WO2015110206A1 - Layer system on the platform of a turbine blade, having a rounded-off edge - Google Patents

Layer system on the platform of a turbine blade, having a rounded-off edge Download PDF

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Publication number
WO2015110206A1
WO2015110206A1 PCT/EP2014/076237 EP2014076237W WO2015110206A1 WO 2015110206 A1 WO2015110206 A1 WO 2015110206A1 EP 2014076237 W EP2014076237 W EP 2014076237W WO 2015110206 A1 WO2015110206 A1 WO 2015110206A1
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WO
WIPO (PCT)
Prior art keywords
layer
layer system
substrate
rounding
coating
Prior art date
Application number
PCT/EP2014/076237
Other languages
German (de)
French (fr)
Inventor
Reiner Anton
Kay Krabiell
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2015110206A1 publication Critical patent/WO2015110206A1/en

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Classifications

    • 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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex

Definitions

  • the invention relates to a layer system in which the substrate and the coating are rounded off in the region of the edge
  • Components are often coated to protect them from corrosion
  • turbine blades which have a blade platform which is also coated and has a side surface below the edge in the area of the blade platform that is nearly perpendicular thereto and uncoated.
  • the object is achieved by a layer system according to claim 1.
  • a coated fillet does not cause any cracks between the interfaces of the layers or the substrate.
  • FIG. 2 shows a layer system according to the invention
  • FIG. 3 shows a turbine blade
  • FIG. 4 is a list of superalloys. The figures and the description represent only embodiments of the invention.
  • FIG. 1 shows a layer system 1 according to the prior art.
  • the layer system 1 has a substrate 2, in particular made of nickel- or cobalt-based superalloys, in particular an alloy according to FIG. 4.
  • First and second surfaces 13, 20 are perpendicular to each other.
  • the second side surface 20 has no coating.
  • the layer 4 is preferably metallic, more preferably a NiCoCrAlX layer.
  • a ceramic layer 7 is applied, which represents the outermost layer.
  • the metallic layer 4 and / or the ceramic layer 7 may be formed in two layers as a metallic layer or as a ceramic layer.
  • an oxide layer of the metallic layer is present only during operation of the layer system or in advance.
  • FIG. 2 shows a layer system 1 'according to the invention.
  • the substrate 2 ' has alloys comparable to the prior art, a modified first surface 13' and a changed second side surface 20 ', since here a rounding 11 exists directly between the first surface 13' and the second side surface 20 'of the substrate 2' is.
  • a plane 21 of the first surface 13 'and a plane through the second surface 20' form a cutting line 27.
  • the metallic coating 4 'thus has, in contrast to the prior art, a region 5, which is below the plane 21, which is determined by the first surface 13', and on the material of the coatings 4 ', 7' is present and in which the at least one layer 4 ', 7' is arranged in the shortest connection from a cutting line 27 to the substrate 2 '.
  • the layer 4 'or layers 4', 7 ' run at its end in the region of the end 24 of the rounding 11 pointed.
  • the further layer 7 ' also has a portion 8 which is below a plane 22 which is defined by the surface 13' 'of the layer 4', but this portion is necessarily made thinner with comparable layer thicknesses with respect to the stand of the technique.
  • the ceramic layer 7 ' preferably also has a portion 30 below the plane 21. Thus, on the modified side surface 20 ', 11 there is no more perpendicular boundary surface and cracks are hardly initiated.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)

Abstract

By rounding off an edge that previously was perpendicular or by applying a corresponding coating (4', 7') thereto the formation of cracks in the interface between the layers (4') and a surface of the substrate (2') is avoided.

