DE102010046579A1 - Component, preferably aircraft component, which is formed of powder to be solidified by energy radiation source, comprises cavity with solidified powder, which is not solidified by energy radiation source and for forming damping element - Google Patents
Component, preferably aircraft component, which is formed of powder to be solidified by energy radiation source, comprises cavity with solidified powder, which is not solidified by energy radiation source and for forming damping element Download PDFInfo
- Publication number
- DE102010046579A1 DE102010046579A1 DE102010046579A DE102010046579A DE102010046579A1 DE 102010046579 A1 DE102010046579 A1 DE 102010046579A1 DE 102010046579 A DE102010046579 A DE 102010046579A DE 102010046579 A DE102010046579 A DE 102010046579A DE 102010046579 A1 DE102010046579 A1 DE 102010046579A1
- Authority
- DE
- Germany
- Prior art keywords
- powder
- cavity
- component
- solidified
- energy radiation
- 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.)
- Ceased
Links
Images
Classifications
-
- 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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/32—Correcting- or balancing-weights or equivalent means for balancing rotating bodies, e.g. vehicle wheels
- F16F15/36—Correcting- or balancing-weights or equivalent means for balancing rotating bodies, e.g. vehicle wheels operating automatically, i.e. where, for a given amount of unbalance, there is movement of masses until balance is achieved
- F16F15/366—Correcting- or balancing-weights or equivalent means for balancing rotating bodies, e.g. vehicle wheels operating automatically, i.e. where, for a given amount of unbalance, there is movement of masses until balance is achieved using fluid or powder means, i.e. non-discrete material
-
- 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
- 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
- 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
-
- 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
- F01D5/005—Repairing methods or devices
-
- 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
-
- 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
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
- B29K2995/0037—Other properties
- B29K2995/0091—Damping, energy absorption
-
- 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
-
- 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
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Plasma & Fusion (AREA)
- Optics & Photonics (AREA)
- Architecture (AREA)
- Composite Materials (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
Die vorliegende Erfindung betrifft ein Bauteil mit wenigstens einem Dämpfungselement und ein Verfahren zum Herstellen bzw. Ausbilden eines Bauteils mit wenigstens einem solchen Dämpfungselement. Das Bauteil ist hierbei insbesondere schichtweise aus einem Pulver hergestellt, welches durch eine Energiestrahlung verfestigt wird, beispielweise mittels eines Laserstrahls oder eines Elektronenstrahls. Das Bauteil ist beispielsweise ein Schaufelelement eines Triebwerks, z. B. Flugzeugtriebwerks.The present invention relates to a component having at least one damping element and a method for producing or forming a component with at least one such damping element. In this case, the component is produced in particular in layers from a powder which is solidified by energy radiation, for example by means of a laser beam or an electron beam. The component is for example a blade element of an engine, for. B. aircraft engine.
Heutige Gehäuse werden konventionell mittels Gusstechnik oder Frästechnik hergestellt. Durch diese Herstellverfahren ergeben sich Einschränkungen, die sich auf das Design auswirken.Today's housings are conventionally produced by means of casting or milling technology. These manufacturing methods have limitations that affect the design.
Dämpfende Elemente können bisher nur unter großem Aufwand und weiteren Fertigungsschritten angebracht werden. Die Optimierung in Richtung eines guten akustischen Verhaltens und bezüglich der Langlebigkeit kann dabei nur über die konstruktive Anpassung der Resonanzfrequenzen oder den Anbau weiterer Elemente erfolgen.Damping elements can be installed only with great effort and other manufacturing steps. The optimization in the direction of a good acoustic behavior and in terms of longevity can be done only on the structural adaptation of the resonance frequencies or the cultivation of other elements.
Neben der Frästechnik und in Ergänzung zu der Gusstechnik ist des Weiteren aus dem Stand der Technik, wie er in der
Der Erfindung liegt nun die Aufgabe zugrunde, ein verbessertes Bauteil mit wenigstens einem Dämpfungselement, sowie ein Verfahren zum Herstellen eines solchen Bauteils bereitzustellen.The invention is based on the object to provide an improved component with at least one damping element, and a method for producing such a component.
Gemäß der Erfindung werden nun ein Bauteil sowie ein entsprechendes Verfahren zur Herstellung bzw. Ausbildung des Bauteils bereitgestellt.According to the invention, a component and a corresponding method for producing or forming the component are now provided.
