WO2008154940A1 - Method for repairing an area of a thermal insulation layer - Google Patents
Method for repairing an area of a thermal insulation layer Download PDFInfo
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- WO2008154940A1 WO2008154940A1 PCT/EP2007/005392 EP2007005392W WO2008154940A1 WO 2008154940 A1 WO2008154940 A1 WO 2008154940A1 EP 2007005392 W EP2007005392 W EP 2007005392W WO 2008154940 A1 WO2008154940 A1 WO 2008154940A1
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- WO
- WIPO (PCT)
- Prior art keywords
- mcraly
- component
- repair area
- film
- barrier coating
- 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
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Classifications
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- 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
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- 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
- C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
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- 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
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- 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
Definitions
- the invention relates to a method for repairing a region of a thermal barrier coating on a component that consists of an MCrAlY film deposited on the component.
- Thermal insulation layers for turbine blades made of nickel or cobalt superalloys in many cases comprise an MCrAlY adhesion promoter layer applied directly to the component surface and a ceramic layer lying thereon.
- the thermal barrier coating on the turbine blade can be damaged in some areas due to wear or impact of an object. In this case, it is essential to immediately repair the damaged area of the thermal barrier coating, otherwise the turbine blade will not be sufficiently protected from heat. It can then be damaged in its structure, ultimately leading to complete component failure.
- thermal barrier coating In order to repair the thermal barrier coating in the damaged area, according to a method generally known in the art, first the thermal barrier coating is completely removed, i. Both the ceramic layer and the underlying MCrAlY adhesion promoter layer are removed. Subsequently, in the repair area, first a new MCrAlY adhesion promoter layer on the
- junction between the old and the new ceramic is therefore weakened, which can lead to an undefined overall performance of the repaired thermal barrier coating and in the worst case to the spalling of the thermal barrier coating in the repair area.
- This object is achieved according to the invention in that the shape and size of the repair area is determined after the removal of the thermal barrier coating, an MCrAlY film is produced having the shape and size of the repair area, the MCrAlY film is placed completely over the repair area on the component, the MCrAlY film is applied. Heat-treated film for connection to the component and the side of the MCrAlY film facing away from the component is coated with a ceramic.
- the basic idea of the invention is therefore to determine the repair area in terms of shape and size after the thermal barrier coating has been removed therefrom. Subsequently, an MCrAlY film is produced which has the shape and size of the repair area. Then the MCrAlY film is placed on the component in such a way that it Repair area completely covered. In order to effect a connection of the MCrAlY film to the component, it is subjected to a heat treatment. Finally, the side of the MCrAlY film facing away from the component is coated with a ceramic.
- the shape and size of the repair area is determined by means of optical methods.
- optical methods especially photographic and in particular 3-D photographic methods are suitable.
- the required data regarding shape and size of the repair area can be determined easily, quickly and with high accuracy.
- MCrAlY films are commercially available in a wide variety of strengths. These can be quickly and with the highest precision cut to the required size with the aid of a laser.
- the MCrAlY film is subjected to a heat treatment, in particular in a vacuum oven, for connection to the component.
- the MCrAlY film can also be locally subjected to a heat treatment by induction.
- the ceramic can be sprayed onto the side of the MCrAlY foil facing away from the component.
- APS atmospheric plasma spraying
- a development of the invention provides that the thermal barrier coating in the repair area is removed mechanically, for example by abrading, chemically or electrochemically.
- the single figure shows a schematic representation of a turbine blade 1 with a blade platform 2 and an associated blade 3.
- the turbine blade 1 is provided on the surface with a thermal barrier coating 4, the latter consisting of an MCrAlY adhesion promoter layer applied directly to the turbine blade 1 and a ceramic layer lying thereon.
- the thermal barrier coating 4 is damaged on the blade platform 2 in a repair area 5.
- the thermal barrier coating 4 in the repair area 5 is completely removed, for example by abrading. Both the ceramic layer and the MCrAlY adhesion promoter layer are removed in the repair area 5.