Description

SCHICHTSYSTEM AUF DER PLATTFORM EINER TURBINENSCHAUFEL MIT ABGERUNDETER KANTE  COATING SYSTEM ON THE PLATFORM OF A TURBINE BLADE WITH ROUNDED EDGES
Die Erfindung betrifft ein Schichtsystem, bei dem das Substrat und die Beschichtung im Bereich der Kante abgerundet The invention relates to a layer system in which the substrate and the coating are rounded off in the region of the edge
Bauteile werden oft beschichtet, um sie vor Korrosion Components are often coated to protect them from corrosion
und/oder Oxidation zu schützen, sowie werden andere Schichten zur Wärmedämmung aufgebracht . and / or to protect oxidation, as well as other layers are applied for thermal insulation.
Ein Beispiel dafür sind Turbinenschaufeln, die eine Schaufelplattform aufweisen, die ebenfalls beschichtet wird und eine Seitenfläche unterhalb der Kante im Bereich der Schaufel - Plattform aufweist, die nahezu senkrecht dazu ausgebildet und unbeschichtet ist. An example of this is turbine blades which have a blade platform which is also coated and has a side surface below the edge in the area of the blade platform that is nearly perpendicular thereto and uncoated.
Im Bereich der Kante kommt es immer wieder zu Schwierigkeiten oder zu Reibungen, da die Seitenfläche benachbarter Turbinenschaufeln aneinander liegen. Es ist daher Aufgabe der vorliegenden Erfindung ein Schichtsystem aufzuzeigen, dass das Problem löst. In the area of the edge, there are always difficulties or friction, since the side surface of adjacent turbine blades lie against each other. It is therefore an object of the present invention to provide a layer system that solves the problem.
Die Aufgabe wird gelöst durch ein Schichtsystem nach Anspruch 1. The object is achieved by a layer system according to claim 1.
In den Unteransprüchen sind weitere vorteilhafte Maßnahmen aufgelistet, die beliebig miteinander kombiniert werden können, um weitere Vorteile zu erzielen. Durch eine beschichtete Abrundung entstehen keine Risse zwischen den Grenzflächen der Schichten oder dem Substrat. In the dependent claims further advantageous measures are listed, which can be combined with each other in order to achieve further advantages. A coated fillet does not cause any cracks between the interfaces of the layers or the substrate.
Es zeigen: Figur 1 ein Schichtsystem nach dem Stand der Technik, 1 shows a layer system according to the prior art,
Figur 2 ein erfindungsgemäßes Schichtsystem,  FIG. 2 shows a layer system according to the invention,
Figur 3 eine Turbinenschaufel,  FIG. 3 shows a turbine blade,
Figur 4 eine Liste von Superlegierungen . Die Figuren und die Beschreibung stellen nur Ausführungsbeispiele der Erfindung dar. Figure 4 is a list of superalloys. The figures and the description represent only embodiments of the invention.
In Figur 1 ist ein Schichtsystem 1 nach dem Stand der Technik dargestellt . FIG. 1 shows a layer system 1 according to the prior art.
Das Schichtsystem 1 weist ein Substrat 2 insbesondere aus nickel- oder kobalbasierten Superlegierungen auf, insbeson- dere eine Legierung gemäß Figur 4.  The layer system 1 has a substrate 2, in particular made of nickel- or cobalt-based superalloys, in particular an alloy according to FIG. 4.
Auf eine erste Oberfläche 13, die eine nahezu rechtwinklige Kante 10 zur zweiten Seitenfläche 20 aufweist, sind Schichten 4 , 7 aufgebracht .  On a first surface 13, which has a nearly right-angled edge 10 to the second side surface 20, layers 4, 7 are applied.
Erste und zweite Oberflächen 13, 20 stehen senkrecht aufein- ander.  First and second surfaces 13, 20 are perpendicular to each other.
Die zweite Seitenfläche 20 weist keine Beschichtung auf.  The second side surface 20 has no coating.
Die Schicht 4 ist vorzugsweise metallisch, ganz vorzugsweise eine NiCoCrAlX-Schicht . The layer 4 is preferably metallic, more preferably a NiCoCrAlX layer.
