EP0906964B1 - Couche formant une barrière thermique et procédé pour sa production - Google Patents

Couche formant une barrière thermique et procédé pour sa production Download PDF

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Publication number
EP0906964B1
EP0906964B1 EP98118456A EP98118456A EP0906964B1 EP 0906964 B1 EP0906964 B1 EP 0906964B1 EP 98118456 A EP98118456 A EP 98118456A EP 98118456 A EP98118456 A EP 98118456A EP 0906964 B1 EP0906964 B1 EP 0906964B1
Authority
EP
European Patent Office
Prior art keywords
thermal barrier
barrier coating
ceramic
particles
thermal
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.)
Expired - Lifetime
Application number
EP98118456A
Other languages
German (de)
English (en)
Other versions
EP0906964A2 (fr
EP0906964A3 (fr
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
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 filed Critical MTU Aero Engines GmbH
Publication of EP0906964A2 publication Critical patent/EP0906964A2/fr
Publication of EP0906964A3 publication Critical patent/EP0906964A3/fr
Application granted granted Critical
Publication of EP0906964B1 publication Critical patent/EP0906964B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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, which is applied by thermal spraying on a metallic component, is ceramic and has a porous structure, and a method for their preparation.
  • thermal barrier coatings In engine and turbine construction, highly stressed metallic components are provided with ceramic thermal barrier coatings to protect against high temperatures.
  • the thermal barrier coatings can be most inexpensively and effectively achieved by thermal spray techniques, e.g. Plasma spraying, apply to the metallic components.
  • the ceramic thermal barrier coatings thus produced have a porous microcracked structure which has a lower modulus of elasticity. As a result, the thermal barrier coating can withstand the damage occurring in operation due to thermo-mechanical stress on an unbounded scale.
  • the thermal barrier coatings in the high temperature range > 900 ° C
  • the ceramic changes. There are sintering effects that result in an increasing modulus of elasticity.
  • the heat-insulating layer is therefore less strain-tolerant, so that the thermomechanical loads lead to so-called segmentation cracks, through which the thermal barrier coating segments into individual clods.
  • a method for the surface treatment of components by means of shot peening is known in which first a metallic MCrAlY layer as an oxidation and hot gas corrosion layer on the component surface and then the layer is shot peened to achieve a smoothing of the rough layer surface and to densify the layer.
  • a metallic layer is homogeneous and fundamentally different from a ceramic thermal barrier coating having grains and grain boundaries.
  • the US 5,277,936 discloses a method for coating a Ni or Co based alloy component by applying a metal powder and oxides to form a metallic oxidation protection and adhesive layer for a thermal barrier coating by plasma spraying.
  • the oxidation protection and adhesive layer is blasted for densification.
  • the ceramic thermal barrier coating should not be blasted.
  • EP 0 455 996 A1 discloses a method for producing a cermet layer in which drop-shaped metal and ceramic particles are sprayed together onto a metallic substrate in such a way that the surface is rough but has no cracks.
  • Out JP 62 274062 A is a thermally sprayed layer is known in which after the application microcracks are generated on the surface by means of a laser treatment.
  • the invention has the object to improve a thermal barrier coating of the type described above so that it is thermomechanically stable as possible even in the high temperature range. Furthermore, a method be created to produce a thermomechanically stable as possible thermal barrier coating.
  • the solution of the problem relating to the method according to the invention is characterized in that the heat-insulating layer is blasted with particles during and / or after the application process (thermal spraying) in such a way that near-surface cracks occur. ;
  • the thermal barrier coating is blasted with spherical particles, which may preferably consist of metal, ceramic or glass.
  • the solution relating to the Wäremdämm Anlagen is inventively characterized in that the heat-insulating layer formed by blasting with particles, near-surface cracks.
  • the advantage is that the occurrence of unfavorable clod sizes is avoided by the thermal barrier coating is defined by the blasting with particles predamaged. Due to the high kinetic energy of the particles, numerous small shallow cracks in the thermal barrier coating occur on impact. In addition, so-called. Micro contact surfaces, which accelerate the sintering process, broken. In this way, both the sintering effects are reduced in thermomechanical stress, and the formation of subcritical, small clods in the segmentation due to the many crack starters promoted.
  • thermal barrier coatings so as not to damage the ceramic.
  • the latter applies to vapor-deposited thermal barrier coatings.
  • the surprising effect according to the present invention occurs in particular in heat-insulating layers produced by thermal spraying, which have numerous microcracks. As a result of the blasting according to the invention, such a layer is not compacted but loosened overall in order to avoid the sintering problem.
  • thermal barrier coating is applied to a metallic engine component.
  • a thermally highly stressed, metallic engine component such as a turbine blade
  • the thermal barrier coating is applied by plasma spraying onto the metallic component and has a porous structure, which is traversed by microcracks.
  • the ceramic thermal barrier coating during or immediately after the manufacturing process by means of plasma spraying, ie the application of the ceramic thermal barrier coating to the metallic component, predamaged by metal shot blasting. Due to the high kinetic energy of the metal balls, many small shallow cracks occur when they impact the thermal barrier coating. The layer is loosened overall. In addition, so-called. Micro contact surfaces, which accelerate the sintering process, broken. The blasting may begin during the application of the thermal barrier coating and then continue or even begin immediately after application.

