WO2017220058A1 - Procédé de fabrication d'au moins un élément structural hybride pourvu de zones partielles réalisées par impression 3d - Google Patents

Procédé de fabrication d'au moins un élément structural hybride pourvu de zones partielles réalisées par impression 3d Download PDF

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Publication number
WO2017220058A1
WO2017220058A1 PCT/DE2016/000426 DE2016000426W WO2017220058A1 WO 2017220058 A1 WO2017220058 A1 WO 2017220058A1 DE 2016000426 W DE2016000426 W DE 2016000426W WO 2017220058 A1 WO2017220058 A1 WO 2017220058A1
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WO
WIPO (PCT)
Prior art keywords
component
cavity
subregion
partial region
generatively
Prior art date
Application number
PCT/DE2016/000426
Other languages
German (de)
English (en)
Inventor
Markus Schlemmer
Gerhard-Heinz Rösele
Andreas Hartung
Manfred Schill
Karl-Heinz Dusel
Original Assignee
MTU Aero Engines AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of WO2017220058A1 publication Critical patent/WO2017220058A1/fr

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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
    • 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
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
    • 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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • 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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
    • 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
    • B33Y80/00—Products made by additive manufacturing
    • 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/01—Vibration-dampers; Shock-absorbers using friction between loose particles, e.g. sand
    • F16F7/015—Vibration-dampers; Shock-absorbers using friction between loose particles, e.g. sand the particles being spherical, cylindrical or the like
    • 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
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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 invention relates to a method for producing at least one component and to a component, in particular for a turbomachine.
  • Methods and apparatus for making individual component areas or complete components are known in a wide variety.
  • additive or generative production methods are known in which the component, which may be, for example, a component of a turbomachine or an aircraft engine, is built up in layers.
  • metallic components can be produced, for example, by laser or electron beam melting or sintering methods.
  • at least one powdered component material is first applied in layers to a component platform in the region of a buildup and joining zone of the device.
  • the powder is locally hardened in layers by selectively supplying the powder in the region of the buildup and joining zone with energy by means of at least one high-energy beam, for example an electron or laser beam, whereby the component material melts and / or sinters.
  • the high-energy beam is controlled in dependence on a layer information of the component layer to be produced in each case.
  • the layer information is usually generated from a 3 D-CAD body of the component and divided into individual component layers.
  • the component platform is lowered layer by layer by a predefined layer thickness. Thereafter, the said steps are repeated until the final completion of the desired component area or the entire component.
  • components with a high geometric complexity can be produced in this way.
  • a disadvantage of the known generative manufacturing process is the fact that components can usually only be made from a single component material. Accordingly, components that consist of two or more subregions for additional functional integration, can not be made or only with great effort, since a change of the component material during manufacture is problematic.
  • the object of the present invention is to provide a method which enables a more flexible production of at least one component with two or more subregions.
  • Another object of the invention is to provide a corresponding component which consists of two or more subregions.
  • a first aspect of the invention relates to a method for producing at least one component, in particular a component of a turbomachine.
  • at least the steps a) generative production of at least a first portion of the component from a solidified by a selective beam melting and / or jet sintering powder, b) providing at least a second portion of the component, c) arranging the second portion of the first portion and d) welding the first portion to the second portion by means of the beam melting and / or jet sintering device.
  • the second subarea is not constructed together with the first subarea, but is manufactured separately and welded to the first subarea using the already existing selective beam melting and / or jet sintering device.
  • a large area and / or geometrically simple constructed second portion can be made separately and with the first portion, for example, smaller and / or geometrically more complex, can be welded.
  • the second subregion can be, for example, a sheet metal element.
  • a component platform allows in a simple way a layer-by-layer lowering by a predefined layer thickness, whereby the layered structure of the first portion can be performed correspondingly precise.
  • the unbonded powder primarily supports the first portion of the component.
  • the first portion can sink in the powder bed. Therefore, it may be advantageous to use one or more support structures for support. In the thermal production of large components or components with unfavorable cross-sectional jumps made of powder material support structures can also prevent distortion. Furthermore, heat can be dissipated via a support structure, for example, into a construction platform or other heat sinks. Likewise, it is possible that the first portion enters into a firm connection with the building platform during its manufacture. For better removal, the first subarea can therefore be constructed on a support structure which, for example, conveys the connection to a construction platform.