- the shape and size of the repair area 5 is determined exactly. This can be done, for example, optically with the aid of a digital camera and a connected data processing system for the evaluation of the received camera data.
- an MCrAlY film 6 is then produced, which determines the exact shape and size of the Repair area 5 has.
- a freestanding MCrAlY film which has the same thickness as the MCrAlY Haftverraittler Anlagen be cut using a laser.
- the MCrAlY film 6 is then placed on the blade platform 2 so that it completely covers the repair area 5. It is subjected to a heat treatment in order to bond it to the surface of the blade platform 2.
- the entire turbine blade 1 can be heated with the MCrAlY film 6 in a vacuum oven.
- the blade platform 2 facing away from the MCrAlY film 6 is coated with a ceramic.
- a ceramic which is identical to the ceramic of the ceramic layer 6 is applied to the MCrAlY foil 6, for example by atmospheric plasma spraying.
- a portion of the newly applied ceramic layer can then be ground away, so that it is planar to the ceramic layer.
- a particular advantage of the method according to the invention is that the new MCrAlY layer can be applied in the repair area 5 without the risk of the ceramic layer being contaminated.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Inorganic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Ceramic Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Verfahren zur Reparatur eines Bereichs einer WärmedämmschichtMethod of repairing a portion of a thermal barrier coating
Die Erfindung betrifft ein Verfahren zur Reparatur eines Bereichs einer Wärmedämmschicht auf einem Bauteil, die aus einer auf dem Bauteil aufgebrachten MCrAlY-The invention relates to a method for repairing a region of a thermal barrier coating on a component that consists of an MCrAlY film deposited on the component.
Haftvermittlerschicht und einer darauf liegenden Keramikschicht besteht, bei dem die Wärmedämmschicht im Reparaturbereich entfernt wird.Adhesive layer and a ceramic layer thereon, in which the thermal barrier coating in the repair area is removed.
Bauteile, wie zum Beispiel Turbinenschaufeln von Gasturbinen, die in einer aggressiven Umgebung hohen Temperaturen ausgesetzt werden, sind häufig mit einer Wärmedämmschicht versehen, um sie zu schützen und ihre Lebensdauer zu erhöhen. Wärmedämmschichten für Turbinenschaufeln aus Nickel- oder Kobalt-Superlegierungen umfassen dabei in vielen Fällen eine direkt auf der Bauteiloberfläche aufgebrachte MCrAlY- Haftvermittlerschicht sowie eine auf dieser liegende Keramikschicht .Components such as turbine blades of gas turbines which are exposed to high temperatures in an aggressive environment are often provided with a thermal barrier coating to protect and increase their service life. Thermal insulation layers for turbine blades made of nickel or cobalt superalloys in many cases comprise an MCrAlY adhesion promoter layer applied directly to the component surface and a ceramic layer lying thereon.
Während des Betriebs der Gasturbine kann die Wärmedämmschicht auf der Turbinenschaufel durch Verschleiß oder Aufprall eines Objektes bereichsweise beschädigt werden. In diesem Fall ist es unerlässlich, den beschädigten Bereich der Wärmedämmschicht unverzüglich zu reparieren, da ansonsten die Turbinenschaufel nicht mehr ausreichend vor Hitze geschützt ist. Sie kann dann in ihrer Struktur beschädigt werden, was letztendlich zu einem vollständigen Bauteilversagen führt. -During operation of the gas turbine, the thermal barrier coating on the turbine blade can be damaged in some areas due to wear or impact of an object. In this case, it is essential to immediately repair the damaged area of the thermal barrier coating, otherwise the turbine blade will not be sufficiently protected from heat. It can then be damaged in its structure, ultimately leading to complete component failure. -