Genauer gesagt wird ein Bauteil bereitgestellt, insbesondere ein Flugzeugbauteil, welches aus einem mittels einer Energiestrahlungsquelle zu verfestigenden Pulver ausgebildet ist, wobei das Bauteil wenigstens einen Hohlraum mit einem nicht durch die Energiestrahlungsquelle verfestigten Pulver zum Bilden eines Dämpfungselements aufweist.More specifically, a component is provided, in particular, an aircraft component formed of a powder to be solidified by means of an energy radiation source, the component having at least one cavity with a powder not solidified by the energy radiation source for forming a damping element.
Das Bauteil hat den Vorteil, dass der Hohlraum mit dem darin aufgenommenen Pulver ein Dämpfungselement bildet, welches beispielsweise Vibrationen dämpfen oder kompensieren kann. Dabei muss kein weiteres Fertigungsverfahren eingesetzt werden, um ein Dämpfungselement an dem Bauteil vorzusehen. Dies führt zu reduzierten Herstellungskosten und einem vereinfachten Herstellungsverfahren.The component has the advantage that the cavity with the powder received therein forms a damping element, which can damp or compensate for vibrations, for example. In this case, no further manufacturing process must be used to provide a damping element on the component. This leads to reduced production costs and a simplified manufacturing process.
Des Weiteren wird ein Verfahren bereitgestellt zum Ausbilden eines Bauteils, insbesondere eines Flugzeugbauteils, wobei das Verfahren die folgenden Schritte aufweist:
Ausbilden eines Bauteils aus einem mittels einer Energiestrahlungsquelle zu verfestigenden Pulver, und
Ausbilden des Bauteils mit wenigstens einem Hohlraum, mit einem nicht durch die Energiestrahlungsquelle verfestigten Pulver zum Bilden eines Dämpfungselements.Furthermore, a method is provided for forming a component, in particular an aircraft component, the method having the following steps:
Forming a component from a powder to be solidified by means of an energy radiation source, and
Forming the device having at least one cavity with a powder not solidified by the energy radiation source to form a damping element.
Das Verfahren hat den Vorteil, dass ein Dämpfungselement durch das Ausbilden des mit einem Pulver gefüllten Hohlraums bereitgestellt werden kann. Das Pulver wirkt in dem Hohlraum dabei als Dämpfung. Des Weiteren werden keine zusätzlichen Fertigungsschritte benötigt, um ein Bauteil mit einem Dämpfungselement zu versehen, wie das bisher im Stand der Technik der Fall war.The method has the advantage that a damping element can be provided by forming the cavity filled with a powder. The powder acts in the cavity as damping. Furthermore, no additional manufacturing steps are needed to provide a component with a damping element, as was the case in the prior art.
Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen sowie der Beschreibung unter Bezugnahme auf die Zeichnungen.Advantageous embodiments and modifications of the invention will become apparent from the dependent claims and the description with reference to the drawings.
In einer Ausführungsform ist der Hohlraumkern aus schmelzbarem Wachs. Dies ist besonders preiswert und kann beispielsweise auch so ausgebildet sein, dass es im Bereich von Raumtemperatur oder im Bereich der Betriebstemperatur des Bauteils geschmolzen oder im Wesentlichen geschmolzen vorliegt.In one embodiment, the lumen core is fusible wax. This is particularly inexpensive and can for example also be designed so that it is melted or essentially molten in the range of room temperature or in the range of the operating temperature of the component.
In einer weiteren Ausführungsform weist der geschlossene Hohlraum wenigstens eine verschlossene Öffnung auf zum zumindest teilweisen Entfernen von Pulver aus dem Hohlraum und gegebenenfalls teilweisen Wiederbefüllen des Hohlraums mit beispielsweise einem anderen Pulver. Im Anschluss an das Entleeren und/oder Befüllen wird dann die Öffnung verschlossen. Das Vorsehen der Öffnung hat den Vorteil, dass das Pulver bis zur Fertigstellung des Bauteils in diesem verbleiben kann und durch die Öffnung zumindest teilweise entfernt werden kann bevor die Öffnung später geschlossen wird.In a further embodiment, the closed cavity has at least one closed opening for at least partial removal of powder from the cavity and optionally partial refilling of the cavity with, for example, another powder. After emptying and / or filling, the opening is then closed. The provision of the opening has the advantage that the powder can remain in this until the completion of the component and through the Opening can be at least partially removed before the opening is closed later.