  • the support structure can basically also be generatively built or manufactured separately.
  • the first subarea is separated from the component platform and / or the support structure by a separation process, in particular by wire erosion.
  • the separation of the portion from the component platform or the support structure is preferably carried out only after completion of the component.
  • wire EDM allows a particularly fast and precise separation, since the spark generated thereby always jumps at the point at which the distance between the component and the wire used for wire EDM is minimal.
  • Wire erosion also allows all conductive materials to be processed, regardless of their hardness. Even with large material thickness extremely small cutting widths are possible.
  • the machined contours are also particularly dimensionally accurate and dimensionally accurate. Further advantages result if the generatively produced first subregion has at least one cavity with unconsolidated powder.
  • the first portion is constructed so as to have one or more cavities filled with non-solidified powder.
  • the powder in the cavity ensures the numerohaltig- speed of the first portion, this is particularly advantageous in the production of components, which should have at least one damping element, for example of Impulsverstimmern.
  • the powder in the cavity can act as cushioning.
  • the at least one cavity can in principle be closed or open towards at least one side, for example with respect to the construction direction upwards.
  • the first subregion comprises a bottom element and a chamber region for forming the at least one cavity, the bottom element and the chamber region being produced generatively in time in step a). Before production of the chamber area, a base element is inserted into a depression of the floor element.
  • the base element serves to stabilize the component structure.
  • the base element is made separately. This makes it possible to produce the component via a hybrid construction, in which the base member may consist of a different material than the first portion, in principle, identical materials for the first portion and the base member may be provided. Again, it is possible to produce the base element generatively or with the aid of deviating, that is to say non-generative, production methods, with the result that corresponding time and cost savings can be realized.
  • the base element may be a sheet metal element.
  • a contour of the depression of the base element of the first subregion corresponds to a contour of the base element, so that it can be arranged flush with the base element, preferably swapping or preventing it being twisted.
  • the at least one cavity is at least partially emptied before arranging the second portion in step c).
  • a partial emptying a simple optimization in the direction of a desired acoustic behavior or adaptation to a desired resonant frequency can be made. It is also possible to completely empty the at least one cavity, for example by suction of the unconsolidated powder. It can continue to do so be provided that a part or all of the non-solidified powder is removed from the space of the selective beam melting and / or jet sintering device, so that the first portion is powder-free in the selective beam melting and / or jet sintering device. This facilitates in particular the execution of step d), that is, the welding of the first and second partial area.
  • At least one damping element is arranged in the at least partially emptied cavity.
  • This also makes possible a simple optimization in the direction of a desired acoustic behavior or adaptation to a desired resonant frequency, as required instead of unconsolidated powder one or more damping elements, which have a defined geometry and may optionally consist of a different material in at least a cavity can be arranged.
  • a spherical damping element can be arranged whose diameter is a multiple of the mean particle diameter of the powder.
  • the second portion is arranged in step c) on the first portion such that it closes the at least one cavity of the first portion.
  • the second portion is formed as a cover or support structure for the at least one cavity of the first portion. It can also be provided that two or more cavities of the first subregion are closed by means of the second subregion.
  • the first subregion is produced in step a) with a depression into which the second subregion is used in step c). This simplifies both the arrangement in step c) and the welding in step d).
  • a contour of the depression corresponds to a contour of the second partial region, so that it can be arranged flush with the first partial region, preferably swapping or preventing rotation.
  • the second portion is welded circumferentially to the first portion in step d). As a result, a particularly reliable cohesive connection is ensured. If the second portion is used as the lid of one or more cavities, this additionally ensures that the one or more in the cavity (s) damping element (s) can not fall out.
  • a third subregion of the component is constructed generatively on the first and / or the second subregion.
  • at least one further (third) subregion of the component is constructed generatively, after the first and second subregions have been welded together.
  • the further (third) subregion comprises a cover element and a chamber region for forming the at least one cavity, wherein the cover element and the chamber region are produced generatively in temporal succession and before the production of the cover element a cover element into a depression of the chamber region for at least partial closure of the cavity is inserted.
  • the cover element also serves to reinforce the component structure.
  • the cover element is produced separately. This makes it possible, in turn, to produce the component via a hybrid construction, in which the cover element and / or base element can be made of a different material than the first and / or further (third) subarea, in principle also identical materials for the first subarea and the cover member and the base member may be provided.
