EP2381005A1 - Système de couche pour composants de turbine - Google Patents

Système de couche pour composants de turbine Download PDF

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Publication number
EP2381005A1
EP2381005A1 EP10004293A EP10004293A EP2381005A1 EP 2381005 A1 EP2381005 A1 EP 2381005A1 EP 10004293 A EP10004293 A EP 10004293A EP 10004293 A EP10004293 A EP 10004293A EP 2381005 A1 EP2381005 A1 EP 2381005A1
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EP
European Patent Office
Prior art keywords
layer
thermal barrier
barrier coating
intermediate layer
linear expansion
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.)
Withdrawn
Application number
EP10004293A
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German (de)
English (en)
Inventor
Jochen Dr. Barnikel
Friedhelm Schmitz
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.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP10004293A priority Critical patent/EP2381005A1/fr
Publication of EP2381005A1 publication Critical patent/EP2381005A1/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • C23C4/134—Plasma spraying

Definitions

  • the invention relates to a layer system comprising a substrate, a thermal barrier coating disposed on the substrate and an erosion control layer.
  • the invention relates to a method for producing a turbine component, in particular a steam turbine component, with a substrate, to which a thermal barrier layer is connected, wherein an erosion control layer is applied to the thermal barrier coating.
  • the steam parameters can be more than 600 ° C, which leads to increased thermal demands on the materials. Therefore, those materials must be used which have a high creep strength. However, such materials usually have no ideal property in terms of oxidation resistance. The oxidation resistance is usually not sufficient for the extreme steam parameters.
  • Suitable coatings used in extreme thermal stresses are aluminum-containing coatings. Such coatings have the advantage that when applying and curing the layer by diffusion of aluminum in the base material, a good connection to the material to be protected is achieved. In addition, an AL 2 O 3 layer is formed which protects the material against oxidation.
  • austenitic steels reach their limits due to unfavorable physical properties, such as high coefficient of thermal expansion or low thermal conductivity, various variants of high-strength, ferritic martensitic steels with chromium contents of 9% by weight to 12% by weight are developed.
  • thermal barrier coatings Another technical challenge is the application of the thermal barrier coatings to a turbine component.
  • One solution to this technical challenge is the use of an adhesive layer between the base material and the thermal barrier coating.
  • This adhesive layer which is also referred to as bond coating, causes not only an improved adhesion of the ceramic thermal barrier coating but also a protection of the base material against oxidation and corrosion.
  • a further protective layer which may also be referred to as a topcoat.
  • Suitable materials for use as adhesive layer and topcoating include Ni / Cr80 / 20 and MCrAlY.
  • the use of the above-mentioned adhesive layers or top coatings is good on base materials based on nickel-based alloy.
  • the problem here is the use of the aforementioned adhesive layers and top coatings against ferritic base materials (1 wt .-% to 2.5 wt .-% chromium or 9 wt .-% to 12 wt .-% chromium - steels) and compared a ZrO 2- litämm layer as the aforementioned adhesive layers have significantly higher thermal expansion coefficients. This leads to higher stresses or strains compared with the base material as well as with respect to the thermal barrier coating, which can lead to cracking.
  • the erosion protection layer and the thermal insulation layer arranged thereunder have different coefficients of linear expansion ⁇ WDS or ⁇ TOP .
  • This problem is currently solved by limiting the erosion control layer to a maximum of 80 ⁇ m, which limits the protective effect.
  • the layer system is developed in such a way that an intermediate layer is arranged between the thermal barrier coating and the erosion layer, which represents a compromise with regard to the linear expansion coefficients ⁇ WDS and ⁇ TOP .
  • the coefficient of linear expansion ⁇ ZW of the intermediate layer should be chosen such that it is greater than the linear expansion coefficient ⁇ WDS .
  • the intermediate layer whose coefficient of linear expansion ⁇ ZW lies between the coefficients of thermal expansion ⁇ WDS of the thermal barrier layer and the coefficient of linear expansion ⁇ TOP of the erosion layer leads to a reduction of the stresses, whereby the cracking and chip-off behavior is minimized and thus larger layer thicknesses are possible in order to minimize erosion erosion , Advantageous developments are specified in the subclaims.
  • the thermal barrier coating of zirconium dioxide is formed and the intermediate layer has a limit proportion of metallic particles.
  • the intermediate layer has a limit proportion of metallic particles.
  • the intermediate layer of ferrite is formed.
  • a ferrite is in this case a crystallographic modification of the iron and has a comparatively similar coefficient of linear expansion as the erosion layer. Chipping off or causing cracks is thereby further minimized.
  • the intermediate layer is applied by means of atmospheric plasma spraying, wherein a powder is used according to the following table: element Concentration in% by weight preferably CR 22-26 23 - 24 al 5-8 6 - 7 Rare earth 0,5 - 2 Fe Base (rest)
  • the intermediate layer zirconium dioxide should be present in this powder in an amount of between 30% by weight and 70% by weight, in particular 50% by weight.
  • FIG. 1 shows a schematic arrangement of a layer according to the invention.
  • an adhesive layer 2 which may also be referred to as a bond coating, applied by a suitable method.
  • a thermal barrier coating 3 is applied by a suitable method in a suitable manner.
  • the turbine component in particular a steam turbine component, such. B. may be part of an inner housing or a turbine blade, consists of a ferritic base material 1.
  • a thermal barrier coating 3 is connected at this ferritic base material 1.
  • This thermal barrier coating 3 is, for example, a zirconium dioxide thermal barrier coating or a zirconium oxide partially stabilized on yttrium. Other thermal barrier coatings are conceivable.
  • an adhesive layer 2 which can also be referred to as a bond coat applied.
  • the adhesive layer 2 is applied to the ferritic base material 1 by an atmospheric plasma spraying process.
  • an erosion protection layer 5 Over the thermal barrier coating 3 is an erosion protection layer 5, which can also be referred to as top-coating applied. Between the erosion protection layer 5 and the thermal barrier coating 3, an intermediate layer 4 is arranged, which is applied to the thermal barrier coating 3 by an atmospheric plasma spraying process.
  • the powder used has the following composition: element Concentration in% by weight preferably CR 22-26 23 - 24 al 5-8 6 - 7 Rare earth 0,5 - 2 Fe Base (rest)
  • weight percentages given in the table can be combined with one another in any desired manner.
  • the ferritic base material 1 which may also be referred to as a substrate, the thermal barrier coating 3, the adhesive layer 2, the intermediate layer 4 and the erosion protection layer 5 form a layer system 6.
  • the thermal barrier coating 3 may be formed of zirconium dioxide (ZrO 2 ), wherein the intermediate layer 4 comprises a limit proportion of metallic particles.
  • the coefficient of linear expansion ⁇ ZW of the intermediate layer 4 is greater than the coefficient of linear expansion ⁇ WDS of the thermal barrier coating 3.
  • the intermediate layer 4 may be formed of a ferrite.
  • the thermal barrier coating 3 has a linear expansion coefficient ⁇ WDS of substantially 8 (10 -6 K -1 at 20 ° C.).
  • the coefficient of linear expansion ⁇ ZW of the ferrite is essentially 11 (10 -6 K -1 at 20 ° C).
  • the layer system 6 can be arranged on a turbine component, in particular a steam turbine component.
  • the method for producing this turbine component, in particular the steam turbine component takes place in that in a first step on a substrate 1, a thermal barrier coating 3 by means of an adhesive layer 2 and on this thermal barrier coating 3 erosion protection layer 5 is applied, wherein between the thermal barrier coating 3 and the erosion control layer 5 an intermediate layer 4 is arranged with a suitable coefficient of linear expansion ⁇ ZW .
  • the intermediate layer 4 is applied by means of atmospheric plasma spraying using a powder according to the table described above.
  • the intermediate layer comprises 30% by weight to 70% by weight of zirconium dioxide, in particular 50% by weight of zirconium dioxide, in order to adapt the coefficients of linear expansion ⁇ ZW and ⁇ TOP .

