EP1591549A1 - Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils - Google Patents
Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils Download PDFInfo
- Publication number
- EP1591549A1 EP1591549A1 EP04101783A EP04101783A EP1591549A1 EP 1591549 A1 EP1591549 A1 EP 1591549A1 EP 04101783 A EP04101783 A EP 04101783A EP 04101783 A EP04101783 A EP 04101783A EP 1591549 A1 EP1591549 A1 EP 1591549A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- heat protection
- adhesive layer
- protection layer
- heat
- 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.)
- Granted
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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
- 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
-
- 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
-
- 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
-
- 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
- C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00019—Repairing or maintaining combustion chamber liners or subparts
Definitions
- the present invention relates to the field of thermal Machinery. It relates to a method for repairing a local damage in the heat protection coating of a component according to the preamble of Claim 1.
- the multi-layer heat protection coating usually comprises an adhesive layer applied to the base material (Bond Coating BC) and the actual heat protection layer (Thermal Barrier Coating TBC), most of which are ceramic (e.g., columnar) Material exists.
- BC Ond Coating BC
- TBC Thermal Barrier Coating
- In operation forms at the boundary between the adhesive layer and the heat protection layer still a thermally grown oxide layer (Thermally Grown Oxide TGO) from which the adhesive layer against further Oxidation and corrosion protects and the adhesion of the heat protection layer continues improved.
- the object is solved by the entirety of the features of claim 1.
- the essence of the invention is that before the direct application of a ceramic filling layer first, the metallic adhesive layer up to a predetermined depth is removed to defined ratios in the restore chemical composition of the adhesive layer. This will it is possible the original mechanical properties of the Heat protection coating also in the area of repaired local To realize damage.
- a preferred embodiment of the inventive method is characterized characterized in that the adhesive layer in the upper thickness range one of the has original deviant chemical composition, and that the predetermined depth is selected so that at least the thickness range of Adhesive layer with the deviating chemical composition removed becomes.
- a thermally grown oxide layer is arranged before the removal of the adhesive layer first in a cleaning process in the area the local damage any residues of the heat protection layer and the Oxide layer removed.
- the thickness of the adhesive layer can be selectively reduced and unnecessary material removal is avoided, it is expedient that the removal of the adhesive layer, the remaining thickness is controlled. This is preferably done in that the thickness control the FSEC (F requency S canning E ddy C urrent) technique is used.
- FSEC Frequency S canning E ddy C urrent
- the ceramic filling layer is applied beyond the surface of the heat protection layer, and if the surface of the ceramic filling layer then by mechanical Machining, in particular grinding and / or polishing, the surface of Heat protection layer is adjusted.
- the inventive method can be installed in particular on site Components is performed. It can also be used as part of service work or to repair new components.
- the method shown in Fig. 1-4 is based on a from a Base material 11 manufactured component 10, e.g. a turbine blade or the like.,
- the on the outer surface with a heat protection coating 12, 13, 14 is provided.
- the heat protection coating 12, 13, 14 comprises a directly on the surface of the Base material 11 applied metallic adhesive layer (bond coating BC) 12, and a ceramic heat protection layer disposed over the adhesion layer 12 (Thermal barrier coating TBC) 14.
- Thermal barrier coating TBC Thermally grown oxide layer
- thermally grown oxide TBO thermally grown oxide
- the heat protection coating 12, 13, 14 now has a local according to FIG. 1 Damage 15, which essentially results in a local flaking of the ceramic heat protection layer 14 consists.
- the Heat protection layer 14 completely chipped, while the oxide layer 13 and the underlying metallic adhesive layer 12 are virtually intact. Let it However, there are other configurations of local damage imagine, for example, parts of the heat protection layer 14 still are present, or the layers 13 and 12 are partially damaged.
- a suitable Material removal method Remains of the ceramic heat protection layer 14 and the underlying Oxide layer 13 or its radicals by means of a suitable Material removal method removed.
- the material removal is preferably carried out through suitable masks 18, which ensure that the lateral Extent of material removal is limited and defined. Furthermore result from the use of masks 18 evenly beveled Edge areas on the layers 12, 13, 14, for the liability of the later padded material are beneficial.
