DE102005050873A1 - Process to manufacture a ceramic-coated gas turbine engine blade incorporating a regular array of surface irregularities - Google Patents
Process to manufacture a ceramic-coated gas turbine engine blade incorporating a regular array of surface irregularities Download PDFInfo
- Publication number
- DE102005050873A1 DE102005050873A1 DE102005050873A DE102005050873A DE102005050873A1 DE 102005050873 A1 DE102005050873 A1 DE 102005050873A1 DE 102005050873 A DE102005050873 A DE 102005050873A DE 102005050873 A DE102005050873 A DE 102005050873A DE 102005050873 A1 DE102005050873 A1 DE 102005050873A1
- Authority
- DE
- Germany
- Prior art keywords
- surface structure
- component
- elevations
- coating
- depressions
- 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.)
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
Die Erfindung betrifft ein Verfahren zur Herstellung einer durch Rissbildung segmentierten Beschichtung, insbesondere einer Keramikschicht auf einem metallischen, wärmebelasteten Bauteil sowie ein nach dem Verfahren hergestelltes Bauteil mit segmentierter Beschichtung.The The invention relates to a process for producing a by cracking segmented coating, in particular a ceramic layer on a metallic, heat-loaded Component and a manufactured by the process component with segmented Coating.
Es ist bekannt, die Oberfläche von metallischen Bauteilen mit einer keramischen Beschichtung zu versehen, um dadurch die Eigenschaften des Bauteils bzw. des für das Bauteil verwendeten Materials zu beeinflussen. Beispielsweise werden bestimmte metallische Komponenten von Flugtriebwerken, wie Turbinenschaufeln, die einer hohen thermischen Belastung ausgesetzt sind, mit einer plasmagespritzten keramischen Wärmedämmschicht ausgebildet, um die Turbine bei möglichst hohen Temperaturen betreiben zu können bzw. die betreffenden Bauelemente vor einer zu hohen Wärmebelastung und den damit verbunden negativen Auswirkungen auf die Material- bzw. Bauteileigenschaften zu schützen. Die Verwendung von mit einer keramischen Beschichtung versehenen Bauteilen bei hohen Temperaturen bereitet jedoch insofern Schwierigkeiten, als die Beschichtung aufgrund ihres begrenzten Wärmedehnverhaltens gegenüber dem metallischen Substrat beschädigt werden oder abplatzen kann und das Bauteil seine Funktion nicht mehr erfüllen kann und ausgetauscht werden muss. Zwar verfügen die keramischen Schichten infolge ihrer typischerweise mikrorissigen Struktur über eine gewisse Deh nungstoleranz, die jedoch bei einer sehr hohen thermischen Belastung und demzufolge größeren Schichtdicken nicht mehr ausreicht, um eine Beschädigung der Beschichtung dauerhaft zu verhindern.It is known, the surface of metallic components with a ceramic coating too provided to thereby the properties of the component or of the component used material to influence. For example, certain metallic components of aircraft engines, such as turbine blades, which are exposed to a high thermal load, with a plasma-sprayed ceramic thermal barrier coating, to the turbine if possible To be able to operate at high temperatures or the relevant Components against excessive heat load and the associated negative effects on the material or to protect component properties. The use of provided with a ceramic coating Components at high temperatures, however, presents difficulties in that as the coating due to their limited Wärmedehnverhaltens over the damaged metallic substrate can or can flake off and the component does not function can fulfill more and needs to be replaced. Although the ceramic layers have due to their typically microcracked structure via a certain expansion tolerance, but at a very high thermal Load and consequently larger layer thicknesses is no longer sufficient to permanently damage the coating to prevent.
Um
die Lebensdauer der keramischen Beschichtung zu erhöhen, ist
es weiterhin bekannt, durch bestimmte Verfahrensparameter bei der
Herstellung der keramischen Beschichtung so genannte Segmentierungsrisse
in der Keramikschicht zu erzeugen. Solche Segmentierungsrisse bilden
sich aus, wenn die Temperatur sowohl der aufgespritzten Keramikpartikel
als auch des Substrats sehr hoch ist. Beim Abkühlen der Schichten von der
Temperatur der Schmelzphase auf die Substrattemperatur treten Zugspannungen
auf, die zur Rissbildung und einer Segmentierung der Beschichtung
führen.
