EP0906964A2 - Thermal barrier coating and process for its manufacture - Google Patents

Thermal barrier coating and process for its manufacture Download PDF

Info

Publication number
EP0906964A2
EP0906964A2 EP98118456A EP98118456A EP0906964A2 EP 0906964 A2 EP0906964 A2 EP 0906964A2 EP 98118456 A EP98118456 A EP 98118456A EP 98118456 A EP98118456 A EP 98118456A EP 0906964 A2 EP0906964 A2 EP 0906964A2
Authority
EP
European Patent Office
Prior art keywords
barrier coating
thermal barrier
thermal
ceramic
layer
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
Application number
EP98118456A
Other languages
German (de)
French (fr)
Other versions
EP0906964A3 (en
EP0906964B1 (en
Inventor
Joachim Dr. Bamberg
Peter Dr. Adam
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Aero Engines GmbH, MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Aero Engines GmbH
Publication of EP0906964A2 publication Critical patent/EP0906964A2/en
Publication of EP0906964A3 publication Critical patent/EP0906964A3/en
Application granted granted Critical
Publication of EP0906964B1 publication Critical patent/EP0906964B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • 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
    • C23C4/18—After-treatment

Definitions

  • the invention relates to a thermal barrier coating by thermal spraying is applied to a metallic component, is ceramic and one porous structure, as well as a process for their preparation.
  • Thermal insulation layers are the cheapest and most effective by thermal spray processes, such as Plasma spraying, apply to the metallic components.
  • the ceramic so produced Thermal insulation layers have a porous, micro-cracks Structure that has a lower modulus of elasticity. Consequently can the thermal barrier coating in operation due to thermomechanical Loads of deformations that always occur are harmless to a limited extent withstand.
  • the thermal insulation layers in the high temperature range > 900 ° C
  • the ceramic changes. Sintering effects occur that result in an increasing modulus of elasticity.
  • the thermal insulation layer is therefore less stretch tolerant, so that the thermomechanical loads lead to so-called segmentation cracks through which the thermal insulation layer segmented into individual clods.
  • DE 40 41 103 A1 describes a method for the surface treatment of Components known by shot peening, in which initially a metallic MCrAlY layer as an oxidation and hot gas corrosion layer on the component surface applied and then the layer is shot peened to to achieve a smoothing of the rough layer surface and to compact the layer.
  • a metallic layer is homogeneous and differs fundamentally of a ceramic thermal barrier coating, the grains and Has grain boundaries.
  • US 5,277,936 discloses a method for coating a component a Ni or Co-based alloy, in which a metal powder and oxides for production a metallic oxidation protection and adhesive layer for a thermal insulation layer can be applied by plasma spraying.
  • the oxidation protection and adhesive layer is blasted for compaction.
  • the ceramic Thermal insulation layer just not be blasted.
  • the invention has for its object a thermal barrier coating of the beginning to improve the genus described so that it also in the high temperature range is thermomechanically as stable as possible.
  • a procedure is also intended for the production of a thermal insulation layer that is as stable as possible be created.
  • the solution to the problem relating to the method is thereby according to the invention characterized in that the thermal barrier coating during and / or after the application process (thermal spraying) is blasted.
  • the thermal barrier coating is spherical Blasted particles, which preferably consist of metal, ceramic or glass can.
  • the solution relating to the thermal barrier coating is thereby characterized in that the thermal barrier coating formed by radiation, near the surface Shows cracks.
  • the advantage is that the occurrence of unfavorable clod sizes is avoided is by the thermal barrier coating by blasting with particles is defined pre-damaged. Due to the high kinetic energy of the particles numerous small cracks near the surface occur in the thermal insulation layer on impact. In addition, so-called. Micro contact surfaces that the Accelerate sintering process, broken up. This way, at thermomechanical Stress both reduced the sintering effects, as well as the Formation of subcritical, small clods in the segmentation as a result of promoted many crack starters.
  • thermal insulation layers Do not damage ceramics. The latter applies to those produced by vapor deposition Thermal insulation layers continue.
  • the surprising effect according to the present The invention occurs particularly when manufactured by thermal spraying Thermal insulation layers, which have numerous microcracks. By the blasting according to the invention does not compact such a layer, but rather loosened overall to avoid the problem of sintering.
  • a thermally highly stressed, metallic engine component like one Turbine blade, is provided with a ceramic thermal barrier coating.
  • the thermal barrier coating is applied by plasma spraying onto the metallic component applied and has a porous, micro-cracked Structure on.
  • the occurrence of unfavorable clod sizes with sintering effects Avoid the ceramic during operation in the high temperature range Thermal barrier layer during or immediately after the manufacturing process by means of plasma spraying, i.e. the application of the ceramic thermal barrier coating on the metallic component, defined by metal shot peening pre-damaged. Due to the high kinetic energy of the metal balls When impacting the thermal insulation layer, many small near-surface Cracks. The layer is loosened overall.
  • so-called micro contact surfaces that accelerate the sintering process, broken up. The Blasting can start while the thermal barrier coating is being applied and continue afterwards or only immediately after application kick off.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The method for producing a ceramic heat barrier layer by thermal spraying on a metal component whereby during and/or after application of such a layer it is subjected to a shot-blasting process. The resultant barrier layer has cracks near the surface produced by the shot-blasting process.

