DE10124398A1 - Applying a ceramic layer to a metallic base body comprises joining a metallic intermediate support having recesses with the base body, and subsequently applying the ceramic layer on the intermediate support - Google Patents
Applying a ceramic layer to a metallic base body comprises joining a metallic intermediate support having recesses with the base body, and subsequently applying the ceramic layer on the intermediate supportInfo
- Publication number
- DE10124398A1 DE10124398A1 DE10124398A DE10124398A DE10124398A1 DE 10124398 A1 DE10124398 A1 DE 10124398A1 DE 10124398 A DE10124398 A DE 10124398A DE 10124398 A DE10124398 A DE 10124398A DE 10124398 A1 DE10124398 A1 DE 10124398A1
- Authority
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- Prior art keywords
- base body
- ceramic layer
- metallic
- intermediate carrier
- intermediate support
- Prior art date
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Links
- 239000000919 ceramic Substances 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 claims abstract description 27
- 230000008569 process Effects 0.000 claims abstract description 13
- 238000003466 welding Methods 0.000 claims abstract description 8
- 238000009792 diffusion process Methods 0.000 claims abstract description 6
- 238000005245 sintering Methods 0.000 claims abstract description 3
- 238000005476 soldering Methods 0.000 claims abstract description 3
- 238000009413 insulation Methods 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 5
- 239000007921 spray Substances 0.000 claims description 4
- 238000005507 spraying Methods 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 44
- 239000000543 intermediate Substances 0.000 description 17
- 239000002184 metal Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 235000010627 Phaseolus vulgaris Nutrition 0.000 description 1
- 244000046052 Phaseolus vulgaris Species 0.000 description 1
- 239000002318 adhesion promoter Substances 0.000 description 1
- 239000012790 adhesive layer Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000001143 conditioned effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B9/047—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material made of fibres or filaments
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/74—Ceramic products containing macroscopic reinforcing agents containing shaped metallic materials
- C04B35/76—Fibres, filaments, whiskers, platelets, or the like
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
-
- 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
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/103—Metal fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/304—Insulating
-
- 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
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Ceramic Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Organic Chemistry (AREA)
- Metallurgy (AREA)
- Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Plasma & Fusion (AREA)
- Structural Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
- Ceramic Products (AREA)
Abstract
Description
Die Erfindung bezieht sich auf ein Verfahren zum Aufbringen einer keramischen Schicht auf einen metallischen Grundkörper sowie auf ein Wärmedämmungsschichtsystem mit einem metal lischen Grundkörper und einer keramischen Schicht.The invention relates to a method for application a ceramic layer on a metallic base as well as a thermal insulation layer system with a metal basic body and a ceramic layer.
Wärmedämmungsschichtsysteme der beschriebenen Art werden in einer Vielzahl von Anwendungsgebieten eingesetzt, bei spielsweise bei Fluggasturbinen, um im Bereich der Brennkam mer sowie im Bereich der Turbinenschaufeln die Temperatur metallischer Bauelemente zu senken und um die Thermoschock beständigkeit der metallischen Grundkörper zu erhöhen.Thermal insulation layer systems of the type described are in used in a variety of applications for example in the case of aircraft gas turbines, in the area of the combustion temperature and in the area of the turbine blades lower metallic components and to reduce the thermal shock increase the resistance of the metallic base body.
Die Zusammensetzung derartiger keramischer Schichten ist aus dem Stand der Technik ebenfalls vorbekannt.The composition of such ceramic layers is made of also known in the prior art.
Zur Auftragung beziehungsweise Befestigung derartiger keramischer Schichten sind die unterschiedlichsten Verfahren bekannt. So beschreibt beispielsweise die US-PS 5,866,271 ein Verfahren, bei welchem die Oberfläche des metallischen Grundkörpers beziehungsweise Substrats in spezieller Weise aufgerauht wird, um die Haftung der keramischen Schicht zu erhöhen. Es ist auch bekannt, sogenannte "bond coats" als Haftvermittler auf die Oberfläche des metallischen Grundkör pers aufzutragen.For application or attachment of such Ceramic layers are a wide variety of processes known. For example, US Pat. No. 5,866,271 a process in which the surface of the metallic Base body or substrate in a special way is roughened to increase the adhesion of the ceramic layer increase. It is also known as "bond coats" Adhesion promoter on the surface of the metallic base body to be applied personally.