Die Erfindung wird nachfolgend anhand der in den schematischen Figuren der Zeichnungen angegebenen Ausführungsbeispiele näher erläutert. Es zeigen:The invention will be explained in more detail with reference to the exemplary embodiments indicated in the schematic figures of the drawings. Show it:
In
Das Bauteil
Das Gehäuse
Mittels der generative Fertigung können Bauteile, insbesondere im Rahmen des sog. Rapid Manufacturing oder auch dem sog. Rapid Prototyping hergestellt werden. Bei der generativen Fertigung werden Bauteile hierzu beispielsweise schichtweise durch Materialauftrag aufgebaut. Dabei wird bei den entsprechenden Verfahren, die als Electron Beam Melting (EBM), LaserCusing, Selective Laser Sintering (SLS), Selective Laser Melting (SLM) oder 3D-Printing bekannt sind, der hinzuzufügende oder aufzutragende Werkstoff/Werkstoffkombination in Pulverform verarbeitet. Das Pulver wird hierbei in einer Schicht auf eine Bauplattform oder einen Träger aufgetragen. Anschließend kann die Pulverschicht selektiv mittels einer Energiestrahlung, wie z. B. eines Laserstrahls oder Elektronenstrahls, verfestigt werden. Die Verfestigung der jeweiligen Pulverschicht erfolgt dabei normalerweise auf Basis von Geometriedaten des herzustellenden Bauteils. Dabei kann die Pulverschicht z. B. auch abgescannt und der zu einer entsprechenden Bauteilschicht gehörende Bereich der Pulverschicht mittels Energiestrahlung verfestigt werden. Durch Einwirken der Energiestrahlung schmilzt oder versintert das Pulver in diesem Bereich. Im Fall des 3D-Printings wird die Pulverschicht verfestigt, indem ein Binder selektiv in die zum Bauteil gehörenden Bereiche eingebracht wird. Anschließend kann die Bauplattform oder der Träger um eine Schichtdicke verfahren, z. B. abgesenkt werden. Daraufhin wird eine neue Pulverschicht darüber aufgetragen und wiederum verfestigt. Auf diese Weise wird Schicht für Schicht das Bauteil aufgebaut.By means of generative manufacturing components can be produced, in particular in the context of so-called. Rapid Manufacturing or the so-called. Rapid prototyping. In generative production, components for this purpose are built up, for example, in layers by material application. In the process known as Electron Beam Melting (EBM), LaserCusing, Selective Laser Sintering (SLS), Selective Laser Melting (SLM) or 3D Printing, the material / material combination to be added or applied is powdered. The powder is applied in this case in a layer on a building platform or a carrier. Subsequently, the powder layer can selectively by means of an energy radiation, such as. B. a laser beam or electron beam are solidified. The solidification of the respective powder layer is normally carried out on the basis of geometric data of the component to be produced. In this case, the powder layer z. B. also scanned and the belonging to a corresponding component layer region of the powder layer are solidified by energy radiation. The powder melts or sinters in this area as a result of the action of energy radiation. In the case of 3D printing, the powder layer is solidified by selectively introducing a binder into the component-associated areas. Subsequently, the construction platform or the carrier can be moved by a layer thickness, for. B. be lowered. Then a new layer of powder is applied over it and solidified again. In this way, the component is built layer by layer.
In
Das erfindungsgemäße Prinzip kann an beliebigen, dynamisch beanspruchten Bauteilen
In
Das Pulver
Das Pulver
Stall eines Hohlraumkerns
Es kann auch das gesamte Pulver
Dadurch, dass ein Teil des Pulvers
Bei dem zweiten Hohlraum
Das Schließen der Öffnung
Grundsätzlich ist es auch denkbar, das gesamte nicht verfestigte Pulver
Als Energiestrahlungsquelle
Statt einer Abstreifereinrichtung als Beschichtungseinrichtung
Zum Bestimmen der vorbestimmten Bauteilbereiche kann das Pulverbett außerdem wahlweise zusätzlich falls erforderlich entsprechend abgescannt werden mittels eines Scanners (nicht dargestellt).In addition, to determine the predetermined component areas, the powder bed can optionally additionally be correspondingly scanned by means of a scanner (not shown).