Die Aufteilung der keramischen Beschichtung in durch diese bewusste
Rissbildung getrennte Segmente hat ein verbessertes Dehnungsverhalten
zur Folge. Die Herstellung einer in der oben beschriebenen Art durch Rissbildung
segmentierten keramischen Beschichtung wird beispielsweise in der
Die zuvor beschriebene segmentierte Ausbildung der keramischen und über den Haftvermittler fixierten keramischen Beschichtung ist jedoch insofern nachteilig, als deren Eigenschaften örtlichen Schwankungen unterliegen, das heißt, es treten lokale Spannungsüberhöhungen auf, die zu einer Schädigung der Keramikschicht führen und damit deren Lebensdauer begrenzen.The previously described segmented formation of the ceramic and over the Adhesion promoter fixed ceramic coating is disadvantageous, however, insofar as their characteristics local variations subject, that is, there are local voltage peaks, the damage lead the ceramic layer and thus limit their life.
Der Erfindung liegt die Aufgabe zugrunde, eine durch Rissbildung segmentierte Keramikbeschichtung auf einem metallischen Substrat so auszubilden, dass deren lange Lebensdauer gewährleistet ist, sowie ein Verfahren zur Herstellung der Keramikschicht auf dem Substrat anzugeben.Of the Invention is based on the object segmented by cracking To form a ceramic coating on a metallic substrate that ensures their long life is, as well as a method for producing the ceramic layer indicate the substrate.
Erfindungsgemäß wird die Aufgabe mit einem Verfahren gemäß den Merkmalen des Patentanspruchs 1 und einem gemäß den Merkmalen des Patentanspruchs 15 ausgebildeten Bauteil gelöst. Weitere Merkmale und vorteilhafte Weiterbildungen der Erfindung sind in den Unteransprüchen angegeben.According to the invention Task with a method according to the features of claim 1 and one according to the features of the claim 15 trained component solved. Further features and advantageous developments of the invention are in the subclaims specified.
Der wesentliche Erfindungsgedanke besteht in der Ausbildung einer definierten, regelmäßig angeordneten, gleichbleibend dimensionierten Oberflächenstruktur der zu beschichtenden Bauteiloberfläche, wobei während und nach dem Aufbringen der Beschichtung durch Plasmaspritzen unter bestimmten Prozessbedingungen eine von den in gleicher Dimensionierung und Anordnung vorgesehenen erhöhten Bereichen der Oberflächenstruktur ausgehende definierte Rissbildung in der Beschichtung initiiert wird, so dass in der Beschichtung eine auf der Gestaltung der Oberflächenstruktur basierende Vielzahl von in Form und Größe weitgehend übereinstimmenden Schichtsegmenten oder – säulen erzeugt wird. Die so ausgebildete Beschichtung weist über ihre gesamte Fläche eine homogene Spannungsverteilung mit geringen und gleichmäßigem Dehnungsverhalten auf. Das heißt, trotz unterschiedlicher Dehnung des Bauteils und eines auf diesem aufgebrachten keramischen Beschichtungsmaterials wird auch eine dicke keramische Schicht nicht zerstört, so dass eine lange Lebensdauer des beschichteten Bauteils gewährleistet ist.Of the essential concept of the invention consists in the formation of a defined, arranged regularly, Consistently dimensioned surface structure of the coated Component surface, while during and after applying the coating by plasma spraying under certain process conditions one of those in the same sizing and arrangement provided increased Areas of surface texture initiated defined cracking in the coating is initiated, so that in the coating one on the design of the surface texture based variety of largely identical in shape and size Layer segments or columns generated becomes. The thus formed coating has over its entire surface a homogeneous stress distribution with low and uniform elongation behavior. This means, despite different elongation of the component and one on this applied ceramic coating material is also a thick ceramic layer not destroyed, allowing a long life ensures the coated component is.
In Ausgestaltung der Erfindung kann die Oberflächenstruktur mit einer Zwischenschicht zur Haftvermittlung oder zum Korrosions- oder Oxidationsschutz abgedeckt sein.In Embodiment of the invention, the surface structure with an intermediate layer covered for adhesion or for corrosion or oxidation protection be.
Die Oberflächenstruktur wird entweder auf die Oberfläche des Bauteils aufgebracht, so dass in gleichem Abstand gleich große Erhöhungen oder Berge vorhanden sind, oder in die Oberfläche werden im Abstand und in der Tiefe übereinstimmende Vertiefungen eingearbeitet, wobei in diesem Fall die unbearbeiteten Oberflächenbereiche die erhöhten Bereiche darstellen.The surface structure is either applied to the surface of the component, so that in the same distance equally large elevations or mountains are present, or in the surface in the distance and in the depth matching recesses are incorporated, in which case the unprocessed surface areas represent the elevated areas.
