times greater than the scan speed chosen for irradiating the structure of the component.

13. The method according to claim 6, wherein the undersize is between 100 μm and 400 μm in diameter.

14. The apparatus according to claim 10, wherein the apparatus comprises a control or irradiation apparatus.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0036] FIG. 1 indicates in a schematic sectional view an additive manufacturing device and the manufacture of a component by powder bed fusion.

[0037] FIG. 2 indicates in a schematic perspective view a component geometry comprising a hole to be realised by additive manufacturing according to the present invention.

[0038] FIG. 3 indicates in a simplified schematic details for a scanning strategy of the component of FIG. 2.

[0039] FIG. 4 indicates in a schematic, further details of the scanning strategy used for the manufacture of the component according to the present invention.

[0040] FIG. 5 indicates, analogue to FIG. 4, a scanning strategy used for the component which is aligned in an alternative directional relationship with regard to its buildup direction.

[0041] FIG. 6 indicates by means of a schematic flow chart method steps of the present invention.

DETAILED DESCRIPTION OF INVENTION

[0042] Like elements, elements of the same kind and identically acting elements may be provided with the same reference numerals in the figures. The figures are not necessarily depicted true to scale and may be scaled up or down to allow for a better understanding of the illustrated principles. Rather, the described Figures are to be construed in a broad sense and as a qualitative base which allows a person skilled in the art to apply the presented teaching in a versatile way.

[0043] The term “and/or” as used herein shall mean that each of the listed elements may be taken alone or in conjunction with two or more of further listed elements.

[0044] FIG. 1 shows an additive manufacturing device 100. The device 100 is advantageously set up for the manufacture of the component 10 by so-called powder bed fusion, encompassing selective laser sintering, selective laser melting and electron beam melting.

[0045] To this effect, the device 100 comprises a build platform 1. Onto the build platform 1, the component 10 is established layer-by-layer by depositing a layer L of a powdery base material P, such as by a recoater 2 and the subsequent (selective) irradiation by an energy beam or an irradiation device (cf. reference numeral 3). Said energy beam may be a laser or an electron beam. It is the inherent principle of this manufacturing route that the powder bed is irradiated only at locations where the structure for the component needs to be established according to a predetermined target geometry. This geometry may e.g. be provided by a CAD (computer aided manufacturing) file. After the irradiation of each layer, the platform is usually lowered by an amount corresponding to a layer thickness (cf. reference numeral L). It is owed by this functionality that the buildup direction of the component is positively the vertical z-direction.

[0046] FIG. 2 shows a schematic perspective view of a geometry of the component 10 which is suitable to be additively manufactured in the described way. The indicated geometry images a central hole 20. For the sake of better illustration of the present invention, the design of the component of FIG. 2 is oversimplified, and may in reality have very complex or filigree shape.

[0047] The hole 20 may be a channel for a cavity or may have the shape of a bore. Prior to the actual physical buildup, the geometry of the component is, advantageously, provided by a CAD file which may be processed by the manufacturing device 100 and/or a control apparatus (see reference numeral 30 below).

[0048] During the additive buildup, small holes or cavities need normally not to be supported, such as mechanically supported or for enabling heat discharge. Larger holes or cavities, such as with dimensions of more than 10 mm may need a support depending on the aimed structural merits and dimensional accuracies.

[0049] According to the present invention (cf. also FIG. 6 below), a volume support strategy is provided which allows to generate a supporting structure 12 in the hole which has a lower rigidity than a structure of the component 10. The mentioned lower rigidity is indicated by the crosswise hatching of the region in the hole 20 and, advantageously allows for an easier re-working or mechanical machining of the region of the hole 20.

[0050] For instance, the supporting structure 12 may comprise a volume or relative density in a range between 90% and 94%.

[0051] Further, the supporting structure 12 may in other words comprise a porosity in a range between 6% and 10%.

[0052] By a suitable choice of irradiation parameters, such as hatching distance, scanning speed and possibly further parameters, the structure of the supporting material in the hole 20 can be tailored (see below).

[0053] The aim of the supporting structure 12 is, according to the present invention, not the conventional known support strategy, such as for mechanically and “thermally” supporting downskin faces for the buildup. Rather the aim is to prevent the component 10 from being distorted either during the buildup or during subsequent thermal treatment, wherein the location of the hole which may be offset or misaligned.

[0054] Such misalignment or shift of either the overall position of the hole in the geometry of the component or a distortion of the shape or contour of the hole 20 as a consequence of thermal or thermomechanical load (cf. reference numeral T in FIG. 2) is indicated by the dashed contour 20′ in FIG. 2.

[0055] Particularly for high-performance materials of superalloys and/or nickel-based or cobalt-based alloys, such deflection poses a major challenge, as the component at issue usually comprises a complex and filigree shape and, at the same time, requires a high degree of its dimensional accuracy. This purpose of the supporting structure 12 is served for almost any chosen build direction with regard to the component's geometry.

[0056] It is e.g. indicated in FIG. 2 that the hole 20 may extend substantially or completely in a vertical z-direction (indicated with the corresponding arrow and the encircled “1”).

[0057] Likewise, it is contemplated by the present invention that the hole extends substantially in a horizontal (spatial) direction as indicated by the arrow x and the encircled number “2” (cf. also FIG. 3 below).

[0058] FIG. 3 indicates in a simplified schematic top view f a section of the component 10 including the hole 20. This indication, advantageously, corresponds to the alternative 1 of FIG. 2, wherein a main extension of the component 10 as well as the hole course is substantially parallel to the vertical z-direction (cf. also FIG. 1). A border of the hole which may constitute or define in inner face of the component 10 is indicated with reference numeral 11.