In
Dabei wird das Bauteil in einem Schritt S1 mit wenigstens einem Hohlraum ausgebildet. Das Bauteil und darunter die Hohlraumwände werden dabei, insbesondere schichtweise, aus einem mittels einer Energiestrahlung verfestigbaren Pulver hergestellt. Das Pulver in den Hohlräumen wird hierbei dagegen nicht mittels der Energiestrahlung verfestigt sondern verbleibt unverfestigt.In this case, the component is formed in a step S1 with at least one cavity. The component and below the cavity walls are made, in particular in layers, from a consolidatable by means of energy radiation powder. In contrast, the powder in the cavities is not solidified by the energy radiation but remains unconsolidated.
Zur Reduzierung des Pulvers wird in dem Schritt S1 als weiterer Schritt S2 wenigstens eine Öffnung in dem Hohlraum zum Entfernen von Pulver aus dem Hohlraum vorgesehen. Nach dem Herstellen des Bauteils in einem Schritt S3 wird ein Teil des Pulvers aus dem Hohlraum über die Öffnung entfernt. In einem Schritt S4 wird die Öffnung dann verschlossen, um den Hohlraum vollständig zu verschließen.In order to reduce the powder, in step S1, as a further step S2, at least one opening is provided in the cavity for removing powder from the cavity. After the component has been manufactured in a step S3, part of the powder is removed from the cavity via the opening. In a step S4, the opening is then closed to completely close the cavity.
Zusätzlich oder alternativ wird in dem Schritt S1 zum Reduzieren eines Teils des Pulvers in dem Hohlraum, in einem Schritt S2* ein Teil des Pulvers in dem Hohlraum durch einen Hohlraumkern ersetzt und anschließend der Hohlraum in einem Schritt S3* vollständig geschlossen. Der Hohlraumkern ist dabei aus einem leicht schmelzbaren Material, das sich z. B. mit dem Pulver verbinden kann aber nicht muss, und mit dem Pulver den Hohlraum völlig oder nicht völlig ausfüllen kann.Additionally or alternatively, in the step S1 for reducing a part of the powder in the cavity, in a step S2 * a part of the powder in the cavity is replaced by a cavity core and then the cavity is completely closed in a step S3 *. The hollow core is made of a fusible material that z. B. can connect to the powder but need not, and with the powder completely or not completely fill the cavity.
Füllen der geschmolzene Hohlraumkern und das Pulver den Hohlraum nicht vollständig aus, so kann das Pulver durch das Bewegen oder sogar Schütteln des Bauteils leicht gelöst werden.If the molten core and the powder do not completely fill the cavity, the powder can be easily released by moving or even shaking the component.
Der Hohlraumkern ist beispielsweise aus einem Wachs welches sich bei Raumtemperatur verflüssigt. Insofern kann beim Herstellen des Bauteils mittels einer Energiestrahlungsquelle zum Verfestigen des Pulvers in den Bauteilbereichen, bei der Verwendung eines solchen leicht schmelzbaren Kerns wahlweise zusätzliche eine Kühleinrichtung vorgesehen werden, um ein sofortiges Schmelzen des Wachskerns zu verhindern bzw. die Prozesskammer entsprechend kühl gehalten werden.The cavity core is for example made of a wax which liquefies at room temperature. In this respect, in the manufacture of the component by means of an energy radiation source for solidifying the powder in the component areas, when using such a fusible core optionally additional cooling means may be provided to prevent immediate melting of the wax core and the process chamber are kept correspondingly cool.
