EP0318803B1 - Composition de revêtement pour la protection à haute température - Google Patents

Composition de revêtement pour la protection à haute température Download PDF

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Publication number
EP0318803B1
EP0318803B1 EP88119394A EP88119394A EP0318803B1 EP 0318803 B1 EP0318803 B1 EP 0318803B1 EP 88119394 A EP88119394 A EP 88119394A EP 88119394 A EP88119394 A EP 88119394A EP 0318803 B1 EP0318803 B1 EP 0318803B1
Authority
EP
European Patent Office
Prior art keywords
weight
protective layer
yttrium
temperature protective
nickel
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
EP88119394A
Other languages
German (de)
English (en)
Other versions
EP0318803A1 (fr
Inventor
Lorenz Dr. Singheiser
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.)
GE Vernova GmbH
ABB AG Germany
Original Assignee
Asea Brown Boveri AG Germany
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 Asea Brown Boveri AG Germany filed Critical Asea Brown Boveri AG Germany
Publication of EP0318803A1 publication Critical patent/EP0318803A1/fr
Application granted granted Critical
Publication of EP0318803B1 publication Critical patent/EP0318803B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • 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
    • 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.
  • Such high-temperature protective layers are used above all 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.
  • high-temperature protective layers are intended to slow down or completely prevent the effects of high-temperature corrosion, especially of sulfur, oil ash, oxygen, alkaline earths and vanadium.
  • Such high-temperature protective layers are designed so that they can be applied directly to the base material of the component to be protected.
  • 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.
  • nickel superalloys in particular are used as the base material.
  • Such high-temperature protective layers have a matrix in which an aluminum-containing phase is embedded.
  • this top layer does not have particularly good adhesion, and is therefore worn away over time by the action of corrosion, so that the protection for the high-temperature protective layer that is automatically created as a result is lost. Over time, the corrosion progresses so far that the matrix of the high-temperature protective layer itself is attacked.
  • An improved high-temperature layer has become known from EP-A-0 134 821.
  • the well-known protective layer is an oxide dispersion hardened nickel-based alloy with a high chromium and aluminum content. Silicon and zirconium or silicon and tantalum are optionally provided as adhesion-increasing additives, which should contribute to the Improve oxidation resistance and adhesion to components. As practice shows, however, not with the desired success.
  • the high-temperature protective layer according to the invention which is also an oxide dispersion-hardened alloy, has not only the known elements such as nickel, chromium and aluminum, as well as silicon and zirconium or tantalum, but also contents of up to 2% of yttrium and / or hafnium.
  • the oxidation resistance is considerably increased in comparison with known high-temperature protective layers, since it also has aluminum-containing phases which enable the formation of an aluminum oxide-containing cover layer.
  • an additional aluminum-nickel-chromium-oxide layer is formed on the aluminum oxide-containing top layer, which significantly increases the protection of the high-temperature protective layer and the component underneath.
  • silicon and tantalum With the addition of silicon and tantalum, the formation of an aluminum oxide cover layer can also be achieved.
  • the high-temperature protective layer according to the invention produced with one or the other additive experiences a considerably better adhesive strength on the components than known layers of this type. This also applies to its cover layers.
  • the firm and permanent adhesion of the protective layer and its cover layer is achieved by the percentage of yttrium and / or hafnium that is specifically determined for the alloy.
  • the high-temperature protective layer according to the invention is formed by an alloy which contains chromium, aluminum, nickel, yttrium, silicon and zirconium. Instead of ytrium, yttrium and hafnium or hafnium alone can also be used.
  • Such an alloy has 25 to 27% by weight of chromium, 4 to 7% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon, and 1 to 2% by weight of zirconium, the remaining part of the alloy is formed by nickel.
  • the 0.2 to 2% by weight ytrrium can also be replaced by 0.2 to 2% by weight yttrium and hafnium or by 0.2 to 2% by weight hafnium.
  • a high temperature protective layer with the same properties is achieved by using an alloy containing chromium, aluminum, yttrium, nickel, silicon and tantalum.
  • the proportion of yttrium can be replaced by yttrium and hafnium or hafnium alone.
  • an alloy which contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon, 0.1 contains up to 3% by weight of tantalum, the remainder of the alloy consisting of nickel.
  • the 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by 0.2 to 2% by weight of hafnium. All weights refer to the total weight of the respective alloy.
  • All the alloys described here are in the same way for the formation of a high-temperature protective layer suitable. Regardless of which of the alloys described above they are formed, aluminum oxide cover layers are formed in each case under operating conditions on these protective layers, which form equally quickly and equally strongly with each of the alloy compositions according to the invention, and also at temperatures which are greater than 950 ° C are not removed.
  • 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 plasma spraying.
  • An alloy is used for the coating, which contains 25 to 27% by weight of chromium, 4 to 7% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 3% by weight of silicon, 1 to 2% by weight of zirconium having. The rest of the alloy consists of nickel.
  • the 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by 0.2 to 2% by weight of hafnium.
  • this alloy it is also possible to use an alloy which contains 23 to 27% by weight of chromium, 3 to 5% by weight of aluminum, 0.2 to 2% by weight of yttrium, 1 to 2.5% by weight of silicon, 0.1 up to 3% by weight of tantalum, the remainder of the alloy being nickel.
  • the 0.2 to 2% by weight of yttrium can also be replaced by 0.2 to 2% by weight of yttrium and hafnium or by the same amount of hafnium alone.
  • All weight figures refer to the total weight the alloy used.
  • the material forming the alloy is in powder form and preferably has a grain size of 45 ⁇ m.
  • the component is heated to 800 ° C. using the plasma.
  • the alloy is applied directly to the base material of the component.
  • Argon and hydrogen are used as the plasma gas.
  • the component is subjected to a heat treatment. This takes place in a high vacuum annealing furnace. A pressure is maintained in it that is less than 0.66 Pa (5x10 ⁇ 3 Torr). After reaching the vacuum, the furnace is heated to a temperature of 1100 ° C.
  • the above temperature is held for about 1 hour with a tolerance of about +/- 4 ° C.
  • the heating of the furnace is then switched off.
  • the coated and heat-treated component is slowly cooled in the oven. Its production is finished after cooling. All alloy variants are applied in the same way.