[0059] For a proper or expedient irradiation of the different layers L of powdery material P in the region of the hole 20, it may be advantages to consider an undersize in the geometry of the component 10 as compared e.g. to the border 11 of the target geometry. Such undersize may e.g. amount to between 50 μm and 200 μm on each side of the contour of the hole region. Measured over the entire diameter, this may amount to an undersize of between 100 μm and 400 μm.

[0060] FIG. 4 indicates in a schematic—analogue to the principle of FIG. 3—further details of the scanning strategy used for the manufacture of the component 10. For the sake of a better overview only, the region of the hole is filled only with simple hatching lines which shall indicate the different irradiation vectors for the generation of the supporting structure. By reference of the coordinate system in the lower left corner of FIG. 4, it is apparent that the depicted situation is such that the main (longitudinal) extension of the hole 20 is aligned substantially parallel to the vertical z-direction.

[0061] Said scanning strategy, comprises a multiplicity of irradiation vectors which are indicated by the tilted hatching lines in FIGS. 4 and 5.

[0062] In the lower right corner of FIG. 4, the difference in the irradiation or scanning strategy of the supporting structure 12 is apparent. As compared to the irradiation mode of the component 10, comprising a hatching distance d, the hatching distance D for the presented supporting structure 12 is e.g. two to four times, such as three times, greater. Absolute values for the hatching distance D may amount to between 50 μm and 500 μm, for example. As a consequence, e.g. a lower aerial energy density is put in the powder bed at the location of the hole 20. Thereby, in turn, the rigidity can be lowered as compared to the structure of the component 10.

[0063] Likewise a scanning speed v may be adapted such that in the regions of the hole 20, it is chosen to be greater, such as two times, than that one chosen for the irradiation of the structure of the component 10. Absolute values for the scanning speed may amount to between 1500 mm/s and 4500 mm/s, for example.

[0064] A lowered rigidity of the supporting structure 12 as compared to the structure of the component 10 can as well be achieved by exposing or irradiating only every second or third layer L of powder P with an energy beam.

[0065] In addition, as indicated by the magnified portion of the transition from the structure of the component to the supporting structure 12 (or its corresponding scanning pattern), it is apparent and contemplated that the scanning vectors of said pattern for the supporting structure 12 overlaps by a distance o of at least 100 μm or more with an irradiation pattern for the component 10. This particularly allows to secure good connection between the supporting structure 12 and the structure for the component 10 at said transition.

[0066] FIG. 5 indicates, analogue to FIG. 4, a scanning strategy used for the component which is aligned in an alternative directional relationship with regard to its buildup direction. By reference of the indicated coordinate system it is apparent that the depicted relationship of alignment of the hole with regard to the additive buildup corresponds to the alternative 2 of FIG. 2. The overall technical improvement which may be achieved by the specific choice of the irradiation strategy of the supporting structure 12 (such as compared to a conventional strategy of a rigid structure) may be the same in this embodiment.

[0067] Particularly, the hatching distance D and the overlap o may be chosen relatively as described by way of the embodiment of FIG. 4. Alternatively, the given values for the hatching distance D, the scanning speed v and/or the overlap o or further parameters may be chosen different from that one conducted for the structure as long as the rigidity of the supporting structure 12 in the region of the hole 20 is reduced.

[0068] FIG. 6 indicates by way of a schematic of a simplified flowchart, a basic sequence of the method according to the present invention (cf. above). Said method is a method of additive manufacturing of the component 10 comprising, a), providing a component 10 geometry with a hole 20 and, b), selectively irradiating a powder bed P with the energy beam according to said geometry in a layerwise manner, wherein in layers L of the component 10 including the hole 20, the respective regions which define the hole 20 are irradiated with the energy beam such that a supporting structure 12 is generated in the hole 20 having a lower rigidity than a structure of the component 10.

[0069] These method steps may e.g. be carried out in the frame of a computer aided manufacturing (CAM) procedure and/or with a computer program product (cf. reference numeral CPP). Further, said procedure or according data may be stored in/or executed by an apparatus 30, such as a control and/or irradiation apparatus, e.g. comprising means for carrying out the selective irradiation of the powder bed P, as described.

[0070] Optionally the presented method may comprise, step c), machining, reworking or post-processing the regions defining the hole 20 in the as-manufactured and/or, optionally, further thermal treatment of the component 10.

[0071] The component 10 as referred to herein may particularly relate to a part or an article of complex shape, such as with filigree portions of structures. Advantageously, said component is made of a high-performance material, such as a material of great strength and/or thermal resistivity stop particularly, said part may constitute a part of a steam or gas turbine component, such as a blade, vane, shroud, shield, such as heat shield, tip, segment, insert, injector, seal, transition, burner, nozzle, strainer, orifice, liner, distributor, dome, boost, cone, lance, plate, resonator, piston or any corresponding retrofit kit. Alternatively, said component may relate to another or similar component.

[0072] It is contemplated for the present invention that further process and/or irradiation parameter may be modified or chosen for the generation of the supporting structure, such as a layer thickness, a beam power or power density, wavelength, beam offset, spot diameter, beam angle or further machine controls.

[0073] The scope of protection of the invention is not limited to the examples given hereinabove. The invention is embodied in each novel characteristic and each combination of characteristics, which particularly includes every combination of any features which are stated in the claims, even if this feature or this combination of features is not explicitly stated in the claims or in the examples.