Description

Die Erfindung betrifft eine Wärmedämmschicht, die durch thermisches Spritzen auf eine metallische Komponente aufgebracht ist, keramisch ist und eine poröse Struktur aufweist, sowie ein Verfahren zu Ihrer Herstellung.The invention relates to a thermal barrier coating by thermal spraying is applied to a metallic component, is ceramic and one porous structure, as well as a process for their preparation.

Im Motoren- und Turbinenbau werden hochbelastete metallische Komponenten zum Schutz vor hohen Temperaturen mit keramischen Wärmedämmschichten versehen. Die Wärmedämmschichten lassen sich am kostengünstigsten und effektivsten durch thermische Spritzverfahren, wie z.B. Plasmaspritzen, auf die metallischen Komponenten aufbringen. Die so hergestellten keramischen Wärmedämmschichten besitzen eine poröse, von Mikrorissen durchzogene Struktur, die einen niedrigeren Elastizitätsmodul aufweist. Infolgedessen kann die Wärmedämmschicht die im Betrieb infolge thermomechanischer Belastung stets auftretenden Verformungen in bergrenztem Umfang schadlos aushalten. Beim Einsatz der Wärmedämmschichten im Hochtemperaturbereich (>900 °C) verändert sich jedoch die Keramik. Es treten Sintereffekte auf, die ein ansteigendes Elastizitätsmodul zur Folge haben. Die Wärmedämmschicht ist mithin weniger dehnungstolerant, so daß die thermomechanischen Belastungen zu sog. Segmentierungsrissen führen, durch welche die Wärmedämmschicht zu einzelnen Schollen segmentiert.Heavy duty metal components are used in engine and turbine construction for protection against high temperatures with ceramic thermal insulation layers Mistake. The thermal insulation layers are the cheapest and most effective by thermal spray processes, such as Plasma spraying, apply to the metallic components. The ceramic so produced Thermal insulation layers have a porous, micro-cracks Structure that has a lower modulus of elasticity. Consequently can the thermal barrier coating in operation due to thermomechanical Loads of deformations that always occur are harmless to a limited extent withstand. When using the thermal insulation layers in the high temperature range (> 900 ° C), however, the ceramic changes. Sintering effects occur that result in an increasing modulus of elasticity. The thermal insulation layer is therefore less stretch tolerant, so that the thermomechanical loads lead to so-called segmentation cracks through which the thermal insulation layer segmented into individual clods.