Um die Wärmedämmschicht im beschädigten Bereich zu reparieren, wird gemäß eines allgemein im Stand der Technik bekannten Verfahrens zunächst die Wärmedämmschicht vollständig entfernt, d.h. sowohl die Keramikschicht als auch die darunterliegende MCrAlY-Haftvermittlerschicht werden abgetragen. Anschließend müssen im Reparaturbereich zunächst eine neue MCrAlY-Haftvermittlerschicht auf derIn order to repair the thermal barrier coating in the damaged area, according to a method generally known in the art, first the thermal barrier coating is completely removed, i. Both the ceramic layer and the underlying MCrAlY adhesion promoter layer are removed. Subsequently, in the repair area, first a new MCrAlY adhesion promoter layer on the
Turbinenschaufel und dann auf dieser einen neuen Keramikschicht aufgebracht werden. Dabei ist es jedoch schwierig, beim Auftragen der neuen MCrAlY-Haftvermittler- schicht sicherzustellen, dass kein MCrAlY auf der noch vorhandenen Keramikschicht außerhalb des Reparaturbereichs abgeschieden wird. So gelangt selbst dann, wenn die Oberfläche der Keramikschicht vor dem Beschichtungsschritt abgedeckt wird, häufig trotzdem MCrAlY auf die senkrecht zur Bauteiloberfläche im Reparaturbereich liegenden Randbereiche der Keramikschicht. Wenn dann die neue Keramikschicht im Reparaturbereich aufgebracht wird, kann sich die neue Keramik nicht mit hinreichender Sicherheit mit der bereits auf dem Bauteil vorhandenen Keramikschicht verbinden. DieTurbine blade and then applied to this a new ceramic layer. However, it is difficult when applying the new MCrAlY adhesion promoter. ensure that no MCrAlY is deposited on the remaining ceramic layer outside the repair area. Thus, even if the surface of the ceramic layer is covered before the coating step, MCrAlY often still reaches the edge regions of the ceramic layer that are perpendicular to the component surface in the repair region. Then, when the new ceramic layer is applied in the repair area, the new ceramic can not connect with sufficient security with the already existing on the component ceramic layer. The
Verbindungsstelle zwischen der alten und der neuen Keramik ist daher geschwächt, was insgesamt zu einem Undefinierten Betriebsverhalten der reparierten Wärmedämmschicht und im schlimmsten Fall zum Abplatzen der Wärmedämmschicht im Reparaturbereich führen kann.Junction between the old and the new ceramic is therefore weakened, which can lead to an undefined overall performance of the repaired thermal barrier coating and in the worst case to the spalling of the thermal barrier coating in the repair area.
Es ist daher Aufgabe der vorliegenden Erfindung, ein Verfahren der eingangs genannten Art so weiter zu entwickeln, dass die neue MCrAlY-Haftvermittlerschicht im Reparaturbereich aufgebracht werden kann, ohne dass dabei Teile der Keramikschicht mit MCrAlY verunreinigt werden.It is therefore an object of the present invention to further develop a method of the aforementioned type such that the new MCrAlY adhesion promoter layer can be applied in the repair area without contaminating parts of the ceramic layer with MCrAlY.
Diese Aufgabe wird erfindungsgemäß dadurch gelöst, dass die Form und Größe des Reparaturbereichs nach der Entfernung der Wärmedämmschicht bestimmt, eine MCrAlY-Folie mit der Form und Größe des Reparaturbereichs hergestellt, die MCrAlY-Folie auf das Bauteil den Reparaturbereich vollständig bedeckend aufgelegt, die MCrAlY-Folie zur Anbindung an das Bauteil einer Wärmebehandlung unterzogen und die dem Bauteil abgewandte Seite der MCrAlY-Folie mit einer Keramik beschichtet wird.This object is achieved according to the invention in that the shape and size of the repair area is determined after the removal of the thermal barrier coating, an MCrAlY film is produced having the shape and size of the repair area, the MCrAlY film is placed completely over the repair area on the component, the MCrAlY film is applied. Heat-treated film for connection to the component and the side of the MCrAlY film facing away from the component is coated with a ceramic.
