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EP0134821B1 - Revêtement protecteur à haute température - Google Patents

Revêtement protecteur à haute température Download PDF

Info

Publication number
EP0134821B1
EP0134821B1 EP83107217A EP83107217A EP0134821B1 EP 0134821 B1 EP0134821 B1 EP 0134821B1 EP 83107217 A EP83107217 A EP 83107217A EP 83107217 A EP83107217 A EP 83107217A EP 0134821 B1 EP0134821 B1 EP 0134821B1
Authority
EP
European Patent Office
Prior art keywords
weight
alloy
temperature protective
nickel
protective 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.)
Expired
Application number
EP83107217A
Other languages
German (de)
English (en)
Other versions
EP0134821A1 (fr
Inventor
Andrew R. Nicoll
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Priority to EP83107217A priority Critical patent/EP0134821B1/fr
Priority to DE8383107217T priority patent/DE3372501D1/de
Priority to AT83107217T priority patent/ATE28335T1/de
Priority to US06/631,578 priority patent/US4546052A/en
Priority to JP59149774A priority patent/JPH0676669B2/ja
Publication of EP0134821A1 publication Critical patent/EP0134821A1/fr
Application granted granted Critical
Publication of EP0134821B1 publication Critical patent/EP0134821B1/fr
Expired 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12937—Co- or Ni-base component next to Fe-base component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12944—Ni-base component