Bei den aus dem Stand der Technik bekannten Verfahren er weist es sich als nachteilig, dass die Bindung zwischen der keramischen Schicht und dem metallischen Grundkörper bezie hungsweise der auf diesen aufgebrachten Haftschichten sehr schwach ist. Die Verbindung beruht größtenteils auf einer mechanischen Verklammerung zwischen der rauhen Oberfläche des metallischen Grundkörpers beziehungsweise der Haftschicht und der keramischen Schicht. Im Laufe der Zeit bildet sich in der Übergangszone zwischen der keramischen Schicht und dem metallischen Körper bei hohen Temperaturen und, bedingt durch die im Einsatz herrschende Atmosphäre, eine Oxydschicht, welche mit der Zeit wächst und zum Ablösen der keramischen Schicht führt. Die Wachstumsprozesse der Oxydschicht sind somit auch der bestimmende Faktor für die Lebensdauer des Wärmedämmungsschichtsystems.In the methods known from the prior art, he it proves disadvantageous that the bond between the ceramic layer and the metallic base the layers of adhesive applied to these very much is weak. The connection is largely based on one mechanical clinging between the rough surface of the metallic base body or Adhesive layer and the ceramic layer. Over time forms in the transition zone between the ceramic Layer and the metallic body at high temperatures and, due to the atmosphere in use, an oxide layer that grows with time and can be removed of the ceramic layer. The growth processes of Oxide layers are therefore also the determining factor for the Service life of the thermal insulation layer system.
Ein weiterer Nachteil liegt darin, dass auf Grund unter schiedlicher Wärmeausdehnungskoeffizienten an der Grenzfläche zwischen der keramischen Schicht und dem metal lischen Grundkörper sehr hohe Schubspannungen erzeugt werden können, die ebenfalls zum vorzeitigen Versagen des Wärmedäm mungsschichtsystems beitragen können. Die auftretenden Schubspannungen begrenzen auch die zulässige oder mögliche Dicke der keramischen Schicht.Another disadvantage is that due to under different coefficients of thermal expansion at the Interface between the ceramic layer and the metal very high shear stresses are generated can also cause the premature failure of the thermal insulation layer system. The occurring Shear stresses also limit the permissible or possible Thickness of the ceramic layer.
Der Erfindung liegt die Aufgabe zu Grunde, ein Wärmedäm mungsschichtsystem sowie ein Verfahren zu dessen Herstellung zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit unter Vermeidung der Nachteile des Standes der Technik eine lange Lebensdauer aufweisen.The invention is based on the object, a thermal insulation layer system and a method for its production to create, which with simple construction and simple, inexpensive to manufacture while avoiding the Disadvantages of the prior art are long life exhibit.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombina tionen der beiden unabhängigen Ansprüche gelöst, die jeweiligen Unteransprüche zeigen weitere vorteilhafte Aus gestaltungen der Erfindung.According to the invention, the task is achieved by the combination of features tion of the two independent claims solved respective sub-claims show further advantageous Aus designs of the invention.
Erfindungsgemäß ist hinsichtlich des Verfahrens somit vorge sehen, dass ein metallischer, mit Ausnehmungen versehener Zwischenträger mit dem Grundkörper verbunden wird und dass die keramische Schicht nachfolgend auf den Zwischenträger aufgebracht wird.According to the invention, the method is therefore preferred see that a metallic, recessed Intermediate carrier is connected to the base body and that the ceramic layer subsequently on the intermediate carrier is applied.
Hinsichtlich des Wärmedämmungsschichtsystems sieht die Er findung vor, dass auf den Grundkörper ein mit Ausnehmungen versehener Zwischenkörper aufgebracht ist, auf welchem die keramische Schicht aufgetragen ist.Regarding the thermal insulation layer system, he sees finding that on the base body with recesses provided intermediate body is applied, on which the ceramic layer is applied.
Durch die Erfindung ergeben sich eine Reihe erheblicher Vorteile.The invention results in a number of significant ones Benefits.