Obwohl die vorliegende Erfindung vorstehend anhand der bevorzugten Ausführungsbeispiele beschrieben wurde, ist sie darauf nicht beschränkt, sondern auf vielfältige Art und Weise modifizierbar. Insbesondere sind die zuvor beschriebenen Ausführungsbeispiele miteinander kombinierbar, insbesondere einzelne Merkmale davon. Die vorliegende Erfindung kann auf jede Art von Bauteil angewendet werden, welche mittels eines durch Energiestrahlung zu verfestigenden Pulvers herstellbar ist und welches mit wenigstens einem Dämpfungselement versehbar ist. Die Erfindung ist nicht auf zu dämpfende Flugzeugbauteile, wie Schaufelelemente beschränkt.Although the present invention has been described above with reference to the preferred embodiments, it is not limited thereto, but modified in many ways. In particular, those described above Embodiments combined with each other, in particular individual features thereof. The present invention can be applied to any type of component which can be produced by means of a powder to be solidified by energy radiation and which can be provided with at least one damping element. The invention is not limited to aircraft components to be damped, such as blade elements.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
- 1010
- Bauteilcomponent
- 1212
- Gehäusecasing
- 1414
- Hohlraumcavity
- 1616
- Pulverpowder
- 1818
- Dämpfungselementdamping element
- 2020
- Wand (Gehäusewand bzw. Hohlraumwand)Wall (housing wall or cavity wall)
- 2222
- Vorrichtungcontraption
- 2424
- Prozesskammerprocess chamber
- 2626
- Bauplattformbuilding platform
- 2828
- Rahmenframe
- 3030
- Beschichtungseinrichtungcoater
- 3232
- EnergiestrahlungsquelleEnergy radiation source
- 3434
- Hohlraumkerncavity core
- 3636
- Deckelcover
- 3838
- Öffnungopening
- 4040
- Bodenground
ZITATE ENTHALTEN IN DER BESCHREIBUNG QUOTES INCLUDE IN THE DESCRIPTION
Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.
Zitierte PatentliteraturCited patent literature
- DE 102007039035 B3 [0004] DE 102007039035 B3 [0004]
Claims (11)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102010046579A DE102010046579A1 (en) | 2010-09-25 | 2010-09-25 | Component, preferably aircraft component, which is formed of powder to be solidified by energy radiation source, comprises cavity with solidified powder, which is not solidified by energy radiation source and for forming damping element |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102010046579A DE102010046579A1 (en) | 2010-09-25 | 2010-09-25 | Component, preferably aircraft component, which is formed of powder to be solidified by energy radiation source, comprises cavity with solidified powder, which is not solidified by energy radiation source and for forming damping element |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102010046579A1 true DE102010046579A1 (en) | 2012-03-29 |
Family
ID=45804639
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102010046579A Ceased DE102010046579A1 (en) | 2010-09-25 | 2010-09-25 | Component, preferably aircraft component, which is formed of powder to be solidified by energy radiation source, comprises cavity with solidified powder, which is not solidified by energy radiation source and for forming damping element |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102010046579A1 (en) |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013163048A1 (en) | 2012-04-24 | 2013-10-31 | United Technologies Corporation | Airfoil with powder damper |
EP2724799A1 (en) * | 2012-10-25 | 2014-04-30 | Alstom Technology Ltd | Method for Manufacturing a Component Having a Damping Structure |
WO2015027064A1 (en) * | 2013-08-21 | 2015-02-26 | General Electric Company | Components having vibration dampers enclosed therein and method of forming such components |
EP2851146A1 (en) * | 2013-09-24 | 2015-03-25 | Siemens Aktiengesellschaft | Method for manufacturing a turbine blade and corresponding turbine blade |
EP2905097A3 (en) * | 2014-02-11 | 2015-10-07 | General Electric Company | Article produced by additive manufacturing |
FR3026034A1 (en) * | 2014-09-18 | 2016-03-25 | Snecma | PROCESS FOR PRODUCING A HOLLOW PIECE BY SELECTIVE FUSION OF POWDER |