  • the cover element may be a sheet metal element.
  • a contour of the depression of the chamber region of the third subregion corresponds to a contour of the covering element, see above that this can be arranged flush with the chamber area and preferably swapping or preventing rotation.
  • the at least one cavity in the chamber region of the third subregion is at least partially emptied before the covering element is arranged.
  • at least one damping element can be arranged in the cavity before arranging the cover element.
  • This facilitates in particular the welding of the cover element to the chamber region of the further (third) subregion.
  • damping elements which have a defined geometry and may optionally consist of a different material, again in at least one Cavity of the other (third) portion can be arranged.
  • a spherical damping element can be arranged whose diameter is a multiple of the mean particle diameter of the powder.
  • the cover is welded circumferentially with the chamber area.
  • a particularly reliable cohesive connection is ensured. If the cover is used as a cover of one or more cavities, this additionally ensures that the one or more in the cavity (s) damping element (s) can not fall out.
  • the second subregion, the base element and / or the covering element are produced by at least one production method from the group of generative production methods, prototypes, forming, separating and / or joining. This allows a high constructive freedom in the production of the second portion, the base member and the cover. It can also be provided that the second portion, the base member and / or the cover are made by a combination of two or more of said manufacturing processes.
  • At least two components in particular at least 400 components are produced in a construction job.
  • particularly high quantities of the component in the hybrid construction according to the invention can be produced, which can be realized corresponding time and cost savings.
  • a selective laser melting device and / or a selective laser sintering device and / or a selective electron beam melting device and / or a selective electron beam sintering device as the selective beam melting and / or beam sintering device.
  • partial regions can be produced whose mechanical properties correspond at least essentially to those of the component material.
  • a laser beam for example, a C0 2 laser, Nd: YAG laser, Yb fiber laser, diode laser or the like may be provided. It can also be provided that two or more high-energy or laser beams are used. Alternatively or additionally, one or more electron beams of high-energy beam can be used to produce components or subregions of virtually any geometry directly from design data.
  • a second aspect of the invention relates to a component, in particular for a turbomachine, which comprises at least one generatively produced first partial region and at least one second partial region, which is welded to the first partial region.
  • the component is produced in hybrid construction from at least one generatively produced first partial region and a second partial region, which is welded to the first partial region.
  • the component according to the invention can be made more flexible and faster than a corresponding component, which is exclusively generative or exclusively non-generatively manufactured.
  • the component is preferably obtainable and / or obtained by a method according to the first aspect of the invention.
  • the resulting advantages are described in the descriptions of the first aspect of the invention, advantageous embodiments of the first aspect of the invention are to be regarded as advantageous embodiments of the second aspect of the invention and vice versa.
  • the component is designed as Impulsverstimmer for a gas turbine.
  • the component may comprise at least one cavity in the first portion, in which at least one damping element is arranged. An opening of the cavity may be closed by means of the second portion.
  • the component can thus be used for the prevention or damping of resonances in a gas turbine, for example an aircraft engine, whereby both a noise development and a dynamic long-term behavior of appropriately equipped assemblies can be advantageously improved.
  • FIG. 1 shows a schematic lateral sectional view of a first subregion of a component generatively constructed on a support structure according to a first embodiment
  • FIG. 2 shows a schematic lateral sectional view of the first subregion according to FIG. 1, on which a second subregion is arranged;
  • FIG. 3 is a schematic side sectional view of the first portion of Figure 1, which is welded circumferentially with the second portion.
  • FIG. 4 shows a schematic lateral sectional view of the first and second partial area according to FIG. 3, on which a third partial area is constructed generatively, and FIG
  • Fig. 5 is a schematic sectional side view of a constructed of a plurality of subregions component according to a second embodiment.
  • FIG. 1 shows a schematic lateral sectional view of a first subregion 12 of a component 14 generatively mounted on a support structure 10 by means of a selective laser melting device (not shown) (see FIG.
  • the support structure 10 is in turn constructed in a manner known per se generatively on a component platform 16 of the selective laser melting device.
  • a laser melting or sintering device instead of a laser melting or sintering device, it is also possible to use an electron beam melting and / or sintering device.
  • the first partial area 12 comprises two cavities 18 which are open towards the top or in the direction of construction.
  • the powdered component material is completely sucked from the component platform 16 and thus also from the cavities 18.
  • the first portion 12 is powder-free in the selective laser melting device.
