EP3731984A1 - Bauteil sowie verfahren zum herstellen eines bauteils mittels additiven fertigungsverfahren - Google Patents
Bauteil sowie verfahren zum herstellen eines bauteils mittels additiven fertigungsverfahrenInfo
- Publication number
- EP3731984A1 EP3731984A1 EP18832993.2A EP18832993A EP3731984A1 EP 3731984 A1 EP3731984 A1 EP 3731984A1 EP 18832993 A EP18832993 A EP 18832993A EP 3731984 A1 EP3731984 A1 EP 3731984A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- producing
- outer body
- additive manufacturing
- manufacturing process
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of 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
- 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
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/22—Manufacture essentially without removing material by sintering
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
-
- 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
- additive manufacturing processes various production methods are summarized, all of which have a three-dimensional structure.
- additive manufacturing processes are also referred to by the term “additive manufacturing” or “3D printing”.
- SLM selective laser melting
- SLS selective laser sintering
- the additive manufacturing processes are a fairly new production technique, which makes it possible to produce very complex geometries, which until now have been difficult or impossible to produce.
- the main disadvantage of additive manufacturing processes is the high production costs (currently approx. 2,000 euros per kilogram) and the long production times.
- the object of the present invention is therefore to provide a component which can be produced quickly and inexpensively by means of additive manufacturing processes. It is a further object of the invention to provide a method for making such a component.
- the component according to the invention comprising at least one Ren ren packing and a the inner filler at least partially enclosing the outer body, characterized as characterized by that the outer body is made by an additive pro duction process. Due to the fact that only the outer body is produced by an additive manufacturing process, the complete component does not have to be manufactured by means of additive manufacturing processes, which on the one hand significantly reduces the costs of the material and significantly reduces the manufacturing time on the other hand.
- the additive Heinrichsvon is used only for the production of the complex final shape of the component.
- the basic structure of the component can be pre-give by the inner filler and the inner packing can be made quickly and a fold by known methods.
- An embodiment of the invention provides that the materi alstor the outer body is only as thick as it is necessary for the formation of a given outer contour (final shape) and for the function of the component. As a result, the manufacturing costs and production time can be reduced to a minimum, without the functional limitations compared to a component which is completely made by an additive manufacturing process, must be accepted.
- a further embodiment of the invention provides that the inner filler body is produced by a conventional compassionsver, in particular by Giesen or by a machining process. Giesen or cutting manufacturing process provide a particularly simple, inexpensive and time-optimized way to produce the inner filler body.
- a further embodiment of the invention provides that the inner packing is formed in lightweight construction, in particular by egg ner honeycomb structure or a porous material.
- the inner packing is formed in lightweight construction, in particular by egg ner honeycomb structure or a porous material.
- the production also a weight-optimized component made light.
- the material can also be optimized with respect to other requirements, for example a vibration damping.
- a further embodiment of the invention provides that the inner filler body comprises an additional skeleton structure.
- the skeleton contour on the one hand simplifies the structure of the filling body and gives this additional strength.
- a further embodiment of the invention provides that the outer body is manufactured separately as a hollow body and connected by means of a joining method with the inner body.
- the outer body For the production of the outer body are in this particular powder bed process such as the SLM or the SLS.
- a further embodiment of the invention provides that the outer body is applied directly to the inner filler body by means of an additive manufacturing process. Free space methods for the additive production of the outer body are particularly suitable here.
- An embodiment of the invention provides that the component is a turbine blade, in particular a turbine blade egg ner steam turbine.
- Steam turbine blades have a com plex final contour and are therefore particularly well for additive manufacturing processes.
- FIG. 1 a first inventive component, in a side view
- FIG. 2 is a sectional view of the ge Service th in Figure 1 component along the line AA;
- FIG. 3 is a sectional view of a second inventions to the invention component, with an identical to Figure 1 outer contour, along the line AA of Figure 1;
- FIG. 4 a third component according to the invention in a side view, with an additional skeleton contour.
- FIG. 1 shows a first inventive component 1.
- the component 1 is a turbine blade, in particular a steam turbine blade.
- the turbine blade comprises an airfoil 5 and a blade root 6. From FIG. 2, the structure of the airfoil 5 can be seen.
- FIG. 2 shows a section along the line A - A in FIG. 1.
- the airfoil 5 comprises an inner filler body 2 and an outer body 3 at least partially surrounding the inner filler body 2.
- the inner filler body 2 may be formed separately or integrally with the blade root 6 ,
- the inner packing 2 is produced by means of a conventional manufacturing method, for example, by casting or by a machining process.
- the outer body 3 is made by an additive manufacturing process.
- the layer thickness of the outer body 3 is only as thick as is necessary for the formation of a predetermined outer contour / final shape and for the function of the component 1.
- the com plexer final shape of the turbine blade is thus registeredbil det by the addi tive manufacturing process and the outer body 3.
- the inner packing 2 can be made in a simple and cost-effective manner. There are no high demands on the shape and surface quality.
- the manufacturing process can be significantly shortened by means of the additive manufacturing process, since only the final shape by the additive Manufacturing process is to train. As a result, the material requirements and the material costs for the additive pro duction process are considerably reduced.
- the manufacture of the turbine blades fel by means of the additive manufacturing process for the first time economically and competitive with the previously conventionally manufactured components.
- FIG. 3 shows a third component according to the invention in a side view, with an additional skeleton contour.