Landscapes

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

Claims (6)

  1. Couche de protection à haute température, caractérisée par le fait que celle-ci contient en pourcents en poids: 25 à 27 % de chrome, 4 à 7 % d'aluminium, 0,2 à 2 % d'yttrium et/ou de hafnium, 1 à 3 % de silicium et 1 à 2 % de zirconium, le reste étant du nickel.
  2. Couche de protection à haute température, caractérisée par le fait que celle-ci contient en pourcents en poids: 25 à 27 % de chrome, 4 à 7 % d'aluminium, 0,2 à 2 % d'yttrium, 1 à 3 de silicium et 1 à 2 % de zirconium, le reste étant du nickel.
  3. Couche de protection à haute température, caractérisée par le fait que celle-ci contient en pourcents en poids: 23 à 27 % de chrome, 3 à 5 % d'aluminium, 0,2 à 2 % d'yttrium, 1 à 2,5 % de silicium et 0,1 à 3 % de tantale, le reste étant du nickel.
  4. Couche de protection à haute température, caractérisée par le fait que celle-ci contient en pourcents en poids: 23 à 27 % de chrome, 3 à 5 % d'aluminium 0,2 à 2 % d'yttrium et/ou de haffnium, 1 à 2,5 % de silicium et 0,1 à 3 % de tantale, le reste étant du nickel.
  5. Matériau de base pour la fabrication d'une couche de protection à haute température selon l'une des revendications 1 à 4, caractérisé par le fait que le matériau constituant l'alliage se présente sous forme de poudre avec une dimension de grain de 45 µm de préférence.
  6. Procédé de réalisation d'une couche de protection à haute température selon l'une des revendications 1 à 4, caractérisé par le fait que, préalablement à l'application de la couche de protection, on nettoie l'organe à revêtir par des moyens chimiques, on augmente sa rugosité par sablage et on le réchauffe à 800 °C au moyen de plasma.
EP88119394A 1987-11-28 1988-11-22 Composition de revêtement pour la protection à haute température Expired - Lifetime EP0318803B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3740478A DE3740478C1 (de) 1987-11-28 1987-11-28 Hochtemperatur-Schutzschicht
DE3740478 1987-11-28

Publications (2)

Publication Number Publication Date
EP0318803A1 EP0318803A1 (fr) 1989-06-07
EP0318803B1 true EP0318803B1 (fr) 1993-06-23

Family

ID=6341537

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88119394A Expired - Lifetime EP0318803B1 (fr) 1987-11-28 1988-11-22 Composition de revêtement pour la protection à haute température

Country Status (3)