  • the said height h of about 2.80 mm is merely exemplary and that larger or smaller height parameters h can also be provided.
  • the empty cavities 18 are each equipped with a spherical damping element 20.
  • a second portion 22 is inserted into a recess 24 of the first portion 12 and closes the cavities 18.
  • the second portion 22 may thus also be referred to as a support structure or cover. This is shown in Fig.
  • the recess 24 has a depth d of about 0.2 mm corresponding to the thickness of the second portion 22.
  • the second portion 22 may in principle also be produced generatively. However, since the second portion 22 has a comparatively simple geometry, other production methods, such as prototyping, forming, separating and the like, individually and in any desired combination, are preferred.
  • the second portion 22 may consist of the same component material as the first portion 12. Alternatively, a different component material can be used.
  • the second partial region 22 is welded circumferentially to the first partial region 12. Welding takes place with the aid of the same selective laser melting device which was used to construct the first subarea 12 and which, depending on the type, can generate one or more laser beams 26.
  • FIG. 3 shows a schematic lateral sectional view of the first partial region 12, which is welded circumferentially to the second partial region 22 by means of a laser beam 26. The first and the second portion 12, 22 thus form a container for the damping elements 20th
  • a third partial region 28 with a height t of between approximately 0.4 mm and approximately 0.5 mm is constructed to be generative make final component 14.
  • FIG. 4 shows a schematic lateral sectional view of the first and second partial regions 12, 22, on which the third partial region 28 is constructed generatively.
  • the powder may be the same component material used to make the first portion 12. Alternatively, a different component material can be used.
  • the first and the third portion 12, 28 thus completely surround the second portion 22, so that the cavities 18 are closed particularly reliable.
  • the component 14 designed here as an impulse tuner for an aircraft engine is produced by wire eroding the support structure 10 from the component platform 16 separated.
  • the separation step takes place at a distance e of about 0.3 mm to the underside of the first portion 12th
  • FIG. 5 shows a schematic lateral sectional view of a component 14 constructed from a plurality of partial regions 12, 22, 28 in accordance with a second embodiment.
  • FIG. 5 features identical to those previously described in Figs. 1 to 4 are designated by identical reference numerals.
  • the illustrated component 14 is in turn a pulse tuner for a gas turbine.
  • the first subregion 12 here comprises a bottom element 12a and a chamber region 12b for forming the cavities 18.
  • the bottom element 12a and the chamber region 12b in step a) are produced successively generatively or additively.
  • a base element 30 is inserted into a depression 32 of the bottom element 12a.
  • the peripheral shape of the recess 32 corresponds to the outer contour of the bottom element 12a.
  • the base member 30 is formed as a sheet metal element and is attached to the bottom member 12a by means of stapling. Other mounting options are conceivable.
  • the chamber region 12b is at least partially built up on the base element 30.
  • each damping elements 20 are arranged.
  • the second portion 22 is inserted into the recess 24 of the first part member 12 and the chamber portion 12b and thereby closes the cavities 18.
  • the recess 24 in turn has a corresponding to the thickness of the second portion 22 depth of about 0th , 2 mm.
  • the second portion 22 may also be made generative in principle. However, since the second portion 22 has a comparatively simple geometry, other manufacturing methods such as prototyping, forming, cutting and the like, individually and in any combination, are preferred.
  • the second partial region 22 can consist of the same component material as the first partial region 12 or the bottom element 12a and the chamber region 12b. Alternatively, a different component material can be used. In the illustrated embodiment, the second portion 22 is formed as a sheet metal element. Furthermore, it can be seen that, by means of the selective beam melting and / or beam sintering device (not shown) according to step d), a third subregion 28 of the component 14 is constructed at least partially generatively on the first and the second subregions 12, 22. In particular, the third subregion 28 is constructed on the chamber region 12b and the second subregion 22. It can be seen that the third subregion 28 comprises a cover element 28a and a chamber region 28b for forming a plurality of cavities 18a.
  • the cover element 28a and the chamber region 28b are produced laterally successively generatively or additively.
  • a cover element 36 is inserted into a recess 34 of the chamber region 28b for closing the cavities 18a.
  • the cover element 36 can in turn be produced in an identical manner as the base element 30 and / or the second part element 22 separately generatively or non-generatively.
  • the cover 34 is formed as a sheet metal element.
  • the recess 34 in turn has a depth corresponding to the thickness of the cover 36 depth of about 0.2 mm.
  • damping elements 20a are arranged in the cavities 18a before arranging the cover element 36.
  • the design of the damping elements 20, 20a corresponds in this embodiment, the embodiments described in connection with the first exemplary embodiment.
  • the hybrid method according to the invention is also suitable for the parallel production of many components 14. For example, at a distance of about 1 mm to the respective neighboring part, about 400 to 550 or more components 14 per construction job can occur the component platform 16 are produced.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Optics & Photonics (AREA)
  • Composite Materials (AREA)
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Abstract