Auf dieser Schicht 4 ist eine keramische Schicht 7 aufgebracht, die die äußerste Schicht darstellt. On this layer 4, a ceramic layer 7 is applied, which represents the outermost layer.
Vorzugsweise sind keine weiteren Schichten aufgebracht. Jedoch können die metallische Schicht 4 und/oder die keramische Schicht 7 zweilagig als eine metallische Schicht bzw. als eine keramische Schicht ausgebildet sein. Preferably, no further layers are applied. However, the metallic layer 4 and / or the ceramic layer 7 may be formed in two layers as a metallic layer or as a ceramic layer.
Auf der metallischen Schicht 4 ist erst während des Betriebs des Schichtsystems oder vorab eine TGO, eine Oxidschicht der metallischen Schicht vorhanden. On the metallic layer 4, a TGO, an oxide layer of the metallic layer is present only during operation of the layer system or in advance.
Insbesondere entlang der Grenzfläche 10 zwischen der Schicht 4 und dem Substrat 2, insbesondere da dies an eine Seitenfläche grenzt und eine Kontaktfläche darstellt, können sich Risse 9 entwickeln. In Figur 2 ist ein erfindungsgemäßes Schichtsystem 1' dargestellt . In particular, along the interface 10 between the layer 4 and the substrate 2, particularly since it is adjacent to a side surface and constitutes a contact surface, cracks 9 may develop. FIG. 2 shows a layer system 1 'according to the invention.
Das Substrat 2' weist zum Stand der Technik vergleichbare Legierungen, eine veränderte erste Oberfläche 13' und verän- derte zweite Seitenfläche 20' auf, da hier eine Abrundung 11 direkt zwischen der ersten Oberfläche 13' und zweiten Seitenfläche 20' des Substrats 2' vorhanden ist.  The substrate 2 'has alloys comparable to the prior art, a modified first surface 13' and a changed second side surface 20 ', since here a rounding 11 exists directly between the first surface 13' and the second side surface 20 'of the substrate 2' is.
Eine Ebene 21 der ersten Oberfläche 13' und eine Ebene durch die zweite Oberfläche 20' bilden eine Schnittlinie 27. A plane 21 of the first surface 13 'and a plane through the second surface 20' form a cutting line 27.
Die metallische Beschichtung 4' weist also im Gegensatz zum Stand der Technik einen Bereich 5 auf, der unterhalb der Ebene 21, die durch die erste Oberfläche 13' bestimmt ist, vorhanden ist und an dem Material der Beschichtungen 4', 7' vorhanden ist und bei dem in der kürzesten Verbindung von einer Schnittlinie 27 zum Substrat 2' die zumindest eine Schicht 4', 7' angeordnet ist. Die Schicht 4' oder Schichten 4', 7' laufen an ihrem Ende im Bereich des Endes 24 der Abrundung 11 spitz zu.  The metallic coating 4 'thus has, in contrast to the prior art, a region 5, which is below the plane 21, which is determined by the first surface 13', and on the material of the coatings 4 ', 7' is present and in which the at least one layer 4 ', 7' is arranged in the shortest connection from a cutting line 27 to the substrate 2 '. The layer 4 'or layers 4', 7 'run at its end in the region of the end 24 of the rounding 11 pointed.
Vorzugsweise weist auch die weitere Schicht 7' darüber einen Anteil 8 auf, der unterhalb einer Ebene 22, die durch die Oberfläche 13'' der Schicht 4' definiert ist, wobei dieser Anteil jedoch zwangsläufig dünner ausgebildet ist bei ver- gleichbaren Schichtdicken gegenüber dem Stand der Technik. Preferably, the further layer 7 'also has a portion 8 which is below a plane 22 which is defined by the surface 13' 'of the layer 4', but this portion is necessarily made thinner with comparable layer thicknesses with respect to the stand of the technique.
Die keramische Schicht 7' weist vorzugsweise auch einen Anteil 30 unterhalb der Ebene 21 auf. Somit ist an der geänderten Seitenfläche 20', 11 keine dazu senkrecht verlaufende Grenzfläche mehr vorhanden und Risse werden kaum noch initiiert. The ceramic layer 7 'preferably also has a portion 30 below the plane 21. Thus, on the modified side surface 20 ', 11 there is no more perpendicular boundary surface and cracks are hardly initiated.