Simulationsrechnungen und Versuche haben gezeigt, daß bei den so segmentierten, keramischen Wärmedämmschichten bei weiterer thermomechanischer Belastung ein Rißfortschritt an der Grenzfläche zur metallischen Komponente (Metallsubstrat) auftritt. Dieser Rißfortschritt führt zum Abplatzen und damit zum völligen Versagen der Wärmedämmschicht.Simulation calculations and tests have shown that in the segmented, ceramic thermal insulation layers for further thermomechanical Load a crack progress at the interface to the metallic component (Metal substrate) occurs. This crack progress leads to chipping and thus for complete failure of the thermal barrier coating.

Aus der DE 40 41 103 A1 ist ein Verfahren zur Oberflächenbehandlung von Bauteilen mittels Kugelstrahlen bekannt, bei dem zunächst eine metallische MCrAlY-Schicht als Oxidations- und Heißgaskorrosionsschicht auf die Bauteiloberfläche aufgebracht und anschließend die Schicht kugelgestrahlt wird, um eine Glättung der rauhen Schichtoberfläche zu erzielen und die Schicht zu verdichten. Eine solche metallische Schicht ist homogen und unterscheidet sich grundlegend von einer keramischen Wärmedämmschicht, die Körner und Korngrenzen aufweist.DE 40 41 103 A1 describes a method for the surface treatment of Components known by shot peening, in which initially a metallic MCrAlY layer as an oxidation and hot gas corrosion layer on the component surface applied and then the layer is shot peened to to achieve a smoothing of the rough layer surface and to compact the layer. Such a metallic layer is homogeneous and differs fundamentally of a ceramic thermal barrier coating, the grains and Has grain boundaries.

Die US 5,277,936 offenbart ein Verfahren zum Beschichten eines Bauteils aus einer Ni- oder Co-Basislegierung, bei dem ein Metallpulver und Oxide zur Herstellung einer metallischen Oxidationsschutz- und Haftschicht für eine Wärmedämmschicht durch Plasmaspritzen aufgebracht werden. Die Oxidationsschutz- und Haftschicht wird zur Verdichtung gestrahlt. Dabei soll die keramische Wärmedämmschicht gerade nicht gestrahlt werden.US 5,277,936 discloses a method for coating a component a Ni or Co-based alloy, in which a metal powder and oxides for production a metallic oxidation protection and adhesive layer for a thermal insulation layer can be applied by plasma spraying. The oxidation protection and adhesive layer is blasted for compaction. The ceramic Thermal insulation layer just not be blasted.

Der Erfindung liegt die Aufgabe zugrunde, eine Wärmedämmschicht der eingangs beschriebenen Gattung so zu verbessern, daß sie auch im Hochtemperaturbereich thermomechanisch möglichst beständig ist. Ferner soll ein Verfahren zur Herstellung einer thermomechanisch möglichst beständigen Wärmedämmschicht geschaffen werden.The invention has for its object a thermal barrier coating of the beginning to improve the genus described so that it also in the high temperature range is thermomechanically as stable as possible. A procedure is also intended for the production of a thermal insulation layer that is as stable as possible be created.

Die das Verfahren betreffende Lösung der Aufgabe ist erfindungsgemäß dadurch gekennzeichnet, daß die Wärmedämmschicht während und/oder nach dem Aufbringvorgang (thermisches Spritzen) gestrahlt wird.The solution to the problem relating to the method is thereby according to the invention characterized in that the thermal barrier coating during and / or after the application process (thermal spraying) is blasted.

In einer bevorzugten Ausgestaltung wird die Wärmedämmschicht mit kugelförmigen Partikeln gestrahlt, die bevorzugt aus Metall, Keramik oder Glas bestehen können.In a preferred embodiment, the thermal barrier coating is spherical Blasted particles, which preferably consist of metal, ceramic or glass can.

Die die Wäremdämmschicht betreffende Lösung ist erfindungsgemäß dadurch gekennzeichnet, daß die Wärmedämmschicht durch Strahlen gebildete, oberflächennahe Risse aufweist. According to the invention, the solution relating to the thermal barrier coating is thereby characterized in that the thermal barrier coating formed by radiation, near the surface Shows cracks.