Durch die Verwendung eines mechanischen Zwischenträgers ist es möglich, eine sehr starke, verbesserte mechanische Ver klammerung zwischen dem metallischen Grundkörper und der keramischen Schicht zu erzielen. Hierdurch erhöht sich die Lebensdauer des Wärmedämmungsschichtsystems ganz erheblich. Die Gefahr, dass sich die keramische Schicht von dem metal lischen Grundkörper löst, von diesem abspringt oder dass sich im Übergangsbereich Spalten bilden, wird weitgehend eliminiert. Durch die Auswahl der Strukturgröße der Zwischenschicht, die bei Drahtgeweben in Mikrometerbereich liegen kann, können Mikrorisse gezielt in die Schicht eingebracht werden. Diese Mikrorisse bauen Spannungen ab, ohne zum Versagen der Schicht zu führen.By using a mechanical intermediate support it possible a very strong, improved mechanical ver bracketing between the metallic body and the ceramic layer. This increases the The service life of the thermal insulation layer system is very considerable. The danger of the ceramic layer becoming detached from the metal solves basic body, jumps off it or that gaps form in the transition area is largely eliminated. By selecting the structure size of the Intermediate layer, the wire mesh in the micrometer range micro cracks can be targeted into the layer be introduced. These micro cracks relieve tension, without causing the layer to fail.
Weiterhin ist es vorteilhaft, dass die, bei den aus dem Stand der Technik bekannten Systemen, scharf ausgeprägten Grenzflächen zwischen der keramischen Schicht und dem metal lischen Grundkörper entfallen. Hierdurch entfällt auch weit gehend das Problem der beim Stand der Technik auftretenden Schubspannungen, die durch die sehr unterschiedlichen physi kalischen Eigenschaften der keramischen Schicht und des me tallischen Grundkörpers bedingt sind. Erfindungsgemäß ergibt sich hierdurch eine wesentliche Verlängerung der Lebensdauer des Wärmedämmungsschichtsystems. Der Grund hierfür liegt un ter anderem darin, dass der Zwischenträger zu einer deutli chen Reduzierung des Spannungsniveaus führt. Die Schichtdicke wird durch die Haftfestigkeit begrenzt, so dass mit dieser verbesserten Zwischenschicht gegenüber dem Stand der Technik dickere und damit besser isolierende Schichten möglich sind. Furthermore, it is advantageous that the, in which from the Systems known in the art, sharply defined Interfaces between the ceramic layer and the metal basic body are eliminated. This also eliminates a lot going the problem of those encountered in the prior art Shear stresses caused by the very different physi Kalische properties of the ceramic layer and me taller base body are conditioned. According to the invention this significantly extends the lifespan of the thermal insulation layer system. The reason for this is un inter alia in that the intermediate carrier becomes a clear Chen reduction of the voltage level leads. The Layer thickness is limited by the adhesive strength, so that with this improved intermediate layer compared to the stand technology thicker and therefore better insulating layers possible are.
Ein weiterer, wesentlicher Vorteil der erfindungsgemäßen Ausgestaltung ist auch dadurch gegeben, dass hochbean spruchte keramische Schichten mit sehr viel preiswerteren Herstellungsverfahren aufgebracht werden können, beispiels weise mit einem Schlickerverfahren.Another essential advantage of the invention Design is also given by the high bean said ceramic layers with much cheaper Manufacturing processes can be applied, for example wise with a slip process.
In einer besonders günstigen Ausgestaltung der Erfindung ist vorgesehen, dass der Zwischenträger in Form eines Drahtgewe bes, eines Drahtgitters oder eines Drahtfilzes ausgestaltet ist. Die Gesamtdicke des Drahtgewebes, Drahtgitters oder Drahtfilzes sowie die Durchmesser der einzelnen Drähte kön nen in einfachster Weise den jeweiligen Einsatzbedingungen sowie der gewünschten Geometrie angepasst werden.In a particularly favorable embodiment of the invention provided that the intermediate carrier in the form of a wire mesh bes, a wire mesh or a wire felt designed is. The total thickness of the wire mesh, wire mesh or Wire felt and the diameter of the individual wires can in the simplest way to the respective operating conditions as well as the desired geometry.