Grundgedanke der Erfindung ist also den Reparaturbereich in Form und Größe zu bestimmen, nachdem die Wärmedämmschicht in diesem entfernt worden ist. Anschließend wird eine MCrAlY- Folie hergestellt, die die Form und Größe des Reparaturbereiches aufweist. Dann wird die MCrAlY-Folie derart auf das Bauteil aufgelegt, dass sie den Reparaturbereich vollständig bedeckt. Um eine Anbindung der MCrAlY-Folie an das Bauteil zu bewirken, wird diese einer Wärmebehandlung unterzogen. Zuletzt wird die dem Bauteil abgewandte Seite der MCrAlY-Folie mit einer Keramik beschichtet .The basic idea of the invention is therefore to determine the repair area in terms of shape and size after the thermal barrier coating has been removed therefrom. Subsequently, an MCrAlY film is produced which has the shape and size of the repair area. Then the MCrAlY film is placed on the component in such a way that it Repair area completely covered. In order to effect a connection of the MCrAlY film to the component, it is subjected to a heat treatment. Finally, the side of the MCrAlY film facing away from the component is coated with a ceramic.
Bei dem erfindungsgemäßen Verfahren ist insbesondere vorteilhaft, dass eine Verunreinigung der auf dem Bauteil vorhandenen Keramikschicht während des Aufbringens der neuen MCrAlY-Schicht im Reparaturbereich ausgeschlossen ist.In the method according to the invention, it is particularly advantageous that contamination of the ceramic layer present on the component during the application of the new MCrAlY layer in the repair area is precluded.
Gemäß einer ersten Ausführungsform der Erfindung ist vorgesehen, dass die Form und Größe des Reparaturbereichs mit Hilfe optischer Methoden bestimmt wird. Dafür sind besonders fotografische und insbesondere 3 -D fotografische Methoden geeignet. Auf diese Weise können einfach, schnell und mit hoher Genauigkeit die benötigten Daten bezüglich Form und Größe des Reparaturbereichs ermittelt werden.According to a first embodiment of the invention it is provided that the shape and size of the repair area is determined by means of optical methods. For this purpose, especially photographic and in particular 3-D photographic methods are suitable. In this way, the required data regarding shape and size of the repair area can be determined easily, quickly and with high accuracy.
Es ist ebenfalls möglich, die MCrAlY-Folie mit Hilfe einesIt is also possible to use the MCrAlY film with the help of a
Lasers aus einer freistehenden MCrAlY-Folie auf die benötigte Form und Größe zuzuschneiden. MCrAlY-Folien sind in verschiedensten Stärken im Handel erhältlich. Diese können unter Zuhilfenahme eines Lasers schnell und mit höchster Präzision auf die benötigte Größe zugeschnitten werden.Cut laser from a freestanding MCrAlY film to the required shape and size. MCrAlY films are commercially available in a wide variety of strengths. These can be quickly and with the highest precision cut to the required size with the aid of a laser.
Gemäß einer weiteren Ausführungsform der Erfindung ist vorgesehen, dass die MCrAlY-Folie zur Anbindung an das Bauteil einer Wärmebehandlung, insbesondere im Vakuumofen unterzogen wird. Die MCrAlY-Folie kann auch lokal einer Wärmebehandlung durch Induktion unterzogen werden.According to a further embodiment of the invention, it is provided that the MCrAlY film is subjected to a heat treatment, in particular in a vacuum oven, for connection to the component. The MCrAlY film can also be locally subjected to a heat treatment by induction.
Die Keramik kann auf die auf dem Bauteil abgewandte Seite der MCrAlY-Folie aufgespritzt werden. Dabei ist insbesondere ein Auftragen durch atmosphärisches Plasmaspritzen (APS) vorteilhaft. Eine Weiterbildung der Erfindung sieht vor, dass die Wärmedämmschicht im Reparaturbereich mechanisch, beispielsweise durch Abschleifen, chemisch oder elektrochemisch entfernt wird.The ceramic can be sprayed onto the side of the MCrAlY foil facing away from the component. In particular, an application by atmospheric plasma spraying (APS) is advantageous. A development of the invention provides that the thermal barrier coating in the repair area is removed mechanically, for example by abrading, chemically or electrochemically.