- the inner packing 2 is made in lightweight construction.
- Lightweight construction can be formed for example by means of a honeycomb structure or by means of a porous material.
- the material for the inner packing 2 can also be selected according to further criteria and requirements, so for example, the vibration damping by a suitable choice from the material for the inner packing 2 positive be influenced be.
- Figure 4 shows a further embodiment of a turbine nenschaufel in a partial section outbreak).
- the inner filling body 2 has an additional skeleton structure 4, which is formed integrally with the blade root 6 in the embodiment.
- the skeleton structure 4 facilitates the formation of the inner filler body 2 and additionally ensures Sta stabilization of the packing 2.
- the outer body 3 encloses the inner packing 2 in the region of the blade 5.
- the outer body 3 is made by an additive compassionsver drive.
- the layer thickness of the outer body 3 is preferably only as thick as that for the formation of a predetermined
- a first method for producing the turbine blade provides that initially the inner filler 2 is formed.
- the inner filler body 2 may comprise the blade root 6 or the two components are formed as separate components and are then connected together.
- the outer body 3 is applied directly to the inner filling body 2 by means of an additive manufacturing process.
- the application of the outer body 3 on the inner packing 2 can be done in particular with any known free space method such as build-up welding or cold gas spraying.
- the outer shape of the turbine blade 5 isaded det by the additive manufacturing process.
- the inner packing 2 can be formed in a conventional manner, for example, by casting or a machining process or in lightweight construction, for example by a honeycomb structure or by a porous material.
- a second method for producing the turbine blade of the outer body 3 is first prepared separately as a hollow body and then connected by means of a Fügeverfah rens with the filler body 2.
- the manufacture of the sepa rate hollow body can preferably be carried out in the powder bed process, for example, the SLM or SLS. Since when Entachid gene of the outer body 3 with the filler 2 no high temperatures occur, this method is also suitable for Guangematerialien heat sensitive.
- the invention provides that the additive manufacturing process is used only for the manufacture of the complex final shape and that the basic structure of the component is realized by an inner filler body. This can be produced quickly, easily and inexpensively. As a result, the production costs are significantly reduced and the production significantly reduced verrin.
- the properties of the component can be added. For example, be optimized in terms of weight and vibration damping.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Composite Materials (AREA)
- Architecture (AREA)
- General Engineering & Computer Science (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102018202685.8A DE102018202685A1 (de) | 2018-02-22 | 2018-02-22 | Bauteil sowie Verfahren zum Herstellen eines Bauteils mittels additiven Fertigungsverfahren |
| PCT/EP2018/084895 WO2019161959A1 (de) | 2018-02-22 | 2018-12-14 | Bauteil sowie verfahren zum herstellen eines bauteils mittels additiven fertigungsverfahren |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EP3731984A1 true EP3731984A1 (de) | 2020-11-04 |
Family
ID=65010714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP18832993.2A Withdrawn EP3731984A1 (de) | 2018-02-22 | 2018-12-14 | Bauteil sowie verfahren zum herstellen eines bauteils mittels additiven fertigungsverfahren |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP3731984A1 (de) |
| DE (1) | DE102018202685A1 (de) |
| WO (1) | WO2019161959A1 (de) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19903436A1 (de) * | 1999-01-29 | 2000-08-24 | Fraunhofer Ges Forschung | Verfahren zur Herstellung dreidimensionaler Formkörper |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1130285A (en) * | 1967-05-05 | 1968-10-16 | Rolls Royce | Method of making an aerofoil shaped blade for a fluid flow machine |
| EP2522810A1 (de) * | 2011-05-12 | 2012-11-14 | MTU Aero Engines GmbH | Verfahren zum generativen Herstellen eines Bauteils, insbesondere eines Verdichterschaufelelements, sowie ein derartiges Bauteil |
| WO2015058043A1 (en) * | 2013-10-18 | 2015-04-23 | United Technologies Corporation | Multiple piece engine component |
| DE102014220787A1 (de) * | 2014-10-14 | 2016-04-14 | Siemens Aktiengesellschaft | Gasturbinenbauteil mit Innenmodul und Verfahren zu seiner Herstellung unter Verwendung von Selektivem Laserschmelzen |
| EP3028793A1 (de) * | 2014-12-04 | 2016-06-08 | Siemens Aktiengesellschaft | Verfahren zur Herstellung einer Laufschaufel |
| US9982684B2 (en) * | 2015-08-07 | 2018-05-29 | General Electric Company | Hybrid metal compressor blades |
| DE102016203680A1 (de) * | 2016-03-07 | 2017-09-07 | Siemens Aktiengesellschaft | Vorrichtung zur Durchführung eines Selective Laser Melting Prozesses sowie damit hergestelltes Bauteil |
-
2018
- 2018-02-22 DE DE102018202685.8A patent/DE102018202685A1/de not_active Withdrawn
- 2018-12-14 WO PCT/EP2018/084895 patent/WO2019161959A1/de not_active Ceased
- 2018-12-14 EP EP18832993.2A patent/EP3731984A1/de not_active Withdrawn
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19903436A1 (de) * | 1999-01-29 | 2000-08-24 | Fraunhofer Ges Forschung | Verfahren zur Herstellung dreidimensionaler Formkörper |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102018202685A1 (de) | 2019-08-22 |
| WO2019161959A1 (de) | 2019-08-29 |
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