Besonders vorteilhaft ist es, wenn der Zwischenträger aus einem Material gefertigt ist, welches dem Material des Grundkörpers ähnlich ist.It is particularly advantageous if the intermediate carrier is made of a material is made which is the material of the Basic body is similar.
Die Befestigung des Zwischenträgers an dem metallischen Grundkörper kann in unterschiedlichster Weise erfolgen, bei spielsweise durch Sintern, Löten oder Diffusionsschweißen.The attachment of the intermediate carrier to the metallic Base body can be done in many different ways for example by sintering, soldering or diffusion welding.
Der Zwischenträger kann erfindungsgemäß einschichtig ausge bildet sein, es ist jedoch auch möglich, diesen aus mehre ren, aufeinander gelegten Schichten herzustellen. Somit kann die Intensität der mechanischen Verklammerung in einfachster Weise an die jeweiligen Anwendungsbedingungen angepasst wer den.According to the invention, the intermediate carrier can have a single layer be formed, but it is also possible to multiply this other layers on top of each other. So can the intensity of mechanical bracing in the simplest Adapted to the respective application conditions the.
Die Aufbringung der keramischen Schicht auf den Zwischenträ ger kann beispielsweise mittels eines Sprayverfahrens oder mittels Schickerverfahrens erfolgen. In beiden Fällen wird der Hohlraum zwischen den einzelnen Gewebemaschen des Zwi schenträgers beziehungsweise dem in diesen ausgebildeten Ausnehmungen zuverlässig durch Keramikmaterial gefüllt. The application of the ceramic layer on the intermediate layers ger can for example by means of a spray process or by means of a fuss method. In both cases the cavity between the individual meshes of the Zwi Schenträgers or those trained in these Recesses reliably filled with ceramic material.
Hierdurch ergeben sich die bereits oben genannten Vorteile der besseren Verklammerung und eines weichen Übergangs, wo durch die Ausdehnungskoeffizienten und die hierdurch resul tierenden Schubspannungen günstig beeinflusst werden.This results in the advantages already mentioned above better bracketing and a smooth transition where by the expansion coefficient and the resultant shear stresses can be influenced favorably.
Bei Verwendung eines Sprayverfahrens können beispielsweise
folgende Parameter vorgesehen werden:
When using a spray process, the following parameters can be provided, for example:
Versuche, die unter Einhaltung der oben angegebenen Werte durchgeführt wurden, haben gezeigt, dass die Biegefestigkeit einer durch Plasmaspray erzeugten keramischen Schicht erheb liche Verbesserungen gegenüber einer keramischen Schicht aufweist, die ohne Verwendung eines Zwischenträgers gemäß dem Stand der Technik erzeugt wurde.Attempts that comply with the values given above have shown that the flexural strength a ceramic layer produced by plasma spray improvements over a ceramic layer has, according to without using an intermediate carrier the prior art was generated.
Im Folgenden wird die Erfindung anhand eines Ausführungsbei spiels in Verbindung mit der Zeichnung beschrieben.In the following, the invention is illustrated by means of an embodiment game described in connection with the drawing.
Dabei zeigtIt shows
Fig. 1 eine metallurgische Schliffansicht eines erfin dungsgemäß ausgestalteten Wärmedämmungsschichtsy stems. Fig. 1 is a metallurgical sectional view of a thermal insulation layer system designed according to the invention.
Die in Fig. 1 gezeigte metallurgische Schliffansicht zeigt zunächst im oberen und unteren Bereich eine Einbettmasse 4 beziehungsweise 5, die lediglich zur Erzeugung des Schliffes und zu dessen Präparation erforderlich ist.The metallurgical sectional view shown in FIG. 1 initially shows an investment compound 4 and 5 in the upper and lower region, which is only required to produce the section and to prepare it.