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  • 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)
EP10004293A 2010-04-22 2010-04-22 Système de couche pour composants de turbine Withdrawn EP2381005A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10004293A EP2381005A1 (fr) 2010-04-22 2010-04-22 Système de couche pour composants de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10004293A EP2381005A1 (fr) 2010-04-22 2010-04-22 Système de couche pour composants de turbine

Publications (1)

Publication Number Publication Date
EP2381005A1 true EP2381005A1 (fr) 2011-10-26

Family

ID=42340648

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10004293A Withdrawn EP2381005A1 (fr) 2010-04-22 2010-04-22 Système de couche pour composants de turbine

Country Status (1)

Country Link
EP (1) EP2381005A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108350560A (zh) * 2015-11-05 2018-07-31 西门子股份公司 制造用于由空心的氧化铝球和最外部的玻璃层构成的隔热层的防腐蚀保护层的方法和构件以及材料混合物

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3091548A (en) * 1959-12-15 1963-05-28 Union Carbide Corp High temperature coatings
US3977660A (en) * 1974-02-28 1976-08-31 Toyo Calorizing Ind. Co., Ltd. Blast-furnace tuyere having excellent thermal shock resistance and high durability
JPH0320451A (ja) * 1989-06-16 1991-01-29 Hitachi Ltd セラミック被覆タービン動翼
WO1994008069A1 (fr) * 1992-09-30 1994-04-14 United Technologies Corporation Materiau de revetement en ceramique composite
EP1382707A1 (fr) * 2002-07-17 2004-01-21 Siemens Aktiengesellschaft Systeme stratifie
EP1970461A1 (fr) * 2007-03-14 2008-09-17 Siemens Aktiengesellschaft Pièce de turbine dotée d'une couche d'isolation thermique

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3091548A (en) * 1959-12-15 1963-05-28 Union Carbide Corp High temperature coatings
US3977660A (en) * 1974-02-28 1976-08-31 Toyo Calorizing Ind. Co., Ltd. Blast-furnace tuyere having excellent thermal shock resistance and high durability
JPH0320451A (ja) * 1989-06-16 1991-01-29 Hitachi Ltd セラミック被覆タービン動翼
WO1994008069A1 (fr) * 1992-09-30 1994-04-14 United Technologies Corporation Materiau de revetement en ceramique composite
EP1382707A1 (fr) * 2002-07-17 2004-01-21 Siemens Aktiengesellschaft Systeme stratifie
EP1970461A1 (fr) * 2007-03-14 2008-09-17 Siemens Aktiengesellschaft Pièce de turbine dotée d'une couche d'isolation thermique

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108350560A (zh) * 2015-11-05 2018-07-31 西门子股份公司 制造用于由空心的氧化铝球和最外部的玻璃层构成的隔热层的防腐蚀保护层的方法和构件以及材料混合物

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