Definitions

  • the invention relates to a high-temperature protective layer according to the preamble of claim 1.
  • Such high-temperature protective layers are mainly used where the base material of components made of heat-resistant steels and / or alloys that are used at temperatures above 600 ° C is to be protected. These high-temperature protective layers are intended to slow down the effects of high-temperature corrosion, especially of sulfur, oil ash, oxygen, alkaline earths and vanadium.
  • the high-temperature protective layers are applied directly to the base material of the component.
  • High-temperature protective layers are of particular importance for components of gas turbines. They are mainly applied to rotor blades and guide vanes as well as to heat accumulation segments in gas turbines.
  • An austenitic material based on nickel, cobalt or iron is preferably used to manufacture these components. In the manufacture of gas turbine components, nickel superalloys in particular are used as the base material.
  • a high-temperature protective layer which is formed by an alloy which has M-Cr-AI-Y as the base material.
  • M stands for Ni, NiCo, Co, Fe.
  • the applied high-temperature protective layer has a matrix in which an aluminum-containing phase is embedded. If a component that is provided with such a high-temperature protective layer is exposed to an operating temperature of more than 950 ° C., the aluminum contained in the phase begins to diffuse to the surface, where an AL 2 0 3 top layer is formed .
  • This top layer does not have particularly good adhesion and is therefore removed by the action of corrosion. Over time, the corrosion spreads so far that the matrix itself is ultimately attacked.
  • high-temperature protective layers on which such cover layers are formed, are best suited to protecting components made of austenitic materials from high-temperature corrosion.
  • An alloy is known from EP-A-25263, the base material of which contains chromium, titanium, aluminum and nickel.
  • the alloy can contain rare earth metals, hafnium and silicon as further additives.
  • the independent formation of a cover layer containing aluminum oxide at a temperature of more than 950 ° C is not used with this alloy.
  • EP-A-81170 describes a high-temperature protective layer whose base material consists essentially of chromium, silicon, boron, iron and nickel.
  • the alloy is added with aluminum.
  • the silicon content is limited to a defined value. Measures to increase the adhesive strength of the self-forming cover layer containing aluminum oxide are not described here.
  • the invention is therefore based on the object of providing a high-temperature protective layer which has an optimally adhering, durable top layer.
  • the alloy according to the invention is an oxide dispersion hardened alloy. It shows a significant improvement in oxidation resistance compared to already known high-temperature protective layers. In the case of the applied high-temperature protective layer, it should be noted that it likewise has aluminum-containing phases which enable the formation of an aluminum oxide-containing cover layer. If zirconium and silicon are alloyed to the base material that forms the high-temperature protective layer alloy (claim 1), an additional aluminum-nickel-chromium-oxide layer is formed on the aluminum oxide-containing cover layer, which layer protects the high-temperature protective layer and the one underneath Component significantly increased.
  • the high-temperature protective layer according to the invention also has the property that it has a substantially better adhesive strength on the components. This also applies to their top layer.
  • a high-temperature protective layer with the same properties is achieved by using an alloy which contains chromium, aluminum, nickel, silicon and tantalum (claim 2).
  • All of the alloys described here are suitable for the formation of a high-temperature protective layer. Regardless of which of the alloys described above, they are formed in any case under operating conditions on these protective layers aluminum oxide cover layers, which are not removed even at temperatures that are higher than 900 ° C.
  • the invention is explained in more detail using an exemplary embodiment which describes the production of a coated gas turbine component.
  • the gas turbine component to be coated is made of an austenitic material, in particular a nickel superalloy. Before coating, the component is first chemically cleaned and then roughened with a sandblast. The component is coated under vacuum using the plasma spraying process.
  • An alloy is used for the coating, which has 27% by weight of chromium, 7% by weight of aluminum, 3% by weight of silicon, 1% by weight of zirconium, the remaining part of the alloy being formed by nickel.
  • the weight specifications relate to the total weight of the Alloy.
  • the powdery alloy preferably has a grain size of 45 microns.
  • the component Before the high-temperature protective layer is applied, the component is heated to approximately 800 ° C. using the plasma stream.
  • the alloy that forms the high-temperature protective layer is applied directly to the base material of the component. Argon and hydrogen are used as the plasma gas.
  • the plasma current is approximately 580 amperes and the applied voltage is 80 volts.
  • the furnace heating is then switched off.
  • the coated and heat-treated component is slowly cooled in the oven. This concludes its manufacture.
  • An analysis of the applied high-temperature protective layer shows that it has a matrix composition which contains 28% by weight of chromium, 3% by weight of silicon, 3.6% by weight of aluminum, the rest being nickel.
  • two separated phases can be determined, in which one contains 14.4% by weight aluminum, 2.4% by weight silicon, 8.9% by weight chromium and nickel.
  • the second phase has 11% by weight silicon, 26% by weight zirconium, 4% by weight chromium and nickel.
  • the same process can also be used to apply a high-temperature protective layer which has a nickel-chromium-aluminum base material to which silicon and tantalum have been alloyed.
  • a high-temperature protective layer an alloy is preferably used which has 27% by weight of chromium, 5% by weight of aluminum, 2.5% by weight of silicon and 1 to 3% by weight of tantalum.
  • the high-temperature protective layer has a matrix composition which contains 27% by weight of chromium, 3% by weight of aluminum, 2.4% by weight of silicon, Contains 7% by weight of tantalum, the remainder being nickel. Furthermore, when the high-temperature protective layer is formed, a phase is precipitated which contains 8.5% by weight aluminum, 1.8% by weight silicon, 5.8% by weight tantalum, 5.8% by weight chromium, wherein the remaining part consists of nickel.

Landscapes

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

Claims (3)