FR3027243A1 (en) * | 2014-10-16 | 2016-04-22 | Dcns | PROCESS FOR THE ADDITIVE MANUFACTURE OF A HOLLOW PROPELLER BLADE |
EP2855963A4 (en) * | 2012-05-31 | 2016-04-27 | Aerojet Rocketdyne De Inc | Tuned damper member |
FR3029829A1 (en) * | 2014-12-10 | 2016-06-17 | Snecma | TEST, EXPERIMENTAL DEVICE AND METHOD FOR CHARACTERIZING POWDER FOR ADDITIVE MANUFACTURE |
WO2016111896A1 (en) * | 2015-01-05 | 2016-07-14 | Sikorsky Aircraft Corporation | Integrated vibration damper for additively manufactured structure and method |
EP3075471A1 (en) * | 2015-03-30 | 2016-10-05 | MTU Aero Engines GmbH | Method of production of a gas turbine housing section by additive manufacturing |
GB2546851A (en) * | 2015-10-27 | 2017-08-02 | Hamilton Sundstrand Corp | Powder removal |
DE102016211068A1 (en) * | 2016-06-21 | 2017-12-21 | MTU Aero Engines AG | Method for producing at least one component |
WO2018019850A1 (en) * | 2016-07-28 | 2018-02-01 | General Electric Technology Gmbh | A method of manufacturing a component and a component manufactured by the method |
EP3299098A1 (en) * | 2016-09-21 | 2018-03-28 | BAE Systems PLC | Improved additive layer manufacturing |
WO2018055345A1 (en) * | 2016-09-21 | 2018-03-29 | Bae Systems Plc | Improved additive layer manufacturing |
WO2019115886A1 (en) * | 2017-12-12 | 2019-06-20 | Safran Helicopter Engines | Vibration damper for a turbomachine rotor vane |
DE102018202198A1 (en) * | 2018-02-13 | 2019-08-14 | MTU Aero Engines AG | COMPONENT FOR ARRANGEMENT IN THE GAS CHANNEL OF A FLOW MACHINE |
DE102018002933A1 (en) * | 2018-04-11 | 2019-10-17 | Mtu Friedrichshafen Gmbh | Method for producing a turbocharger subassembly |
WO2019238951A1 (en) * | 2018-06-15 | 2019-12-19 | Safran Landing Systems | Method for producing a part with a cavity by additive manufacturing |
US10577940B2 (en) | 2017-01-31 | 2020-03-03 | General Electric Company | Turbomachine rotor blade |
US20200108551A1 (en) * | 2018-10-08 | 2020-04-09 | Rolls-Royce North American Technologies, Inc. | Damped articles and systems and techniques for forming damped articles |
EP3689500A1 (en) * | 2019-01-30 | 2020-08-05 | Siemens Aktiengesellschaft | Component, in particular for a thermal flow engine and method for producing such a component |
JP2021162184A (en) * | 2020-03-31 | 2021-10-11 | 三菱パワー株式会社 | Gas turbine combustor and method for manufacturing fuel nozzle |
EP3985277A1 (en) * | 2020-10-12 | 2022-04-20 | ArianeGroup SAS | Improved damping device for spacecraft and method for manufacturing the damping device |
US11420260B2 (en) * | 2020-03-31 | 2022-08-23 | Mitsubishi Heavy Industries, Ltd. | Method of manufacturing fabricated object |
US11654484B2 (en) | 2020-10-01 | 2023-05-23 | Ford Global Technologies, Llc | Method for manufacturing binder jet parts |
US11732366B2 (en) | 2016-02-15 | 2023-08-22 | Rem Technologies, Inc. | Chemical processing of additive manufactured workpieces |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007039035B3 (en) | 2007-08-17 | 2009-01-02 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Method for producing a component and use of the component produced by the method |
US20090258168A1 (en) * | 2008-04-15 | 2009-10-15 | Rolls-Royce Plc | Article and method of manufacture thereof |
-
2010
- 2010-09-25 DE DE102010046579A patent/DE102010046579A1/en not_active Ceased
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007039035B3 (en) | 2007-08-17 | 2009-01-02 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Method for producing a component and use of the component produced by the method |
US20090258168A1 (en) * | 2008-04-15 | 2009-10-15 | Rolls-Royce Plc | Article and method of manufacture thereof |
Cited By (43)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9181806B2 (en) | 2012-04-24 | 2015-11-10 | United Technologies Corporation | Airfoil with powder damper |
WO2013163048A1 (en) | 2012-04-24 | 2013-10-31 | United Technologies Corporation | Airfoil with powder damper |
EP2841704A4 (en) * | 2012-04-24 | 2015-04-29 | United Technologies Corp | Airfoil with powder damper |
EP2855963A4 (en) * | 2012-05-31 | 2016-04-27 | Aerojet Rocketdyne De Inc | Tuned damper member |