Gemäß einer weiteren Ausführungsform der Erfindung ist vorgesehen, dass ein Bereich einer Wärmedämmschicht auf einer Turbinenschaufel repariert wird.According to a further embodiment of the invention it is provided that a region of a thermal barrier coating on a turbine blade is repaired.
Der Erfindung wird im Folgenden anhand einesThe invention will be described below with reference to a
Ausführungsbeispiels unter Bezugnahme auf die Zeichnung näher erläutert. In der Zeichnung zeigt die einzige Figur eine schematische Darstellung einer Turbinenschaufel 1 mit einer Schaufelplattform 2 und einem damit verbundenen Schaufelblatt 3.Embodiment explained in more detail with reference to the drawing. In the drawing, the single figure shows a schematic representation of a turbine blade 1 with a blade platform 2 and an associated blade 3.
Die Turbinenschaufel 1 ist flächig mit einer Wärmedämmschicht 4 versehen, wobei diese aus einer unmittelbar auf der Turbinenschaufel 1 aufgebrachten MCrAlY-Haftvermitt- lerschicht und einer darauf liegenden Keramikschicht besteht. Die Wärmedämmschicht 4 ist auf der Schaufelplattform 2 in einem Reparaturbereich 5 beschädigt .The turbine blade 1 is provided on the surface with a thermal barrier coating 4, the latter consisting of an MCrAlY adhesion promoter layer applied directly to the turbine blade 1 and a ceramic layer lying thereon. The thermal barrier coating 4 is damaged on the blade platform 2 in a repair area 5.
Um die Wärmedämmschicht 4 gemäß des erfindungsgemäßen Verfahrens zu reparieren, wird in einem ersten Schritt die Wärmedämmschicht 4 im Reparaturbereich 5 vollständig, beispielsweise durch Abschleifen entfernt. Dabei werden sowohl die Keramikschicht als auch die MCrAlY-Haftver- mittlerschicht im Reparaturbereich 5 abgetragen.In order to repair the thermal barrier coating 4 according to the method according to the invention, in a first step the thermal barrier coating 4 in the repair area 5 is completely removed, for example by abrading. Both the ceramic layer and the MCrAlY adhesion promoter layer are removed in the repair area 5.
Anschließend wird die Form und Größe des Reparaturbereiches 5 exakt bestimmt. Dies kann beispielsweise optisch mit Hilfe einer digitalen Kamera und einer angeschlossenen Datenverarbeitungsanlage zur Auswertung der erhaltenen Kameradaten erfolgen.Subsequently, the shape and size of the repair area 5 is determined exactly. This can be done, for example, optically with the aid of a digital camera and a connected data processing system for the evaluation of the received camera data.
In einem weiteren Schritt wird dann eine MCrAlY-Folie 6 hergestellt, die die exakte Form und Größe des Reparaturbereichs 5 aufweist. Dazu kann beispielsweise eine freistehende MCrAlY-Folie, welche die selbe Dicke wie die MCrAlY-Haftverraittlerschicht aufweist, mit Hilfe eines Lasers zugeschnitten werden.In a further step, an MCrAlY film 6 is then produced, which determines the exact shape and size of the Repair area 5 has. For this purpose, for example, a freestanding MCrAlY film, which has the same thickness as the MCrAlY Haftverraittlerschicht be cut using a laser.
Die MCrAlY-Folie 6 wird anschließend so auf die Schaufelplattform 2 aufgelegt, das sie den Reparaturbereich 5 vollständig bedeckt. Sie wird einer Wärmebehandlung unterzogen, um sie an die Oberfläche der Schaufelplattform 2 anzubinden. Dazu kann die gesamte Turbinenschaufel 1 mit der MCrAlY-Folie 6 im Vakuumofen erhitzt werden. Alternativ ist es ebenfalls möglich, lediglich die MCrAly-Folie 6 lokal durch Induktion zu erhitzen. In allen Fällen erfolgt die endgültige und vollständige Anbindung der MCrAlY-Folie 6 während des Betriebs der Turbinenschaufel 1.The MCrAlY film 6 is then placed on the blade platform 2 so that it completely covers the repair area 5. It is subjected to a heat treatment in order to bond it to the surface of the blade platform 2. For this purpose, the entire turbine blade 1 can be heated with the MCrAlY film 6 in a vacuum oven. Alternatively, it is also possible to heat only the MCrAly film 6 locally by induction. In all cases, the final and complete bonding of the MCrAlY film 6 takes place during operation of the turbine blade 1.