Der Vorteil besteht darin, daß das Auftreten ungünstiger Schollengrößen vermieden wird, indem die Wärmedämmschicht durch das Strahlen mit Partikeln definiert vorgeschädigt wird. Durch die hohe kinetische Energie der Partikel entstehen beim Aufprall zahlreiche kleine oberflächennahe Risse in der Wärmedämmschicht. Darüberhinaus werden sog. Mikrokontaktflächen, die den Sinterprozeß beschleunigen, aufgebrochen. Auf diese Weise werden bei thermomechanischer Belastung sowohl die Sintereffekte reduziert, als auch die Bildung unterkritischer, kleiner Schollen bei der Segmentierung infolge der vielen Rißstarter gefördert.The advantage is that the occurrence of unfavorable clod sizes is avoided is by the thermal barrier coating by blasting with particles is defined pre-damaged. Due to the high kinetic energy of the particles numerous small cracks near the surface occur in the thermal insulation layer on impact. In addition, so-called. Micro contact surfaces that the Accelerate sintering process, broken up. This way, at thermomechanical Stress both reduced the sintering effects, as well as the Formation of subcritical, small clods in the segmentation as a result of promoted many crack starters.

Anders als bei den metallischen Schichten, die durch Strahlen verdichtet werden, wurde das Strahlen bei Wärmedämmschichten stets vermieden, um die Keramik nicht zu beschädigen. Letzteres gilt für durch Aufdampfen hergestellter Wärmedämmschichten weiter. Der überraschende Effekt gemäß der vorliegenden Erfindung tritt insbesondere bei durch thermisches Spritzen hergestellten Wärmedämmschichten auf, welche zahlreiche Mikrorisse aufweisen. Durch das erfindungsgemäße Strahlen wird eine solche Schicht nicht verdichtet, sondern zur Vermeidung der Sinterproblematik insgesamt aufgelockert.Unlike the metallic layers that are compressed by radiation, blasting has always been avoided in the case of thermal insulation layers Do not damage ceramics. The latter applies to those produced by vapor deposition Thermal insulation layers continue. The surprising effect according to the present The invention occurs particularly when manufactured by thermal spraying Thermal insulation layers, which have numerous microcracks. By the blasting according to the invention does not compact such a layer, but rather loosened overall to avoid the problem of sintering.

Im folgenden wird die Erfindung anhand eines Ausführungsbeispiels näher erläutert, bei dem die Wärmedämmschicht auf eine metallische Triebwerkskomponente aufgebracht wird.The invention is explained in more detail below using an exemplary embodiment, in which the thermal barrier coating on a metallic engine component is applied.

Eine thermisch hochbelastete, metallische Triebwerkskomponente, wie eine Turbinenschaufel, wird mit einer keramischen Wärmedämmschicht versehen. Die Wärmedämmschicht wird durch Plasmaspritzen auf die metallische Komponente aufgebracht und weist eine poröse, von Mikrorissen durchzogene Struktur auf. Um das Auftreten ungünstiger Schollengrößen bei Sintereffekten während des Betriebs im Hochtemperaturbereich zu vermeiden, wird die keramische Wärmedämmschicht während oder unmittelbar nach dem Herstellprozeß mittels Plasmaspritzen, d.h. dem Aufbringen der keramischen Wärmedämmschicht auf die metallische Komponente, durch Metallkugelstrahlen definiert vorgeschädigt. Durch die hohe kinetische Energie der Metallkugeln entstehen beim Aufprall auf die Wärmedämmschicht viele kleine oberflächennahe Risse. Die Schicht wird insgesamt aufgelockert. Außerdem werden sog. Mikrokontaktflächen, die den Sinterprozeß beschleunigen, aufgebrochen. Das Strahlen kann während des Aufbringens der Wärmedämmschicht beginnen und sich danach fortsetzen oder auch erst unmittelbar nach dem Aufbringen beginnen.A thermally highly stressed, metallic engine component, like one Turbine blade, is provided with a ceramic thermal barrier coating. The thermal barrier coating is applied by plasma spraying onto the metallic component applied and has a porous, micro-cracked Structure on. The occurrence of unfavorable clod sizes with sintering effects Avoid the ceramic during operation in the high temperature range Thermal barrier layer during or immediately after the manufacturing process by means of plasma spraying, i.e. the application of the ceramic thermal barrier coating on the metallic component, defined by metal shot peening pre-damaged. Due to the high kinetic energy of the metal balls When impacting the thermal insulation layer, many small near-surface Cracks. The layer is loosened overall. In addition, so-called micro contact surfaces, that accelerate the sintering process, broken up. The Blasting can start while the thermal barrier coating is being applied and continue afterwards or only immediately after application kick off.