EP2724799A1 (en) * | 2012-10-25 | 2014-04-30 | Alstom Technology Ltd | Method for Manufacturing a Component Having a Damping Structure |
US9903434B2 (en) | 2013-08-21 | 2018-02-27 | General Electric Company | Components having vibration dampers enclosed therein and methods of forming such components |
WO2015027064A1 (en) * | 2013-08-21 | 2015-02-26 | General Electric Company | Components having vibration dampers enclosed therein and method of forming such components |
CN105473822A (en) * | 2013-08-21 | 2016-04-06 | 通用电气公司 | Components having vibration dampers enclosed therein and methods of forming such components |
JP2016528440A (en) * | 2013-08-21 | 2016-09-15 | ゼネラル・エレクトリック・カンパニイ | PARTS HAVING VIBRATION DAMPER ENTRYED IN THE SAME AND METHOD FOR FORMING THE PARTS |
EP3604739A1 (en) * | 2013-08-21 | 2020-02-05 | General Electric Company | Components having vibration dampers enclosed therein and method of forming such components |
US10987733B2 (en) | 2013-08-21 | 2021-04-27 | General Electric Company | Components having vibration dampers enclosed therein and methods of forming such components |
EP2851146A1 (en) * | 2013-09-24 | 2015-03-25 | Siemens Aktiengesellschaft | Method for manufacturing a turbine blade and corresponding turbine blade |
EP2905097A3 (en) * | 2014-02-11 | 2015-10-07 | General Electric Company | Article produced by additive manufacturing |
FR3026034A1 (en) * | 2014-09-18 | 2016-03-25 | Snecma | PROCESS FOR PRODUCING A HOLLOW PIECE BY SELECTIVE FUSION OF POWDER |
FR3027243A1 (en) * | 2014-10-16 | 2016-04-22 | Dcns | PROCESS FOR THE ADDITIVE MANUFACTURE OF A HOLLOW PROPELLER BLADE |
FR3029829A1 (en) * | 2014-12-10 | 2016-06-17 | Snecma | TEST, EXPERIMENTAL DEVICE AND METHOD FOR CHARACTERIZING POWDER FOR ADDITIVE MANUFACTURE |
WO2016111896A1 (en) * | 2015-01-05 | 2016-07-14 | Sikorsky Aircraft Corporation | Integrated vibration damper for additively manufactured structure and method |
EP3075471A1 (en) * | 2015-03-30 | 2016-10-05 | MTU Aero Engines GmbH | Method of production of a gas turbine housing section by additive manufacturing |
US10443445B2 (en) | 2015-03-30 | 2019-10-15 | MTU Aero Engines AG | Method for additive manufacturing of a gas turbine casing part |
US10220422B2 (en) | 2015-10-27 | 2019-03-05 | Hamilton Sundstrand Corporation | Powder removal |
GB2546851A (en) * | 2015-10-27 | 2017-08-02 | Hamilton Sundstrand Corp | Powder removal |
GB2546851B (en) * | 2015-10-27 | 2019-10-09 | Hamilton Sundstrand Corp | Method of powder removal from internal passages of additively manufactured items |
US11732366B2 (en) | 2016-02-15 | 2023-08-22 | Rem Technologies, Inc. | Chemical processing of additive manufactured workpieces |
DE102016211068A1 (en) * | 2016-06-21 | 2017-12-21 | MTU Aero Engines AG | Method for producing at least one component |
WO2018019850A1 (en) * | 2016-07-28 | 2018-02-01 | General Electric Technology Gmbh | A method of manufacturing a component and a component manufactured by the method |
WO2018055345A1 (en) * | 2016-09-21 | 2018-03-29 | Bae Systems Plc | Improved additive layer manufacturing |
EP3299098A1 (en) * | 2016-09-21 | 2018-03-28 | BAE Systems PLC | Improved additive layer manufacturing |
US10577940B2 (en) | 2017-01-31 | 2020-03-03 | General Electric Company | Turbomachine rotor blade |
WO2019115886A1 (en) * | 2017-12-12 | 2019-06-20 | Safran Helicopter Engines | Vibration damper for a turbomachine rotor vane |
CN111448365B (en) * | 2017-12-12 | 2023-02-28 | 赛峰直升机发动机公司 | Vibration damper for a turbine rotor blade |
CN111448365A (en) * | 2017-12-12 | 2020-07-24 | 赛峰直升机发动机公司 | Damper for a turbine rotor blade |
US11333027B2 (en) | 2017-12-12 | 2022-05-17 | Safran Helicopter Engines | Vibration damper for a turbomachine rotor vane |
DE102018202198A1 (en) * | 2018-02-13 | 2019-08-14 | MTU Aero Engines AG | COMPONENT FOR ARRANGEMENT IN THE GAS CHANNEL OF A FLOW MACHINE |
DE102018002933A1 (en) * | 2018-04-11 | 2019-10-17 | Mtu Friedrichshafen Gmbh | Method for producing a turbocharger subassembly |
US11370176B2 (en) | 2018-06-15 | 2022-06-28 | Safran Landing Systems | Method for producing a part with a cavity by additive manufacturing |