Nachfolgend wird die der Schaufelplattform 2 abgewandte Seite der MCrAlY-Folie 6 mit einer Keramik beschichtet. Dazu wird zunächst die noch auf der Schaufelplattform 2 vorhandene Keramikschicht in herkömmlicher Weise abgedeckt und dann eine Keramik, die mit der Keramik der Keramikschicht 6 identisch ist, beispielsweise durch atmosphärisches Plasmaspritzen auf die MCrAlY-Folie 6 aufgebracht. Gegebenenfalls kann anschließend ein Teil der neu aufgebrachten Keramikschicht weggeschliffen werden, so dass diese plan zu der Keramikschicht ist .Subsequently, the blade platform 2 facing away from the MCrAlY film 6 is coated with a ceramic. For this purpose, first of all the ceramic layer still present on the blade platform 2 is covered in a conventional manner and then a ceramic which is identical to the ceramic of the ceramic layer 6 is applied to the MCrAlY foil 6, for example by atmospheric plasma spraying. Optionally, a portion of the newly applied ceramic layer can then be ground away, so that it is planar to the ceramic layer.
Besonderer Vorteil des erfindungsgemäßen Verfahrens ist, dass die neue MCrAlY-Schicht im Reparaturbereich 5 aufgebracht werden kann, ohne dass die Gefahr besteht, dass die Keramikschicht verunreinigt wird. A particular advantage of the method according to the invention is that the new MCrAlY layer can be applied in the repair area 5 without the risk of the ceramic layer being contaminated.
Claims
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/EP2007/005392 WO2008154940A1 (en) | 2007-06-19 | 2007-06-19 | Method for repairing an area of a thermal insulation layer |
| PCT/EP2008/054601 WO2008155147A1 (en) | 2007-06-19 | 2008-04-16 | Method for repairing a region of a heat insulating layer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/EP2007/005392 WO2008154940A1 (en) | 2007-06-19 | 2007-06-19 | Method for repairing an area of a thermal insulation layer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2008154940A1 true WO2008154940A1 (en) | 2008-12-24 |
Family
ID=38691837
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/EP2007/005392 Ceased WO2008154940A1 (en) | 2007-06-19 | 2007-06-19 | Method for repairing an area of a thermal insulation layer |
| PCT/EP2008/054601 Ceased WO2008155147A1 (en) | 2007-06-19 | 2008-04-16 | Method for repairing a region of a heat insulating layer |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/EP2008/054601 Ceased WO2008155147A1 (en) | 2007-06-19 | 2008-04-16 | Method for repairing a region of a heat insulating layer |
Country Status (1)
| Country | Link |
|---|---|
| WO (2) | WO2008154940A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102015200513A1 (en) * | 2015-01-15 | 2016-07-21 | Siemens Aktiengesellschaft | Local damage detection and local heat treatment and apparatus therefor |
| DE102019217580A1 (en) * | 2019-11-14 | 2021-05-20 | Siemens Aktiengesellschaft | Repair of coated components by means of design adaptation |
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| EP1065297A2 (en) * | 1999-06-29 | 2001-01-03 | General Electric Company | A method of providing wear-resistant coatings, and related articles |
| EP1091020A1 (en) * | 1999-10-04 | 2001-04-11 | General Electric Company | A method of applying a bond coating and a thermal barrier coating on a metal substrate, and related articles |
| US20020128790A1 (en) * | 2001-03-09 | 2002-09-12 | Donald Woodmansee | System and method of automated part evaluation including inspection, disposition recommendation and refurbishment process determination |
| EP1256635A1 (en) * | 2001-05-08 | 2002-11-13 | General Electric Company | Method for applying diffusion aluminide coating on a selective area of a turbine engine component |
| EP1312438A1 (en) * | 2001-11-19 | 2003-05-21 | Mitsubishi Heavy Industries, Ltd. | Method of automatically repairing cracks and apparatus for use in such method |