In weiterer Ausgestaltung der Erfindung sind die Erhöhungen oder Vertiefungen so geformt, dass an bzw. in diesen Strukturen Hinterschneidungen ausgebildet sind und so eine feste – formschlüssige – Verbindung zwischen der Bauteiloberfläche und der Beschichtung gewährleistet ist.In Another embodiment of the invention, the elevations or Recesses shaped so that formed on or in these structures undercuts are a fixed - form-fitting - connection between the component surface and the coating guaranteed is.
Der Abstand zwischen den Erhöhungen/Vertiefungen ist so gewählt, dass möglichst viele Segmentierungsrisse pro Längeneinheit ausgebildet werden. Vorzugsweise beträgt der Abstand etwa 0,05 bis 2mm, während die Höhe der erhöhten Bereiche zwischen 0,02 und 1mm liegt.Of the Distance between the elevations / depressions is chosen that possible many segmentation cracks per unit length be formed. Preferably, the distance is about 0.05 to 2mm, while the height the heightened Ranges between 0.02 and 1mm.
Das Beschichtungsmaterial ist sprühgetrocknetes oder feines, geschmolzen gebrochenes Spritzpulver, das bei hohen Partikel- und Substrattemperaturen und hohen Partikelgeschwindigkeiten durch atmosphärisches Plasmaspritzen auf getragen wird. Es können aber auch Suspensionen oder Vorstufen des Beschichtungsmaterials (Precursor) aufgetragen werden, um poröse segmentierte Beschichtungen herzustellen.The Coating material is spray-dried or fine, molten broken spray powder, which at high Particle and substrate temperatures and high particle velocities by atmospheric Plasma spraying is carried on. But it can also suspensions or precursors of the coating material (precursor) are applied, around porous produce segmented coatings.
Ein gemäß dem erfindungsgemäßen Verfahren hergestelltes Bauteil, beispielsweise eine Turbinenschaufel mit keramischer Beschichtung, weist auf der Bauteiloberfläche regelmäßig angeordnete, übereinstimmend dimensionierte Erhöhungen bzw. Vertiefungen auf, wobei in der Keramikschicht Segmentierungsrisse ausgebildet sind, die von den erhöhten Bereichen der Oberflächenstruktur des Bauteils ausgehen und in der Keramikschicht eine Vielzahl von Schichtsegmenten oder -säulen erzeugen.One according to the method of the invention manufactured component, such as a turbine blade with ceramic coating, has on the component surface regularly arranged, coincident dimensioned elevations or depressions, wherein in the ceramic layer Segmentierungsrisse are formed by the raised areas of the surface structure go out of the component and in the ceramic layer a plurality of layer segments or pillars produce.
Ausführungsbeispiele
der Erfindung werden anhand der in den
Gemäß der in
Die
Oberflächenstruktur
In
den
Prinzipiell
ist das Aufbringen einer Zwischenschicht als Haftvermittler nicht
erforderlich, weil bereits die Oberflächenstruktur
Die
Herstellung der segmentierten keramischen Beschichtung
- 11
- Keramikschicht (Beschichtung)ceramic layer (Coating)
- 22
- Bauteil (Substrat)component (Substrate)
- 33
- Oberflächenstruktursurface structure
- 44
-
Erhöhungen von
3 Increases of3 - 55
- Hinterschneidungenundercuts
- 66
- Zwischenschichtinterlayer
- 77
- Segmentierungsrissesegmentation cracks
- 88th
-
Vertiefungen
von
3 Wells of3 - 99
- Keramische Schichtsegmenteceramic layer segments
Claims (17)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005050873.1A DE102005050873B4 (en) | 2005-10-21 | 2005-10-21 | Process for producing a segmented coating and component produced by the process |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005050873.1A DE102005050873B4 (en) | 2005-10-21 | 2005-10-21 | Process for producing a segmented coating and component produced by the process |
Publications (2)
Publication Number | Publication Date |
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DE102005050873A1 true DE102005050873A1 (en) | 2007-04-26 |
DE102005050873B4 DE102005050873B4 (en) | 2020-08-06 |
Family
ID=37905306
Family Applications (1)
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DE102005050873.1A Active DE102005050873B4 (en) | 2005-10-21 | 2005-10-21 | Process for producing a segmented coating and component produced by the process |
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Country | Link |
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EP2395129A1 (en) * | 2010-06-08 | 2011-12-14 | United Technologies Corporation | Ceramic coating arrangement and corresponding manufacturing method |
WO2012131100A1 (en) | 2011-04-01 | 2012-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component, component and turbomachine having a component |