- the underlying metallic adhesive layer 12 within the Material removal 16 is removed to a predetermined depth (Fig. 2).
- the predetermined depth of the removal of the adhesive layer 12 depends on how far in the depth of the chemical composition of the adhesive layer 12 compared to the original chemical composition due to Surface processes such as e.g. the formation of the oxide layer 13 has changed.
- test method which is called FSECT (Frequency Scanning eddy current) technique is known and induced the formation of Eddy currents in an electrically conductive multi-layer composite in dependence from the induction frequency.
- FIG. 3 On this newly formed surface of the adhesive layer 12 is now shown in FIG. 3 one of the heat protection layer 14 in composition and orientation corresponding ceramic filling layer 17 applied, which by the local Damage 15 and the material removal resulting depression fills and even beyond the surface 20 of the heat protection layer 14 ( Figure 4). Also the order of the ceramic filling layer 17 can by suitable masks 19 through to limit the order laterally.
- the remaining adhesive layer 12 has the same properties as the original adhesive layer, results in a layer composite 11, 12, 17, the has largely the same mechanical properties as the original layer composite 11, 12, 14 before the formation of the oxide layer 13.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Inorganic Chemistry (AREA)
- Materials Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
- Es wird die Haftschicht BC, die durch die lokale Abplatzung exponiert ist, gereinigt, um Oxide und Reste der keramischen Hitzeschutzschicht TBC zu entfernen.
- Die Haftschicht BC wird behandelt, um ihrer Oberfläche eine Struktur zu verleihen.
- Es wird auf der Oberfläche der Haftschicht keramisches Material abgelagert, welches eine die Haftschicht vollständig bedeckende keramische Schicht bildet.
- Die MCrAlY-Schicht wird lokal durch Ersetzen mit neuem MCrAIY ausgebessert.
- Die teilweise verarmte MCrAIY-Schicht wird auf der gesamten Oberfläche des Bauteils aluminisiert oder chromiert, so dass Al oder Cr zumindest teilweise in die verarmte MCrAIY-Schicht eindiffundieren und den Gehalt der MCrAIY-Schicht an Al oder Cr wieder auffüllen kann.
- Das Verfahren ist auch anwendbar, selbst wenn eine keramische Beschichtung vorliegt. Die keramische Beschichtung, z.B. eine Hitzeschutzschicht TBC, die sich oberhalb der MCrAlY-Schicht befindet, wird mit einem geeigneten Verfahren, z.B. mittels Säurereinigung, entfernt, bevor die MCrAIY-Schicht in der oben beschriebenen Weise aufgearbeitet wird. Das Bauteil wird anschliessend wieder mit einer TBC-Schicht überzogen.
- Die Haftschicht wird nur bearbeitet, um deren Oberfläche zu strukturieren. Später entsteht eine thermisch gewachsene Oxidschicht (TGO) auf der Oberfläche der behandelten Haftschicht.
- Die chemische Zusammensetzung der verbleibenden Haftschicht (BC) und der neu wachsende TGO-Schicht verändert sich, und zwar in erster Linie entsprechend dem Wachsen der TGO-Schicht.
- Die verbleibende Haftschicht und die neu gewachsene TGO-Schicht haben
im Vergleich zu ihrem ursprünglichen Zustand verschlechterte
Eigenschaften:
- o Wegen der internen Oxidation und Ausscheidung von sekundären Phasen (z.B. σ- oder α-Phasen) nahe der Oberfläche ist der Prozess nicht vorhersagbar.
- o Nach dem Einsatz des Bauteils bei hohen Temperaturen ist im oberen Teil der Haftschicht (BC) wegen der Bildung des TGO und der Diffusion von Aluminium zur Oberfläche der Aluminiumgehalt deutlich verringert, d.h., die Schicht zeigt nahe der Oberfläche den niedrigsten Al-Gehalt. Es besteht daher die erhebliche Gefahr, dass anstelle von reinem Al2O3 gemischte Oxide wachsen und die Hitzeschutzschicht TBC schnell wieder abplatzt.