Claims (4)

Verfahren zur Herstellung einer Wärmedämmschicht, bei dem eine keramische Wärmedämmschicht durch thermisches Spritzen auf eine metallische Komponente aufgebracht wird, dadurch gekennzeichnet, daß die Wärme dämmschicht während und/oder nach dem Aufbringvorgang gestrahlt wird.Process for producing a thermal barrier coating, in which a ceramic Thermal insulation layer by thermal spraying on a metallic Component is applied, characterized in that the heat insulation layer is blasted during and / or after the application process. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Wärmedämmschicht mit kugelförmigen Partikeln gestrahlt wird.A method according to claim 1, characterized in that the thermal barrier coating is blasted with spherical particles. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Partikel aus Metall, Keramik oder Glas bestehen.A method according to claim 1 or 2, characterized in that the particles consist of metal, ceramic or glass. Wärmedämmschicht, die durch thermisches Spritzen auf eine metallische Komponente aufgebracht ist, keramisch ist und eine poröse Struktur aufweist, dadurch gekennzeichnet, daß die Wärmedämmschicht durch Strahlen gebildete, oberflächennahe Risse aufweist.Thermal barrier coating by thermal spraying on a metallic Component is applied, is ceramic and has a porous structure, characterized in that the thermal barrier coating by blasting formed, near-surface cracks.
EP98118456A 1997-10-02 1998-09-30 Thermal barrier coating and process for its manufacture Expired - Lifetime EP0906964B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19743579A DE19743579C2 (en) 1997-10-02 1997-10-02 Thermal barrier coating and process for its manufacture
DE19743579 1997-10-02

Publications (3)

Publication Number Publication Date
EP0906964A2 true EP0906964A2 (en) 1999-04-07
EP0906964A3 EP0906964A3 (en) 2002-09-18
EP0906964B1 EP0906964B1 (en) 2008-01-02

Family

ID=7844397

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98118456A Expired - Lifetime EP0906964B1 (en) 1997-10-02 1998-09-30 Thermal barrier coating and process for its manufacture

Country Status (5)

Country Link
US (1) US6214475B1 (en)
EP (1) EP0906964B1 (en)
JP (1) JP4603105B2 (en)
DE (1) DE19743579C2 (en)
ES (1) ES2297872T3 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2483528C (en) * 2002-10-09 2015-07-21 Ishikawajima-Harima Heavy Industries Co., Ltd. Rotating member and method for coating the same
DE10335425B3 (en) 2003-08-01 2004-08-26 Öko-Insel Energietechnik GmbH Heat storage unit, for storing heat, comprises base body made from ceramic materials for storing heat and having heat-conducting insert surrounded by protective layer
DE102004050474A1 (en) * 2004-10-16 2006-04-20 Mtu Aero Engines Gmbh Process for producing a component coated with a wear protection coating
DE102005030266A1 (en) * 2005-06-29 2007-01-18 Mtu Aero Engines Gmbh Blade of a turbomachine with a blade tip armor
DE102005037448A1 (en) * 2005-08-09 2007-02-15 Mtu Aero Engines Gmbh Thermal barrier coating system
DE102005050873B4 (en) * 2005-10-21 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Process for producing a segmented coating and component produced by the process
DE102014222684A1 (en) * 2014-11-06 2016-05-12 Siemens Aktiengesellschaft Segmented thermal barrier coating made of fully stabilized zirconium oxide