FR3082449A1 (en) * | 2018-06-15 | 2019-12-20 | Safran Landing Systems | PROCESS FOR PRODUCING A PART WITH CAVITY BY ADDITIVE MANUFACTURING |
WO2019238951A1 (en) * | 2018-06-15 | 2019-12-19 | Safran Landing Systems | Method for producing a part with a cavity by additive manufacturing |
US20200108551A1 (en) * | 2018-10-08 | 2020-04-09 | Rolls-Royce North American Technologies, Inc. | Damped articles and systems and techniques for forming damped articles |
EP3689500A1 (en) * | 2019-01-30 | 2020-08-05 | Siemens Aktiengesellschaft | Component, in particular for a thermal flow engine and method for producing such a component |
JP2021162184A (en) * | 2020-03-31 | 2021-10-11 | 三菱パワー株式会社 | Gas turbine combustor and method for manufacturing fuel nozzle |
US11420260B2 (en) * | 2020-03-31 | 2022-08-23 | Mitsubishi Heavy Industries, Ltd. | Method of manufacturing fabricated object |
US11654484B2 (en) | 2020-10-01 | 2023-05-23 | Ford Global Technologies, Llc | Method for manufacturing binder jet parts |
EP3985277A1 (en) * | 2020-10-12 | 2022-04-20 | ArianeGroup SAS | Improved damping device for spacecraft and method for manufacturing the damping device |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE102010046579A1 (en) | Component, preferably aircraft component, which is formed of powder to be solidified by energy radiation source, comprises cavity with solidified powder, which is not solidified by energy radiation source and for forming damping element | |
DE102007039035B3 (en) | Method for producing a component and use of the component produced by the method | |
DE102008012064B4 (en) | Method and device for producing a hybrid molding produced by a hybrid process and hybrid molding produced by the process | |
DE102008022946B4 (en) | Apparatus and method for applying powders or pastes | |
DE69910384T2 (en) | METHOD FOR THE PRODUCTION OF FIRE-RESISTANT MOLDED BODIES | |
EP3022008B1 (en) | Method for manufacturing a component and optical irradiation device | |
DE102008044759B4 (en) | Support for an aircraft structural component which can be produced using the selective laser melting method | |
EP3331688B1 (en) | Method for producing a three-dimensional object | |
DE102013223407A1 (en) | Apparatus and method for layering a three-dimensional object and unpacking the finished object | |
DE102007023152A1 (en) | Method for producing a casting, casting mold and casting produced therewith | |
DE112010002686T5 (en) | A method of manufacturing a three-dimensional molded article and a three-dimensional molded article produced by this method | |
EP2522810A1 (en) | Method for generative production of a component, in particular of a compressor blade, and such a component | |
DE4410046C2 (en) | Method and material for producing a three-dimensional object by sintering | |
EP3253514B1 (en) | Method and device for additively producing components, and components produced through said method | |
DE102015216802A1 (en) | Method for producing a capsule for hot isostatic pressing | |
EP3621758B1 (en) | Method for a component with a predetermined surface structure to be produced by additive manufacturing | |
DE102018203151A1 (en) | Method for producing a three-dimensional component | |
WO2019180095A1 (en) | Method for producing a casting mould for filling with melt and casting mould | |
DE102017201084A1 (en) | Process for additive production and coating apparatus | |
DE102015217469A1 (en) | Method and device for producing a three-dimensional object | |
DE102016211068A1 (en) | Method for producing at least one component | |
DE102016210356A1 (en) | Method and apparatus for providing a number of three-dimensional objects | |
DE102021105991A1 (en) | Process for the production of a three-dimensional component | |
AT15102U1 (en) | Process for the layered production of a three-dimensional hard metal body | |
AT523694B1 (en) | Process for the production of a shaped component |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
R002 | Refusal decision in examination/registration proceedings | ||
R003 | Refusal decision now final |
Effective date: 20120411 |