Erfindungsgemäß ist ein plattenförmiger metallischer Grund körper 2 vorgesehen. Auf diesen ist ein metallischer Zwi schenträger 3 aufgebracht. Der metallische Zwischenträger 3 ist, wie sich aus der Darstellung der Fig. 1 ergibt, in Form eines Drahtgitters oder Drahtgeflechtes ausgebildet. Die Be festigung an dem metallischen Grundkörper 2 erfolgt beispielsweise durch ein Diffusionsschweißverfahren (Diffu sionsschweißzone 6). Hierdurch wird der Zwischenträger 3 fest und einstückig mit dem metallischen Grundkörper 2 ver bunden. Die einzelnen Drähte bilden eine Vielzahl von Aus nehmungen 7, in welche Material einer keramischen Schicht 1 eingebracht ist. Es ergibt sich, dass die keramische Schicht 1 zusätzlich zu ihrer Haftung auf der Oberfläche der einzel nen Elemente des Zwischenträgers 3 durch das Einbringen in die Ausnehmungen 7 fest mechanisch verklammert ist.According to the invention, a plate-shaped metallic base body 2 is provided. On this a metallic inter mediate carrier 3 is applied. The metallic intermediate carrier 3 is, as can be seen from the illustration in FIG. 1, in the form of a wire mesh or wire mesh. The attachment to the metallic base body 2 is carried out, for example, by a diffusion welding process (diffusion welding zone 6 ). As a result, the intermediate carrier 3 is fixed and integral with the metallic base body 2 a related party. The individual wires form a plurality of recesses 7 , into which material a ceramic layer 1 is introduced. It follows that the ceramic layer 1 is clamped additionally fixed mechanically to their adhesion to the surface of the single NEN elements of the intermediate member 3 by the introduction into the recesses. 7
Die Erfindung ist nicht auf das gezeigte Ausführungsbeispiel beschränkt. Vielmehr ergeben sich im Rahmen der Erfindung vielfältige Abwandlungs- und Modifikationsmöglichkeiten.The invention is not based on the embodiment shown limited. Rather, there are within the scope of the invention diverse modification and modification options.
11
keramische Schicht
ceramic layer
22
metallischer Grundkörper
metallic body
33
Zwischenträger
subcarrier
44
Einbettmasse
investment
55
Einbettmasse
investment
66
Diffusionsschweißzone
Diffusion welding zone
77
Ausnehmung
recess
Claims (13)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10124398A DE10124398A1 (en) | 2001-05-18 | 2001-05-18 | Applying a ceramic layer to a metallic base body comprises joining a metallic intermediate support having recesses with the base body, and subsequently applying the ceramic layer on the intermediate support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10124398A DE10124398A1 (en) | 2001-05-18 | 2001-05-18 | Applying a ceramic layer to a metallic base body comprises joining a metallic intermediate support having recesses with the base body, and subsequently applying the ceramic layer on the intermediate support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE10124398A1 true DE10124398A1 (en) | 2002-11-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| DE10124398A Ceased DE10124398A1 (en) | 2001-05-18 | 2001-05-18 | Applying a ceramic layer to a metallic base body comprises joining a metallic intermediate support having recesses with the base body, and subsequently applying the ceramic layer on the intermediate support |
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| Country | Link |
|---|---|
| DE (1) | DE10124398A1 (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10357180A1 (en) * | 2003-12-08 | 2005-06-30 | Alstom Technology Ltd | Bonding of a non metallic material as a surface layer on a metal base using a profiled interface |
| DE102009011913A1 (en) | 2009-03-10 | 2010-09-16 | Rolls-Royce Deutschland Ltd & Co Kg | Thermal insulation layer system for use in gas turbine, comprises metallic adhesion-promoting layer, and ceramic thermal insulation layer applied on adhesion-promoting layer |
| US9151175B2 (en) | 2014-02-25 | 2015-10-06 | Siemens Aktiengesellschaft | Turbine abradable layer with progressive wear zone multi level ridge arrays |
| US9243511B2 (en) | 2014-02-25 | 2016-01-26 | Siemens Aktiengesellschaft | Turbine abradable layer with zig zag groove pattern |