FR2975023A1 (en) * | 2011-05-12 | 2012-11-16 | Peugeot Citroen Automobiles Sa | Producing a surface having thermal-spray coating, comprises forming patterns against undercut by melting and lifting local material of surface using laser/by laser welding, where surface is interior surface of barrel of cylinder casing |
DE102011077620A1 (en) * | 2011-06-16 | 2012-12-20 | Rolls-Royce Deutschland Ltd & Co Kg | Component, useful in turbomachine and aircraft engine, comprises metallic coating provided on metallic base material, where metallic coating comprises adhesion zone connected with the metallic base material and structure zone |
DE102011085801A1 (en) * | 2011-11-04 | 2013-05-08 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Component and turbomachine with a component |
EP2628816A1 (en) * | 2012-02-14 | 2013-08-21 | Siemens Aktiengesellschaft | Method for applying a heat insulation layer |
WO2014144152A1 (en) * | 2013-03-15 | 2014-09-18 | Rolls-Royce Corporation | Improved coating interface |
US20140302282A1 (en) * | 2011-11-14 | 2014-10-09 | Siemens Aktiengesellschaft | Layer system with a structured substrate surface and production process |
EP2857637A1 (en) * | 2013-10-01 | 2015-04-08 | Siemens Aktiengesellschaft | Turbine airfoil and corresponding method of manufacturing |
EP2998417A1 (en) * | 2014-09-19 | 2016-03-23 | Rolls-Royce plc | A method of applying a thermal barrier coating to a metallic article and a thermal barrier coated metallic article |
EP2987960A3 (en) * | 2014-08-06 | 2016-06-22 | United Technologies Corporation | Ceramic coating system and method |
WO2017084850A1 (en) * | 2015-11-19 | 2017-05-26 | Siemens Aktiengesellschaft | Segmented two-layered system |
US9713912B2 (en) | 2010-01-11 | 2017-07-25 | Rolls-Royce Corporation | Features for mitigating thermal or mechanical stress on an environmental barrier coating |
US10196920B2 (en) | 2014-02-25 | 2019-02-05 | Siemens Aktiengesellschaft | Turbine component thermal barrier coating with crack isolating engineered groove features |
US10221716B2 (en) | 2014-02-25 | 2019-03-05 | Siemens Aktiengesellschaft | Turbine abradable layer with inclined angle surface ridge or groove pattern |
US10408079B2 (en) | 2015-02-18 | 2019-09-10 | Siemens Aktiengesellschaft | Forming cooling passages in thermal barrier coated, combustion turbine superalloy components |
EP3611343A1 (en) | 2018-08-13 | 2020-02-19 | Rolls-Royce Deutschland Ltd & Co KG | Component comprising an adhesive structure for a turbomachine, method for producing a component with an adhesive structure for a turbomachine and turbomachine comprising a component with an adhesive structure |
US20200256206A1 (en) * | 2019-02-08 | 2020-08-13 | United Technologies Corporation | Divot pattern for thermal barrier coating |
DE102021202032A1 (en) | 2021-03-03 | 2022-09-08 | Aesculap Ag | Medical device and method for manufacturing a medical device |
US11686208B2 (en) | 2020-02-06 | 2023-06-27 | Rolls-Royce Corporation | Abrasive coating for high-temperature mechanical systems |
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WO2008153709A1 (en) * | 2007-05-22 | 2008-12-18 | Corning Incorporated | Method for bonding refractory ceramic and metal related application |
CN101827952B (en) * | 2007-05-22 | 2012-08-08 | 康宁股份有限公司 | Method for bonding refractory ceramic and metal related application |
US8852720B2 (en) * | 2009-07-17 | 2014-10-07 | Rolls-Royce Corporation | Substrate features for mitigating stress |
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EP2395129A1 (en) * | 2010-06-08 | 2011-12-14 | United Technologies Corporation | Ceramic coating arrangement and corresponding manufacturing method |
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DE102011006659A1 (en) | 2011-04-01 | 2012-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component, component and turbomachine with component |
WO2012131100A1 (en) | 2011-04-01 | 2012-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component, component and turbomachine having a component |
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DE102011077620A1 (en) * | 2011-06-16 | 2012-12-20 | Rolls-Royce Deutschland Ltd & Co Kg | Component, useful in turbomachine and aircraft engine, comprises metallic coating provided on metallic base material, where metallic coating comprises adhesion zone connected with the metallic base material and structure zone |
DE102011085801A1 (en) * | 2011-11-04 | 2013-05-08 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Component and turbomachine with a component |
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EP2589872A3 (en) * | 2011-11-04 | 2016-12-14 | Rolls-Royce Deutschland Ltd & Co KG | Component and turbo engine with such a component |
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