- Fig. 1-4
- verschiedene Teilschritte bei der Reparatur einer lokalen Beschädigung der Hitzeschutzbeschichtung eines Bauteils gemäss einem bevorzugten Ausführungsbeispiel der Erfindung.
- 10
- Bauteil
- 11
- Basismaterial (Bauteil)
- 12
- Haftschicht (bond coating BC)
- 13
- Oxidschicht (thermisch gewachsen; TGO)
- 14
- Hitzeschutzschicht (keramisch; TBC)
- 15
- lokale Beschädigung (Abplatzung)
- 16
- Materialabtrag
- 17
- keramische Füllschicht
- 18,19
- Maske
- 20
- Oberfläche
Claims (9)
- Verfahren zum Ausbessern einer lokalen Beschädigung (15) in der Hitzeschutzbeschichtung eines Bauteils (10), wobei die Hitzeschutzbeschichtung eine metallische Haftschicht (12) und eine über der metallischen Haftschicht (12) aufgebrachte keramische Hitzeschutzschicht (14) umfasst, und wobei die lokale Beschädigung (15) durch ein lokales Abplatzen der Hitzeschutzschicht (14) hervorgerufen worden ist, dadurch gekennzeichnet, dass in einem ersten Schritt die metallische Haftschicht (12) bis zu einer vorgegebenen Tiefe abgetragen wird, und dass in einem zweiten Schritt auf die dickenreduzierte Haftschicht (12) zum Auffüllen der Hitzeschutzschicht (14) eine keramische Füllschicht (17) aufgetragen wird.
- Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass die Haftschicht (12) im oberen Dickenbereich eine von der ursprünglichen abweichende chemische Zusammensetzung aufweist, und dass die vorgegebene Tiefe so gewählt ist, dass zumindest der Dickenbereich der Haftschicht (12) mit der abweichenden chemischen Zusammensetzung abgetragen wird.
- Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass zwischen der Haftschicht (12) und der darüber liegenden Hitzeschutzschicht (13) eine thermisch gewachsene Oxidschicht (13) angeordnet ist, und dass vor dem Abtragen der Haftschicht (12) zunächst in einem Reinigungsprozess im Bereich der lokalen Beschädigung (15) etwaige Reste der Hitzeschutzschicht (14) und einer Oxidschicht (13) entfernt werden.
- Verfahren nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass beim Abtragen der Haftschicht (12) die verbleibende Dicke kontrolliert wird.
- Verfahren nach Anspruch 4, dadurch gekennzeichnet, dass zur Dickenkontrolle die FSEC(Frequency Scanning Eddy Current)-Technik eingesetzt wird.
- Verfahren nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Abtragen der Schichten (12, 13) und/oder das Auffüllen der Hitzeschutzschicht (14) zur Erzeugung eines definierten Randbereichs durch entsprechende Masken (18, 19) hindurch erfolgt.
- Verfahren nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass im zweiten Schritt die keramische Füllschicht (17) über die Oberfläche (20) der Hitzeschutzschicht (14) hinausgehend aufgetragen wird, und dass die Oberfläche der keramischen Füllschicht (17) dann durch mechanische Bearbeitung, insbesondere Schleifen und/oder Polieren, der Oberfläche (20) der Hitzeschutzschicht (14) angeglichen wird.
- Verfahren nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass das Verfahren vor Ort an eingebauten Bauteilen (10) durchgeführt wird.