1. Couche protectrice pour hautes températures, qui comporte une couche de recouvrement contenant un oxyde métallique et qui est constituée d'un alliage à base de nickel et contenant du chrome et de l'aluminium, en particulier pour composants constitués d'un matériau austénitique, caractérisée par le fait que l'alliage contient de 25 à 27% en poids de chrome, de 4 à 7% en poids d'aluminium, de 1 à 3% en poids de silicium et de 1 à 2% en poids de zirconium, par rapport au poids total de l'alliage, le reste étant constitué de nickel.
2. Couche protectrice pour hautes températures, qui comporte une couche de recouvrement contenant un oxyde métallique et qui est constituée d'un alliage à base de nickel et contenant du chrome et de l'aluminium, en particulier pour composants constitués d'un matériau austénitique, caractérisée par le fait que l'alliage contient de 25 à 27% en poids de chrome, de 3 à 5% en poids d'aluminium, de 1 à 2,5% en poids de silicium et de 1 à 3% en poids de tantale, par rapport au poids total de l'alliage, le reste étant composé de nickel.
3. Couche protectrice pour hautes températures selon l'une revendications 1 ou 2, caractérisée par le fait que l'alliage est un alliage durci par dispersion d'oxyde.
EP83107217A 1983-07-22 1983-07-22 Revêtement protecteur à haute température Expired EP0134821B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP83107217A EP0134821B1 (fr) 1983-07-22 1983-07-22 Revêtement protecteur à haute température
DE8383107217T DE3372501D1 (en) 1983-07-22 1983-07-22 High-temperature protective coating
AT83107217T ATE28335T1 (de) 1983-07-22 1983-07-22 Hochtemperatur-schutzschicht.
US06/631,578 US4546052A (en) 1983-07-22 1984-07-17 High-temperature protective layer
JP59149774A JPH0676669B2 (ja) 1983-07-22 1984-07-20 高温保護層材料

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP83107217A EP0134821B1 (fr) 1983-07-22 1983-07-22 Revêtement protecteur à haute température

Publications (2)

Publication Number Publication Date
EP0134821A1 EP0134821A1 (fr) 1985-03-27
EP0134821B1 true EP0134821B1 (fr) 1987-07-15

Family

ID=8190587

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83107217A Expired EP0134821B1 (fr) 1983-07-22 1983-07-22 Revêtement protecteur à haute température

Country Status (5)

Country Link
US (1) US4546052A (fr)
EP (1) EP0134821B1 (fr)
JP (1) JPH0676669B2 (fr)
AT (1) ATE28335T1 (fr)
DE (1) DE3372501D1 (fr)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3225500A1 (de) * 1982-07-08 1984-01-12 Doduco KG Dr. Eugen Dürrwächter, 7530 Pforzheim Magnetischer fuehler
DE3225499C2 (de) * 1982-07-08 1984-05-24 Doduco KG Dr. Eugen Dürrwächter, 7530 Pforzheim Magnetischer Näherungssensor
DE3539029A1 (de) * 1985-11-02 1987-05-07 Bbc Brown Boveri & Cie Hochtemperatur-schutzschicht und verfahren zu ihrer herstellung
DE3612568A1 (de) * 1986-04-15 1987-10-29 Bbc Brown Boveri & Cie Hochtemperatur-schutzschicht
DE3740478C1 (de) * 1987-11-28 1989-01-19 Asea Brown Boveri Hochtemperatur-Schutzschicht
US4758480A (en) * 1987-12-22 1988-07-19 United Technologies Corporation Substrate tailored coatings
US5037070A (en) * 1990-09-20 1991-08-06 General Motors Corporation Melt containment apparatus with protective oxide melt contact surface
FR2717874B1 (fr) * 1994-03-25 1996-04-26 Gec Alsthom Transport Sa Disque multimatériaux pour freinage à haute énergie.
KR20030024685A (ko) * 2000-06-08 2003-03-26 서피스 엔지니어드 프로덕츠 코포레이션 고온 스테인레스강을 위한 코팅 시스템
US7789995B2 (en) 2002-10-07 2010-09-07 Georgia-Pacific Consumer Products, LP Fabric crepe/draw process for producing absorbent sheet
US8398820B2 (en) 2002-10-07 2013-03-19 Georgia-Pacific Consumer Products Lp Method of making a belt-creped absorbent cellulosic sheet
US7442278B2 (en) * 2002-10-07 2008-10-28 Georgia-Pacific Consumer Products Lp Fabric crepe and in fabric drying process for producing absorbent sheet
US7494563B2 (en) * 2002-10-07 2009-02-24 Georgia-Pacific Consumer Products Lp Fabric creped absorbent sheet with variable local basis weight
EP1411210A1 (fr) * 2002-10-15 2004-04-21 ALSTOM Technology Ltd Méthode de déposition d'un revêtement de type MCrAlY résistant à la fatigue et à l'oxydation
EP1428982B1 (fr) * 2002-12-06 2009-02-04 ALSTOM Technology Ltd Méthode pour déposer localement un revêtement de type MCrAlY
DE60225569T2 (de) * 2002-12-06 2009-09-03 Alstom Technology Ltd. Verfahren zur örtlichen Abscheidung einer MCrAlY - Beschichtung
EP1541713A1 (fr) * 2003-12-11 2005-06-15 Siemens Aktiengesellschaft Une couche métallique protective
US8293072B2 (en) 2009-01-28 2012-10-23 Georgia-Pacific Consumer Products Lp Belt-creped, variable local basis weight absorbent sheet prepared with perforated polymeric belt
US8540846B2 (en) 2009-01-28 2013-09-24 Georgia-Pacific Consumer Products Lp Belt-creped, variable local basis weight multi-ply sheet with cellulose microfiber prepared with perforated polymeric belt
DE102019006457A1 (de) 2019-06-07 2020-12-10 SAUKE.SEMRAU GmbH Verbundwerkstoff aus Metall und Keramik und Verfahren zu dessen Herstellung