| US9458763B2 (en) | 2011-11-04 | 2016-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Component and turbomachine having a component |
| US9908173B2 (en) | 2011-04-01 | 2018-03-06 | Rolls-Royce Deutschland & Co Kg | Method for producing a component, component and turbomachine having a component |
| US10189082B2 (en) | 2014-02-25 | 2019-01-29 | Siemens Aktiengesellschaft | Turbine shroud with abradable layer having dimpled forward zone |
| US10190435B2 (en) | 2015-02-18 | 2019-01-29 | Siemens Aktiengesellschaft | Turbine shroud with abradable layer having ridges with holes |
| US10196920B2 (en) | 2014-02-25 | 2019-02-05 | Siemens Aktiengesellschaft | Turbine component thermal barrier coating with crack isolating engineered groove features |
| US10408079B2 (en) | 2015-02-18 | 2019-09-10 | Siemens Aktiengesellschaft | Forming cooling passages in thermal barrier coated, combustion turbine superalloy components |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3036520A1 (en) * | 1979-09-28 | 1981-05-14 | Leuven Research & Development, 3000 Leuven | COMPOSITE MATERIAL FOR PROSTHESES |
| US4639388A (en) * | 1985-02-12 | 1987-01-27 | Chromalloy American Corporation | Ceramic-metal composites |
| DE19534194A1 (en) * | 1994-09-29 | 1996-06-05 | Tissu Rothrist Ag | Flat composite material for use as e.g. heat insulating material |
| US5866271A (en) * | 1995-07-13 | 1999-02-02 | Stueber; Richard J. | Method for bonding thermal barrier coatings to superalloy substrates |
-
2001
- 2001-05-18 DE DE10124398A patent/DE10124398A1/en not_active Ceased
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3036520A1 (en) * | 1979-09-28 | 1981-05-14 | Leuven Research & Development, 3000 Leuven | COMPOSITE MATERIAL FOR PROSTHESES |
| US4639388A (en) * | 1985-02-12 | 1987-01-27 | Chromalloy American Corporation | Ceramic-metal composites |
| DE19534194A1 (en) * | 1994-09-29 | 1996-06-05 | Tissu Rothrist Ag | Flat composite material for use as e.g. heat insulating material |
| US5866271A (en) * | 1995-07-13 | 1999-02-02 | Stueber; Richard J. | Method for bonding thermal barrier coatings to superalloy substrates |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10357180A1 (en) * | 2003-12-08 | 2005-06-30 | Alstom Technology Ltd | Bonding of a non metallic material as a surface layer on a metal base using a profiled interface |
| DE102009011913A1 (en) | 2009-03-10 | 2010-09-16 | Rolls-Royce Deutschland Ltd & Co Kg | Thermal insulation layer system for use in gas turbine, comprises metallic adhesion-promoting layer, and ceramic thermal insulation layer applied on adhesion-promoting layer |
| US9908173B2 (en) | 2011-04-01 | 2018-03-06 | Rolls-Royce Deutschland & Co Kg | Method for producing a component, component and turbomachine having a component |
| US9458763B2 (en) | 2011-11-04 | 2016-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Component and turbomachine having a component |
| US9920646B2 (en) | 2014-02-25 | 2018-03-20 | Siemens Aktiengesellschaft | Turbine abradable layer with compound angle, asymmetric surface area ridge and groove pattern |
| US9243511B2 (en) | 2014-02-25 | 2016-01-26 | Siemens Aktiengesellschaft | Turbine abradable layer with zig zag groove pattern |
| US9151175B2 (en) | 2014-02-25 | 2015-10-06 | Siemens Aktiengesellschaft | Turbine abradable layer with progressive wear zone multi level ridge arrays |
| US10189082B2 (en) | 2014-02-25 | 2019-01-29 | Siemens Aktiengesellschaft | Turbine shroud with abradable layer having dimpled forward zone |
| 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 |
| US10323533B2 (en) | 2014-02-25 | 2019-06-18 | Siemens Aktiengesellschaft | Turbine component thermal barrier coating with depth-varying material properties |
| US10190435B2 (en) | 2015-02-18 | 2019-01-29 | Siemens Aktiengesellschaft | Turbine shroud with abradable layer having ridges with holes |
| US10408079B2 (en) | 2015-02-18 | 2019-09-10 | Siemens Aktiengesellschaft | Forming cooling passages in thermal barrier coated, combustion turbine superalloy components |
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Effective date: 20120915 |