| WO2003097293A1 (en) * | 2002-05-14 | 2003-11-27 | C.A. Patents, L.L.C. | Method of forming metal preforms by metal spraying |
| EP1507236A1 (en) * | 2003-08-15 | 2005-02-16 | Siemens Westinghouse Power Corporation | System and method for processing inspection data for evaluating degradation of coatings on components |
| US20050235493A1 (en) * | 2004-04-22 | 2005-10-27 | Siemens Westinghouse Power Corporation | In-frame repair of gas turbine components |
| DE102004026352A1 (en) * | 2004-05-26 | 2005-12-15 | Alstom Technology Ltd | Process for repair of protective coating on a coated turbine component, e.g. a turbine blade giving improved repair quality at reduced cost and decreases turbine blade wear |
| DE102004028672A1 (en) * | 2004-06-12 | 2006-01-05 | Mtu Aero Engines Gmbh | Coating inner surfaces of hollow gas turbine blades used in an aircraft engine comprises preparing the blade with a hollow chamber, arranging a metal foil in the chamber and welding the metal foil to the inner surface |
-
2007
- 2007-06-19 WO PCT/EP2007/005392 patent/WO2008154940A1/en not_active Ceased
-
2008
- 2008-04-16 WO PCT/EP2008/054601 patent/WO2008155147A1/en not_active Ceased
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1065297A2 (en) * | 1999-06-29 | 2001-01-03 | General Electric Company | A method of providing wear-resistant coatings, and related articles |
| EP1091020A1 (en) * | 1999-10-04 | 2001-04-11 | General Electric Company | A method of applying a bond coating and a thermal barrier coating on a metal substrate, and related articles |
| US20020128790A1 (en) * | 2001-03-09 | 2002-09-12 | Donald Woodmansee | System and method of automated part evaluation including inspection, disposition recommendation and refurbishment process determination |
| EP1256635A1 (en) * | 2001-05-08 | 2002-11-13 | General Electric Company | Method for applying diffusion aluminide coating on a selective area of a turbine engine component |
| EP1312438A1 (en) * | 2001-11-19 | 2003-05-21 | Mitsubishi Heavy Industries, Ltd. | Method of automatically repairing cracks and apparatus for use in such method |
| WO2003097293A1 (en) * | 2002-05-14 | 2003-11-27 | C.A. Patents, L.L.C. | Method of forming metal preforms by metal spraying |
| EP1507236A1 (en) * | 2003-08-15 | 2005-02-16 | Siemens Westinghouse Power Corporation | System and method for processing inspection data for evaluating degradation of coatings on components |
| US20050235493A1 (en) * | 2004-04-22 | 2005-10-27 | Siemens Westinghouse Power Corporation | In-frame repair of gas turbine components |
| DE102004026352A1 (en) * | 2004-05-26 | 2005-12-15 | Alstom Technology Ltd | Process for repair of protective coating on a coated turbine component, e.g. a turbine blade giving improved repair quality at reduced cost and decreases turbine blade wear |
| DE102004028672A1 (en) * | 2004-06-12 | 2006-01-05 | Mtu Aero Engines Gmbh | Coating inner surfaces of hollow gas turbine blades used in an aircraft engine comprises preparing the blade with a hollow chamber, arranging a metal foil in the chamber and welding the metal foil to the inner surface |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102015200513A1 (en) * | 2015-01-15 | 2016-07-21 | Siemens Aktiengesellschaft | Local damage detection and local heat treatment and apparatus therefor |
| DE102019217580A1 (en) * | 2019-11-14 | 2021-05-20 | Siemens Aktiengesellschaft | Repair of coated components by means of design adaptation |
| US11724343B2 (en) | 2019-11-14 | 2023-08-15 | Siemens Energy Global GmbH & Co. KG | Repair of coated components using design adaptation |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2008155147A1 (en) | 2008-12-24 |
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