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4280975A (en) * 1979-10-12 1981-07-28 General Electric Company Method for constructing a turbine shroud
JPS62274062A (en) * 1986-05-23 1987-11-28 Toyota Motor Corp Production of ceramic coated member
EP0455996A1 (en) * 1990-05-02 1991-11-13 Sulzer Metco (US) Inc. Composite thermal spray powder of metal and non-metal
EP0897019A1 (en) * 1997-07-18 1999-02-17 FINMECCANICA S.p.A. AZIENDA ANSALDO Method and device for forming porous ceramic coatings, in particular thermal barrier coatings, on metal substrates

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6021237B2 (en) * 1977-01-05 1985-05-25 株式会社日立製作所 damping material
JPS5887273A (en) * 1981-11-18 1983-05-25 Hitachi Ltd Parts having ceramic coated layer and their production
CN1007847B (en) * 1984-12-24 1990-05-02 住友特殊金属株式会社 Process for producing magnets having improved corrosion resistance
JPS62112769A (en) * 1985-11-12 1987-05-23 Tadahiro Shimazu Formation of thermally sprayed film having superior wear and corrosion resistance and durability
JPS6338565A (en) * 1986-08-04 1988-02-19 Nippon Kokan Kk <Nkk> Method for reinforcing ceramic film
US5277936A (en) * 1987-11-19 1994-01-11 United Technologies Corporation Oxide containing MCrAlY-type overlay coatings
JPH0250947A (en) * 1988-08-11 1990-02-20 Yamada Kinzoku Boshoku Kk Sealing treatment for sprayed deposit
JPH02254144A (en) * 1989-03-27 1990-10-12 Nippon Steel Corp Manufacture of coated cutting tool having excellent wear resistance and chipping resistance
US5073433B1 (en) * 1989-10-20 1995-10-31 Praxair Technology Inc Thermal barrier coating for substrates and process for producing it
DE4041103A1 (en) * 1990-12-21 1992-07-02 Mtu Muenchen Gmbh METHOD FOR TREATMENT OF COMPONENTS
JP2821295B2 (en) * 1991-10-30 1998-11-05 東芝タンガロイ株式会社 Tool components with excellent fracture resistance
JPH05271900A (en) * 1992-03-23 1993-10-19 Mitsubishi Heavy Ind Ltd Heating and pressurizing method of thermally sprayed film
DE4303135C2 (en) * 1993-02-04 1997-06-05 Mtu Muenchen Gmbh Thermal insulation layer made of ceramic on metal components and process for their production
JP3087504B2 (en) * 1993-02-26 2000-09-11 三菱マテリアル株式会社 Manufacturing method of surface-coated tungsten carbide based cemented carbide cutting tools with excellent wear and fracture resistance
JPH07243018A (en) * 1994-03-08 1995-09-19 Mitsubishi Heavy Ind Ltd Surface modification method for heat insulating film
US5597272A (en) * 1994-04-27 1997-01-28 Sumitomo Electric Industries, Ltd. Coated hard alloy tool
US5674616A (en) * 1995-02-06 1997-10-07 Conversion Technologies International, Inc. Glass beads having improved fracture toughness
JP3501194B2 (en) * 1996-03-19 2004-03-02 株式会社豊田中央研究所 Spray method
US5851409A (en) * 1996-12-24 1998-12-22 General Electric Company Method for removing an environmental coating
US6042898A (en) * 1998-12-15 2000-03-28 United Technologies Corporation Method for applying improved durability thermal barrier coatings

