EP0376061A2 - Revêtement de protection à haute température - Google Patents

Revêtement de protection à haute température Download PDF

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Publication number
EP0376061A2
EP0376061A2 EP89123003A EP89123003A EP0376061A2 EP 0376061 A2 EP0376061 A2 EP 0376061A2 EP 89123003 A EP89123003 A EP 89123003A EP 89123003 A EP89123003 A EP 89123003A EP 0376061 A2 EP0376061 A2 EP 0376061A2
Authority
EP
European Patent Office
Prior art keywords
layer
intermediate layer
temperature protective
protective layer
cover 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
EP89123003A
Other languages
German (de)
English (en)
Other versions
EP0376061A3 (en
EP0376061B1 (fr
Inventor
Lorenz Dr. Singheiser
Klaus Dr. Schneider
Hermann Dr. Grünling
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.)
ABB AG Germany
ABB AB
Original Assignee
Asea Brown Boveri AG Germany
Asea Brown Boveri AB
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, Asea Brown Boveri AB filed Critical Asea Brown Boveri AG Germany
Publication of EP0376061A2 publication Critical patent/EP0376061A2/fr
Publication of EP0376061A3 publication Critical patent/EP0376061A3/de
Application granted granted Critical
Publication of EP0376061B1 publication Critical patent/EP0376061B1/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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material

Definitions

  • the invention relates to a high-temperature protective layer according to the preamble of claim 1.
  • 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 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.
  • protective layers which are essential Contain components nickel, cobalt, chrome, aluminum and yttrium.
  • the aluminum content of these protective layers is relatively high.
  • the surface of the protective layer automatically forms an aluminum oxide-containing coating which contributes to the corrosion resistance of the actual protective layer.
  • a disadvantage of these protective layers is that they are not sufficiently adapted to the base material of the components to be protected. At high temperatures, compatibility problems arise between the protective layers and the base material of the components.
  • the invention is therefore based on the object of demonstrating a high-temperature protective layer with which the disadvantages of the known protective layers of this type are avoided.
  • an intermediate layer which contains nickel, chromium, aluminum, silicon, yttrium and tantalum is first applied to the base material of the component to be coated.
  • the Pore formation can be prevented if an intermediate layer with the composition Ni25Cr5Al3Si0.5Y1TA is first applied to the component.
  • the intermediate layer is preferably applied in a thickness between 50 and 100 ⁇ m.
  • the cover layer which contains nickel, cobalt, chromium, aluminum and yttrium as essential components, is applied directly to this intermediate layer.
  • a cover layer with the composition Ni20.5Cr11.5Al2.5Si0.5Y1Ta12Co is preferably applied.
  • cover layer instead of this cover layer, one with the composition Ni23Cr9.5Al2.5Si0.5Y1Ta10Co can also be applied.
  • the intermediate layer and the top layer are applied by means of low-pressure plasma spraying.
  • the cover layer is preferably applied with a thickness between 200 and 300 ⁇ m. After the top layer has been applied, the component is then heat-treated. After the same, the high-temperature protective layer is completed.
  • the cover layer it is possible to apply the cover layer only partially, specifically at the locations of the components that are subject to very high thermal stress.
  • the cover layer is then embedded in the intermediate layer at these points.
  • the intermediate layer In the areas that are subject to high thermal stress, the intermediate layer is only between 50 and 100 ⁇ m thick, while in the other areas it is applied up to 300 ⁇ m thick.
  • the cover layer is then applied with a thickness between 200 and 300 ⁇ m to the thinly applied intermediate layer in the regions subjected to high thermal stress, in such a way that its surface is flush with the intermediate layer in the edge regions.
  • FIG. 1 shows a vertical section through the high-temperature protective layer 1 according to the invention. This is formed by an intermediate layer 2 and a cover layer 3.
  • the high-temperature protective layer 1 is applied to the thermally highly stressed surface of a gas turbine blade 4, which is shown in regions in FIG. 1.
  • the gas turbine blade 4 is made of an austenitic material, preferably a superalloy based on nickel.
  • the intermediate layer 2, the composition of which corresponds to the state of equilibrium which occurs after a longer diffusion time between the cover layer 3 and the material of the gas turbine blade 4, is first applied to its thermally highly stressed surface 4F by means of low-pressure plasma spraying.
  • the intermediate layer 2 consists of nickel, chromium, aluminum, silicon, yttrium and tantalum.
  • the cover layer 3 has the composition Ni25Cr5AL3Si0.5Y1Ta.
  • the cover layer 3 is also applied with low-pressure plasma spraying.
  • the cover layer preferably has a thickness between 200 and 300 ⁇ m. Its main components are nickel, cobalt, chromium, aluminum and yttrium.
  • the cover layer 3 has a composition in the form of Ni20.5Cr11.5Al2.5Si0.5Y1Ta12Co.
  • a cover layer with this composition is also applied with a thickness of 200 to 300 ⁇ m.
  • the application of the cover layer is followed by a two-hour heat treatment of the high-temperature protective layer 1 in a vacuum at 1120 ° C. After the heat treatment has ended, the high-temperature protective layer 1 is finished.
  • FIG. 2 shows a further possibility for coating the gas turbine blade 4.
  • Such gas turbine blades are subjected to less thermal stress in the foot and shroud area. Mechanical loads, on the other hand, are very high in these areas.
  • the cover layer 3 is therefore only partially applied according to the invention.
  • the intermediate layer 2 is first applied to the surface 4F of the gas turbine blade 4.
  • the intermediate layer 2 is applied with a thickness of 50 to 100 ⁇ m in the region 5 that is subjected to high thermal stress, while it is applied with a thickness of 200 to 300 ⁇ m in the region 6 that is subjected to less thermal stress.
  • the intermediate layer 2 has the same composition as the intermediate layer 2 shown in FIG. 1 and explained in the associated description.
  • the cover layer 3 is applied to the intermediate layer 2 with a thickness between 200 and 300 ⁇ m.
  • the thickness of the cover layer 3 is selected so that the surface 3F of the cover layer 3 lies in one plane with the surface 2F of the intermediate layer 2, and a flush transition between the two layers 2 and 3 is ensured.
  • the top layer 3 can have the same compositions have, as the cover layer 3 shown in Figure 1, which is explained in the associated description.
  • the application of the two layers 2 and 3 is in turn followed by a heat treatment.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Inorganic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP89123003A 1988-12-24 1989-12-13 Revêtement de protection à haute température Expired - Lifetime EP0376061B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3843834 1988-12-24
DE3843834A DE3843834A1 (de) 1988-12-24 1988-12-24 Hochtemperatur-schutzschicht