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)

Claims (4)

  1. Procédé de production d'une couche calorifuge, pour lequel une couche calorifuge céramique est appliquée par moulage par injection thermique sur un composant métallique, caractérisé en ce que la couche calorifuge est rayonnée pendant et/ou après le processus d'application avec des particules de telle sorte que des fissures se forment près de la surface.
  2. Procédé selon la revendication 1, caractérisé en ce que la couche calorifuge est rayonnée avec des particules sphériques.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que les particules se composent de métal, de céramique ou de verre.
  4. Couche calorifuge qui est appliquée par moulage par injection thermique sur un composant métallique, est céramique et présente une structure poreuse, caractérisée en ce que la couche calorifuge présente des fissures près de la surface, formées avec des particules par rayonnement.
EP98118456A 1997-10-02 1998-09-30 Couche formant une barrière thermique et procédé pour sa production Expired - Lifetime EP0906964B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19743579 1997-10-02
DE19743579A DE19743579C2 (de) 1997-10-02 1997-10-02 Wärmedämmschicht und Verfahren zu ihrer Herstellung

Publications (3)

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

Family

ID=7844397

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98118456A Expired - Lifetime EP0906964B1 (fr) 1997-10-02 1998-09-30 Couche formant une barrière thermique et procédé pour sa production

Country Status (5)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014222684A1 (de) * 2014-11-06 2016-05-12 Siemens Aktiengesellschaft Segmentierte Wärmedämmschicht aus vollstabilisiertem Zirkonoxid

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TWI272993B (en) * 2002-10-09 2007-02-11 Ishikawajima Harima Heavy Ind Method for coating rotary member, rotary member, labyrinth seal structure and method for manufacturing rotary member
DE10335425B3 (de) * 2003-08-01 2004-08-26 Öko-Insel Energietechnik GmbH Wärmespeicher
DE102004050474A1 (de) * 2004-10-16 2006-04-20 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines mit einer Verschleißschutzbeschichtung beschichteten Bauteils
DE102005030266A1 (de) * 2005-06-29 2007-01-18 Mtu Aero Engines Gmbh Schaufel einer Turbomaschine mit einer Schaufelspitzenpanzerung
DE102005037448A1 (de) * 2005-08-09 2007-02-15 Mtu Aero Engines Gmbh Wärmedämmschichtsystem
DE102005050873B4 (de) * 2005-10-21 2020-08-06 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung einer segmentierten Beschichtung und nach dem Verfahren hergestelltes Bauteil

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JPS6021237B2 (ja) * 1977-01-05 1985-05-25 株式会社日立製作所 減衰材料
US4280975A (en) * 1979-10-12 1981-07-28 General Electric Company Method for constructing a turbine shroud
JPS5887273A (ja) * 1981-11-18 1983-05-25 Hitachi Ltd セラミツク被覆層を有する部品とその製造方法
CN1007847B (zh) * 1984-12-24 1990-05-02 住友特殊金属株式会社 制造具有改进耐蚀性磁铁的方法
JPS62112769A (ja) * 1985-11-12 1987-05-23 Tadahiro Shimazu 耐摩耗性、耐食性、耐久性に優れる容射被膜の形成方法
JPS62274062A (ja) * 1986-05-23 1987-11-28 Toyota Motor Corp セラミツク被覆部材の製造方法
JPS6338565A (ja) * 1986-08-04 1988-02-19 Nippon Kokan Kk <Nkk> セラミツクス被膜の強化方法
US5277936A (en) * 1987-11-19 1994-01-11 United Technologies Corporation Oxide containing MCrAlY-type overlay coatings
JPH0250947A (ja) * 1988-08-11 1990-02-20 Yamada Kinzoku Boshoku Kk 溶射被膜の封孔処理法
JPH02254144A (ja) * 1989-03-27 1990-10-12 Nippon Steel Corp 耐摩耗特性、耐欠損性に優れた被覆切削工具の製造方法
US5073433B1 (en) * 1989-10-20 1995-10-31 Praxair Technology Inc Thermal barrier coating for substrates and process for producing it
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014222684A1 (de) * 2014-11-06 2016-05-12 Siemens Aktiengesellschaft Segmentierte Wärmedämmschicht aus vollstabilisiertem Zirkonoxid

Also Published As

Publication number Publication date
JPH11158599A (ja) 1999-06-15
EP0906964A2 (fr) 1999-04-07
ES2297872T3 (es) 2008-05-01
DE19743579A1 (de) 1999-04-15
EP0906964A3 (fr) 2002-09-18
US6214475B1 (en) 2001-04-10
DE19743579C2 (de) 2001-08-16
JP4603105B2 (ja) 2010-12-22

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