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4280975A (en) * 1979-10-12 1981-07-28 General Electric Company Method for constructing a turbine shroud
JPS62274062A (en) * 1986-05-23 1987-11-28 Toyota Motor Corp Production of ceramic coated member
EP0455996A1 (en) * 1990-05-02 1991-11-13 Sulzer Metco (US) Inc. Composite thermal spray powder of metal and non-metal
EP0897019A1 (en) * 1997-07-18 1999-02-17 FINMECCANICA S.p.A. AZIENDA ANSALDO Method and device for forming porous ceramic coatings, in particular thermal barrier coatings, on metal substrates

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 012, no. 165 (C-496), 18. Mai 1988 (1988-05-18) & JP 62 274062 A (TOYOTA MOTOR CORP), 28. November 1987 (1987-11-28) *

Also Published As

Publication number Publication date
ES2297872T3 (en) 2008-05-01
EP0906964A3 (en) 2002-09-18
EP0906964B1 (en) 2008-01-02
JPH11158599A (en) 1999-06-15
DE19743579A1 (en) 1999-04-15
US6214475B1 (en) 2001-04-10
JP4603105B2 (en) 2010-12-22
DE19743579C2 (en) 2001-08-16

Similar Documents

Publication Publication Date Title
DE69707056T2 (en) Process for repairing a thermal barrier layer
EP0776985B1 (en) Method for applying a metallic adhesion layers for ceramic insulating layer on metallic articles
DE4238369C2 (en) Component made of a metallic base substrate with a ceramic coating
DE60222613T2 (en) Method of locally repairing an article coated with a thermal barrier structure
DE69509334T2 (en) Scoops with tips on zirconium oxide biscuits with macroriss structure and manufacturing process therefor
DE60301074T2 (en) Method for removing the coating of a through-hole in a component and component processed in this way
DE102005033176A1 (en) Abradable coatings for a 7FA + E-stage 1 and process for producing the coatings
DE60105830T2 (en) Method for removing a metal layer of a layer system
DE102005050873A1 (en) Process to manufacture a ceramic-coated gas turbine engine blade incorporating a regular array of surface irregularities
WO2005072884A1 (en) Method for removing a layer
WO2013004213A1 (en) Method for producing a cylinder liner surface and cylinder liner
DE102008014726A1 (en) Method of shot blasting of integrally bladed rotors
WO2005031038A1 (en) Wear-resistant layer, component comprising such a wear-resistant layer, and production method
EP1552037B1 (en) Method for removing a layer area of a component
WO2006042506A1 (en) Method for producing a component covered with a wear-resistant coating
EP0906964A2 (en) Thermal barrier coating and process for its manufacture
EP3458431B1 (en) Process for producing a ceramic heat shields having a reaction coating
EP1382707A1 (en) Layer system
DE102008004559A1 (en) Method for processing a thermally loaded component
EP2603355B1 (en) Method for removing a layer from a surface of a body
DE10026044C1 (en) Coating vehicle suspension springs comprises heat treating the spring surface by shot peening, mechanical and/or thermal pre treating the spring surface, and partially coating the spring surface by thermal spraying
DE102009020674A1 (en) Manufacturing coated component, comprises bearing metal alloy- or wear protective layer on component surface by spraying process, and post-treating component with surface layer subsequently by tapping/hammering process using hammer head
EP1598444B1 (en) Process to adjust the electric conductivity of a coating on a machine component by dry ice blasting, the electric conductivity being variable by pressure
WO2010088879A1 (en) Method for producing a wear-resistant coating on a component
AT390964B (en) METHOD FOR PRODUCING EROSION PROTECTION FOR TURBINE BLADES

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES GMBH

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

RIC1 Information provided on ipc code assigned before grant

Free format text: 7C 23C 4/10 A, 7C 23C 4/12 B, 7C 23C 4/18 B, 7C 04B 35/5831 B

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20030306

AKX Designation fees paid

Designated state(s): ES FR GB IT

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

17Q First examination report despatched

Effective date: 20031107

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): ES FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20080103

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2297872

Country of ref document: ES

Kind code of ref document: T3

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20081003

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20100927

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20110928

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20120926

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121001

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120930

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20130920

Year of fee payment: 16

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20141007

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20131001

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20140930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140930