Publications (3)

Publication Number Publication Date
EP0376061A2 true EP0376061A2 (fr) 1990-07-04
EP0376061A3 EP0376061A3 (en) 1990-09-26
EP0376061B1 EP0376061B1 (fr) 1993-10-20

Family

ID=6370221

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89123003A Expired - Lifetime EP0376061B1 (fr) 1988-12-24 1989-12-13 Revêtement de protection à haute température

Country Status (2)

Country Link
EP (1) EP0376061B1 (fr)
DE (2) DE3843834A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0845547A1 (fr) * 1996-11-30 1998-06-03 ROLLS-ROYCE plc Revêtement resistant à haute température pour pièce en superalliage et procédé de sa fabrication
US5981091A (en) * 1994-12-24 1999-11-09 Rolls-Royce Plc Article including thermal barrier coated superalloy substrate

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2126458C1 (ru) * 1998-03-31 1999-02-20 Конструкторское бюро "Салют" - филиал Государственного космического научно- производственного центра им.М.В.Хруничева Покрытие

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB660076A (en) * 1949-01-24 1951-10-31 Standard Telephones Cables Ltd Improvements in or relating to metallic structures
DE3144745A1 (de) * 1981-11-11 1983-05-19 Brown, Boveri & Cie Ag, 6800 Mannheim Hochtemperaturschutzschicht
DE3426201A1 (de) * 1984-07-17 1986-01-23 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Verfahren zum aufbringen von schutzschichten
FR2615871B1 (fr) * 1987-05-26 1989-06-30 Snecma Pieces de turbomachine en superalliage comportant un revetement protecteur metalloceramique

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5981091A (en) * 1994-12-24 1999-11-09 Rolls-Royce Plc Article including thermal barrier coated superalloy substrate
EP0845547A1 (fr) * 1996-11-30 1998-06-03 ROLLS-ROYCE plc Revêtement resistant à haute température pour pièce en superalliage et procédé de sa fabrication

Also Published As

Publication number Publication date
EP0376061A3 (en) 1990-09-26
EP0376061B1 (fr) 1993-10-20
DE3843834A1 (de) 1990-07-05
DE58905975D1 (de) 1993-11-25

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