- Verfahren nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass das Verfahren im Rahmen von Servicearbeiten oder zur Ausbesserung neuer Bauteile (10) durchgeführt wird.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT04101783T ATE462023T1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum ausbessern einer lokalen beschädigung in der hitzeschutzbeschichtung eines bauteils |
EP04101783A EP1591549B1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils |
DE502004010936T DE502004010936D1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04101783A EP1591549B1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1591549A1 true EP1591549A1 (de) | 2005-11-02 |
EP1591549B1 EP1591549B1 (de) | 2010-03-24 |
Family
ID=34929028
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04101783A Expired - Lifetime EP1591549B1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP1591549B1 (de) |
AT (1) | ATE462023T1 (de) |
DE (1) | DE502004010936D1 (de) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1794341A1 (de) * | 2004-10-07 | 2007-06-13 | Siemens Aktiengesellschaft | Verfahren zur herstellung eines schichtsystems |
US8221825B2 (en) | 2009-03-30 | 2012-07-17 | Alstom Technology Ltd. | Comprehensive method for local application and local repair of thermal barrier coatings |
EP3202954A1 (de) * | 2016-02-08 | 2017-08-09 | United Technologies Corporation | Reparatur einer beschichtung mit einem vorkonfigurierten beschichtungspflaster |
US10717166B2 (en) | 2016-12-02 | 2020-07-21 | General Electric Company | Motorized apparatus for use with rotary machines |
WO2020233925A1 (de) * | 2019-05-22 | 2020-11-26 | Siemens Aktiengesellschaft | Verfahren zur durchführung von servicemassnahmen an einer energieumwandlungsanlage und energieumwandlungsanlage |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10494926B2 (en) | 2017-08-28 | 2019-12-03 | General Electric Company | System and method for maintaining machines |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0808913A1 (de) * | 1996-05-24 | 1997-11-26 | General Electric Company | Methode zum Reparieren von einer wärmehemmenden Beschichtung |
US6235352B1 (en) * | 1999-11-29 | 2001-05-22 | Electric Power Research Institute, Inc. | Method of repairing a thermal barrier coating |
EP1197585A2 (de) * | 2000-10-12 | 2002-04-17 | General Electric Company | Verfahren zur Reparatur einer Wärmesperrschicht und reparierte Beschichtung |
-
2004
- 2004-04-28 AT AT04101783T patent/ATE462023T1/de not_active IP Right Cessation
- 2004-04-28 EP EP04101783A patent/EP1591549B1/de not_active Expired - Lifetime
- 2004-04-28 DE DE502004010936T patent/DE502004010936D1/de not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0808913A1 (de) * | 1996-05-24 | 1997-11-26 | General Electric Company | Methode zum Reparieren von einer wärmehemmenden Beschichtung |
US6235352B1 (en) * | 1999-11-29 | 2001-05-22 | Electric Power Research Institute, Inc. | Method of repairing a thermal barrier coating |
EP1197585A2 (de) * | 2000-10-12 | 2002-04-17 | General Electric Company | Verfahren zur Reparatur einer Wärmesperrschicht und reparierte Beschichtung |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1794341A1 (de) * | 2004-10-07 | 2007-06-13 | Siemens Aktiengesellschaft | Verfahren zur herstellung eines schichtsystems |
EP1794340A1 (de) * | 2004-10-07 | 2007-06-13 | Siemens Aktiengesellschaft | Verfahren zur herstellung eines schichtsystems |
US8221825B2 (en) | 2009-03-30 | 2012-07-17 | Alstom Technology Ltd. | Comprehensive method for local application and local repair of thermal barrier coatings |
EP3202954A1 (de) * | 2016-02-08 | 2017-08-09 | United Technologies Corporation | Reparatur einer beschichtung mit einem vorkonfigurierten beschichtungspflaster |
US10927684B2 (en) | 2016-02-08 | 2021-02-23 | Raytheon Technologies Corporation | Repairing a coating with a pre-configured coating patch |
US10717166B2 (en) | 2016-12-02 | 2020-07-21 | General Electric Company | Motorized apparatus for use with rotary machines |
WO2020233925A1 (de) * | 2019-05-22 | 2020-11-26 | Siemens Aktiengesellschaft | Verfahren zur durchführung von servicemassnahmen an einer energieumwandlungsanlage und energieumwandlungsanlage |
Also Published As
Publication number | Publication date |
---|---|
EP1591549B1 (de) | 2010-03-24 |
DE502004010936D1 (de) | 2010-05-06 |
ATE462023T1 (de) | 2010-04-15 |
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