Family Cites Families (16)

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US3547673A (en) * 1969-02-19 1970-12-15 Wall Colmonoy Corp Method of forming cermet-type protective coatings on heat resistant alloys
US3761301A (en) * 1969-04-22 1973-09-25 L Sama Processes for producing ductile high temperature oxidation resistant composites
US3741791A (en) * 1971-08-05 1973-06-26 United Aircraft Corp Slurry coating superalloys with fecraiy coatings
US4054723A (en) * 1972-11-08 1977-10-18 Rolls-Royce Limited Composite articles
US4034142A (en) * 1975-12-31 1977-07-05 United Technologies Corporation Superalloy base having a coating containing silicon for corrosion/oxidation protection
CH616960A5 (en) * 1976-02-25 1980-04-30 Sulzer Ag Components resistant to high-temperature corrosion.
US4124737A (en) * 1976-12-30 1978-11-07 Union Carbide Corporation High temperature wear resistant coating composition
US4198442A (en) * 1977-10-31 1980-04-15 Howmet Turbine Components Corporation Method for producing elevated temperature corrosion resistant articles
US4169726A (en) * 1977-12-21 1979-10-02 General Electric Company Casting alloy and directionally solidified article
DE2816520C2 (de) * 1978-04-17 1984-04-12 Brown, Boveri & Cie Ag, 6800 Mannheim Verwendung eines Hartmetalls
US4339509A (en) * 1979-05-29 1982-07-13 Howmet Turbine Components Corporation Superalloy coating composition with oxidation and/or sulfidation resistance
DE3064929D1 (en) * 1979-07-25 1983-10-27 Secr Defence Brit Nickel and/or cobalt base alloys for gas turbine engine components
US4447503A (en) * 1980-05-01 1984-05-08 Howmet Turbine Components Corporation Superalloy coating composition with high temperature oxidation resistance
JPS57155338A (en) * 1981-03-23 1982-09-25 Hitachi Ltd Metallic body with alloy coating resistant to corrosion and thermal shock
US4419416A (en) * 1981-08-05 1983-12-06 United Technologies Corporation Overlay coatings for superalloys
DE3148198A1 (de) * 1981-12-05 1983-06-09 Brown, Boveri & Cie Ag, 6800 Mannheim "hochtemperaturschutzschicht"

Also Published As

Publication number Publication date
EP0134821A1 (fr) 1985-03-27
US4546052A (en) 1985-10-08
JPS6039173A (ja) 1985-02-28
ATE28335T1 (de) 1987-08-15
DE3372501D1 (en) 1987-08-20
JPH0676669B2 (ja) 1994-09-28

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