L'invention concerne un procédé de production d'un composant, en particulier d'un élément structural d'une turbomachine. Le procédé comprend au moins les étapes consistant à : a) réaliser par impression 3D au moins une première zone partielle (12) de l'élément structural (14) avec une poudre consolidée à l'aide d'un dispositif de fusion par faisceau et/ou de frittage par faisceau sélectif, b) prendre au moins une deuxième zone partielle (22) de l'élément structural (14), c) disposer la deuxième zone partielle (22) sur la première zone partielle (12), et d) souder la première zone partielle (12) à la deuxième zone partielle (22) à l'aide du dispositif de fusion par faisceau et/ou de frittage par faisceau. L'invention concerne également un élément structural correspondant.
PCT/DE2016/000426 2016-06-21 2016-12-02 Procédé de fabrication d'au moins un élément structural hybride pourvu de zones partielles réalisées par impression 3d WO2017220058A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016211068.3 2016-06-21
DE102016211068.3A DE102016211068A1 (de) 2016-06-21 2016-06-21 Verfahren zum Herstellen mindestens eines Bauteils

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WO2017220058A1 true WO2017220058A1 (fr) 2017-12-28

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Cited By (3)

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DE102018202198A1 (de) * 2018-02-13 2019-08-14 MTU Aero Engines AG Bauteil zum anordnen im gaskanal einer strömungsmaschine
EP3527864A1 (fr) * 2018-02-14 2019-08-21 Rolls-Royce plc Procédés de fabrication d'une soupape ou un élément utilisé pour former une soupape
EP3667019A1 (fr) * 2018-12-13 2020-06-17 MTU Aero Engines GmbH Agencement modulaire de corps d'impulsion, pluralité d'agencements, aube de turbine à gaz, utilisation d'un agencement modulaire de corps d'impulsion, et procédé pour fabriquer un agencement modulaire de corps d'impulsion