Claims

Patentansprüche claims
1. Schichtsystem (IM, 1st layer system (IM,
das zumindest aufweist:  that at least has:
ein Substrat (2λ) a substrate (2 λ )
mit zumindest zwei Seitenflächen (13 20'),  with at least two side surfaces (13 20 '),
deren Ebenen unter einem Winkel von 90° + 10° verlaufen, insbesondere unter einem Winkel von 90°,  whose planes are at an angle of 90 ° + 10 °, in particular at an angle of 90 °,
zumindest eine Beschichtung (4λ, 7') auf der ersten Seitenfläche (13 M und at least one coating (4 λ , 7 ') on the first side surface (13 M and
nur teilweise oder gar keine Beschichtung auf der zweiten Seitenfläche (204 ) , only partial or no coating on the second side surface (20 4 ),
wobei zwischen der zweiten Seitenfläche (20 M und der ers- ten Seitenfläche (13 M eine Abrundung (11) vorhanden ist und  wherein between the second side surface (20 M and the first side surface (13 M a rounding (11) is present, and
wobei Material der zumindest einen Schicht (4λ, 7') auf der Abrundung (11) vorhanden ist, wherein material of the at least one layer (4 λ , 7 ') is present on the rounding (11),
wobei die Abrundung (11) direkt an die erste Seitenfläche (13 M und direkt an die zweite Seitenfläche (20 M angrenzt.  wherein the rounding (11) directly adjacent to the first side surface (13 M and directly to the second side surface (20 M).
2. Schichtsystem nach Anspruch 1, 2. Layer system according to claim 1,
bei dem die Abrundung (11) dazu führt,  in which the rounding (11) leads to
dass sich die Ebenen der Seitenflächen (13 20') in einer Schnittlinie (27) schneiden,  that the planes of the side surfaces (13 20 ') intersect in a section line (27),
und bei dem in der kürzesten Verbindung von der Schnittlinie (27) zum Substrat (2λ) die zumindest eine Schicht (4λ, 7λ) auch angeordnet ist, and in which in the shortest connection from the cutting line (27) to the substrate (2 λ ) the at least one layer (4 λ , 7 λ ) is also arranged,
insbesondere eine Schicht (4M,  in particular a layer (4M,
ganz insbesondere zwei Schichten (4\ 7M .  in particular two layers (4 \ 7M.
3. Schichtsystem nach einem oder beiden der Ansprüche 1 oder 2, 3. Layer system according to one or both of claims 1 or 2,
bei dem das Schichtsystem (IM zwei Schichten (4\ 7M aufweist ,  where the layer system (IM has two layers (4 \ 7M,
insbesondere nur zwei Schichten (4\ 7M aufweist. especially only two layers (4 \ 7M has.
4. Schichtsystem nach einem oder mehreren der Ansprüche 1,2 oder 3 , 4. Layer system according to one or more of claims 1, 2 or 3,
bei dem das Substrat (2λ) nickel- oder kobaltbasiert ist, bei dem darauf (2l) , insbesondere direkt darauf, eine metallische Schicht (4M und in which the substrate (2 λ ) is nickel- or cobalt-based, in which thereon (2 l ), in particular directly thereon, a metallic layer (4M and
bei der darauf (4M, insbesondere direkt darauf, eine keramische äußerste Schicht (7M vorhanden ist.  in which there is (4M, in particular directly on it, a ceramic outermost layer (7M).
5. Schichtsystem nach einem oder mehreren der Ansprüche 1 bis 4, 5. Layer system according to one or more of claims 1 to 4,
bei dem die Schichten (4\ 7M zum Ende (24) der Abrundung (11) zur zweiten Oberfläche (20 M hin dünner werden.  in which the layers (4 \ 7M become thinner towards the end (24) of the rounding (11) towards the second surface (20M).
6. Schichtsystem nach einem oder mehreren der Ansprüche 1 bis 5 , 6. Layer system according to one or more of claims 1 to 5,
bei der sich die Beschichtung (4\ 7M auf der gesamten Abrundung (11) des Substrats (2M befindet.  in which the coating (4 \ 7M is located on the entire rounding (11) of the substrate (2M).
7. Schichtsystem nach einem oder mehreren der Ansprüche 1 bis 6, 7. Layer system according to one or more of claims 1 to 6,
bei der die Beschichtung (4\ 7M nicht über eine Ebene, die durch die zweite Seitenfläche (20 M verläuft,  where the coating (4 \ 7M does not have a plane passing through the second side face (20 M)
hinausragt .  protrudes.
8. Schichtsystem nach einem oder mehreren der Ansprüche 1 bis 7, 8. Layer system according to one or more of claims 1 to 7,
bei dem die zweite Seitenfläche (20 M keine Beschichtung (4\ 7M aufweist. Schichtsystem nach einem oder mehreren der Ansprüche 1 bis 8, in which the second side surface (20 M has no coating (4 \ 7M. Layer system according to one or more of claims 1 to 8,
bei dem durch die zweite Seitenfläche (20 und der dazu schneidenden verlaufenden ersten Oberfläche (13 ein Bereich (5) definiert wird, in which an area (5) is defined by the second side face (20 and the intersecting first surface (13),
der zwischen dem Substrat (2λ) und der Schnittlinie (27) der Ebene der Seitenfläche (20 13') liegt. which lies between the substrate (2 λ ) and the section line (27) of the plane of the side surface (20 13 ').
PCT/EP2014/076237 2014-01-21 2014-12-02 Layer system on the platform of a turbine blade, having a rounded-off edge WO2015110206A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014201003.9A DE102014201003A1 (en) 2014-01-21 2014-01-21 Layer system with rounded edge
DE102014201003.9 2014-01-21

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1239058A2 (en) * 2001-03-06 2002-09-11 Mitsubishi Heavy Industries, Ltd. Coating for gas turbine blades
EP1428981A1 (en) * 2002-12-11 2004-06-16 Siemens Aktiengesellschaft Turbine blade with a protective coating
US20100143655A1 (en) * 2008-12-10 2010-06-10 General Electric Company Articles for high temperature service and methods for their manufacture
EP2418357A1 (en) * 2010-08-05 2012-02-15 Siemens Aktiengesellschaft Turbine airfoil and method for thermal barrier coating

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE9013268U1 (en) * 1989-09-19 1990-11-22 Braas Gmbh, 6370 Oberursel, De
DE19748192A1 (en) * 1997-10-31 1999-05-06 Ipm Alternative Werkstoffe Gmb Material plate based on paper for e.g. supporting posters

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1239058A2 (en) * 2001-03-06 2002-09-11 Mitsubishi Heavy Industries, Ltd. Coating for gas turbine blades
EP1428981A1 (en) * 2002-12-11 2004-06-16 Siemens Aktiengesellschaft Turbine blade with a protective coating
US20100143655A1 (en) * 2008-12-10 2010-06-10 General Electric Company Articles for high temperature service and methods for their manufacture
EP2418357A1 (en) * 2010-08-05 2012-02-15 Siemens Aktiengesellschaft Turbine airfoil and method for thermal barrier coating

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