Country Link
US (1) US4973445A (fr)
EP (1) EP0318803B1 (fr)
DE (2) DE3740478C1 (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2675415B1 (fr) * 1991-04-22 1995-06-30 Creusot Loire Tole plaquee inoxydable et procede de realisation de cette tole plaquee.
EP1260608A1 (fr) * 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Procédé pour la déposition d'un couche de liaison à base de MCrAlY
EP1260612A1 (fr) 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd Couche de liason ou revêtement en MCrAlY
EP1295970A1 (fr) * 2001-09-22 2003-03-26 ALSTOM (Switzerland) Ltd Revêtement de l'alliage du type MCrAlY
EP1295969A1 (fr) * 2001-09-22 2003-03-26 ALSTOM (Switzerland) Ltd Procédé pour la croissance d'un revêtement de MCrAlY ainsi qu'un objet revêtu de cet alliage
US6942929B2 (en) 2002-01-08 2005-09-13 Nianci Han Process chamber having component with yttrium-aluminum coating
US7371467B2 (en) 2002-01-08 2008-05-13 Applied Materials, Inc. Process chamber component having electroplated yttrium containing coating
EP1327702A1 (fr) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Revêtement de liaison de type MCrAlY et procédé de depôt de ce revêtement de liason de type MCrAlY
CA2473565C (fr) * 2002-01-18 2010-12-07 Alstom Technology Ltd Couche de protection haute temperature
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
EP1426759B1 (fr) 2002-12-06 2011-11-16 Alstom Technology Ltd Méthode non-destructive pour la détermination du la déplétion d'un revêtement
EP1426458B1 (fr) * 2002-12-06 2008-03-12 ALSTOM Technology Ltd Procédé pour le dépot local d'une couche de MCrAlY
EP1426760A1 (fr) 2002-12-06 2004-06-09 ALSTOM Technology Ltd Méthode non-destructive pour déterminer la température de service d'un métal d'un composant
EP1428982B1 (fr) * 2002-12-06 2009-02-04 ALSTOM Technology Ltd Méthode pour déposer localement un revêtement de type MCrAlY
EP1491659B1 (fr) * 2003-06-26 2006-06-07 ALSTOM Technology Ltd Méthode d'application d'un système de couches
US7875200B2 (en) * 2008-05-20 2011-01-25 United Technologies Corporation Method for a repair process
DE102009010026A1 (de) * 2009-02-21 2010-08-26 Mtu Aero Engines Gmbh Bauteil für eine Strömungsmaschine
CN102808178A (zh) * 2011-05-30 2012-12-05 昆山市瑞捷精密模具有限公司 一种具有耐高温耐磨涂层的锌合金模具

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US3837894A (en) * 1972-05-22 1974-09-24 Union Carbide Corp Process for producing a corrosion resistant duplex coating
GB1426438A (en) * 1972-11-08 1976-02-25 Rolls Royce Nickel or cobalt based alloy composition
US4088479A (en) * 1976-01-16 1978-05-09 Westinghouse Electric Corp. Hot corrosion resistant fabricable alloy
US4095003A (en) * 1976-09-09 1978-06-13 Union Carbide Corporation Duplex coating for thermal and corrosion protection
EP0025263B1 (fr) * 1979-07-25 1983-09-21 The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Alliages à base de nickel et/ou de cobalt pour des élémentes d'un moteur à turbine à gaz
US4312682A (en) * 1979-12-21 1982-01-26 Cabot Corporation Method of heat treating nickel-base alloys for use as ceramic kiln hardware and product
US4419416A (en) * 1981-08-05 1983-12-06 United Technologies Corporation Overlay coatings for superalloys
US4439248A (en) * 1982-02-02 1984-03-27 Cabot Corporation Method of heat treating NICRALY alloys for use as ceramic kiln and furnace hardware
US4743514A (en) * 1983-06-29 1988-05-10 Allied-Signal Inc. Oxidation resistant protective coating system for gas turbine components, and process for preparation of coated components
DE3372501D1 (en) * 1983-07-22 1987-08-20 Bbc Brown Boveri & Cie High-temperature protective coating
DE3683091D1 (de) * 1985-05-09 1992-02-06 United Technologies Corp Schutzschichten fuer superlegierungen, gut angepasst an die substrate.
DE3612568A1 (de) * 1986-04-15 1987-10-29 Bbc Brown Boveri & Cie Hochtemperatur-schutzschicht

Also Published As

Publication number Publication date
DE3740478C1 (de) 1989-01-19
US4973445A (en) 1990-11-27
DE3882024D1 (de) 1993-07-29
EP0318803A1 (fr) 1989-06-07

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