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EP3725435A1 (fr) * 2019-04-17 2020-10-21 Siemens Aktiengesellschaft Fabrication d'un objet métallique

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US2999669A (en) * 1958-11-21 1961-09-12 Westinghouse Electric Corp Damping apparatus
JP2000190086A (ja) * 1998-12-22 2000-07-11 Matsushita Electric Works Ltd 三次元形状造形物の製造方法および金型
US20140165381A1 (en) * 2011-06-21 2014-06-19 Technische Universität Darmstadt Method for producing a housing structure at least partially enclosing at least one component and housing structure produced by said method
FR3027243A1 (fr) * 2014-10-16 2016-04-22 Dcns Procede de fabrication additive d'une pale creuse de propulseur
US20160146041A1 (en) * 2014-11-24 2016-05-26 MTU Aero Engines AG Blade or vane for a turbomachine and axial turbomachine

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GB2459262B (en) * 2008-04-15 2010-09-22 Rolls Royce Plc Solid freeform fabricated damper
DE102010046579A1 (de) * 2010-09-25 2012-03-29 Mtu Aero Engines Gmbh Bauteil mit wenigstens einem Dämpfungselement und Verfahren zum Herstellen eines Bauteils mit wenigstens einem Dämpfungselement
DE102011008695A1 (de) * 2011-01-15 2012-07-19 Mtu Aero Engines Gmbh Verfahren zum generativen Herstellen eines Bauelements mit einer integrierten Dämpfung für eine Strömungsmaschine und generativ hergestelltes Bauelement mit einer integrierten Dämpfung für eine Strömungsmaschine
DE102014224442A1 (de) * 2014-11-28 2016-06-02 Siemens Aktiengesellschaft Verfahren zum Erzeugen eines Bauteils mit einer eine Vorzugsorientierung des Gefüges hervorrufenden Gefügetextur und Anlage für ein additives pulverbettbasiertes Herstellungsverfahren

Patent Citations (5)

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Publication number Priority date Publication date Assignee Title
US2999669A (en) * 1958-11-21 1961-09-12 Westinghouse Electric Corp Damping apparatus
JP2000190086A (ja) * 1998-12-22 2000-07-11 Matsushita Electric Works Ltd 三次元形状造形物の製造方法および金型
US20140165381A1 (en) * 2011-06-21 2014-06-19 Technische Universität Darmstadt Method for producing a housing structure at least partially enclosing at least one component and housing structure produced by said method
FR3027243A1 (fr) * 2014-10-16 2016-04-22 Dcns Procede de fabrication additive d'une pale creuse de propulseur
US20160146041A1 (en) * 2014-11-24 2016-05-26 MTU Aero Engines AG Blade or vane for a turbomachine and axial turbomachine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018202198A1 (de) * 2018-02-13 2019-08-14 MTU Aero Engines AG Bauteil zum anordnen im gaskanal einer strömungsmaschine
EP3527864A1 (fr) * 2018-02-14 2019-08-21 Rolls-Royce plc Procédés de fabrication d'une soupape ou un élément utilisé pour former une soupape
EP4215784A1 (fr) * 2018-02-14 2023-07-26 Rolls-Royce plc Procédés de fabrication d'une soupape ou d'un élément utilisé pour former une soupape
EP3667019A1 (fr) * 2018-12-13 2020-06-17 MTU Aero Engines GmbH Agencement modulaire de corps d'impulsion, pluralité d'agencements, aube de turbine à gaz, utilisation d'un agencement modulaire de corps d'impulsion, et procédé pour fabriquer un agencement modulaire de corps d'impulsion
US11306596B2 (en) 2018-12-13 2022-04-19 MTU Aero Engines AG Gas turbine blade impulse body module

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