EP0386618A1 - Elément à couche de recouvrement à base de nickel ou de cobalt - Google Patents

Elément à couche de recouvrement à base de nickel ou de cobalt Download PDF

Info

Publication number
EP0386618A1
EP0386618A1 EP90103963A EP90103963A EP0386618A1 EP 0386618 A1 EP0386618 A1 EP 0386618A1 EP 90103963 A EP90103963 A EP 90103963A EP 90103963 A EP90103963 A EP 90103963A EP 0386618 A1 EP0386618 A1 EP 0386618A1
Authority
EP
European Patent Office
Prior art keywords
base material
protective layer
coating
component according
weight
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
EP90103963A
Other languages
German (de)
English (en)
Other versions
EP0386618B1 (fr
Inventor
Albin Platz
Klaus Dr. Schweitzer
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 Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0386618A1 publication Critical patent/EP0386618A1/fr
Application granted granted Critical
Publication of EP0386618B1 publication Critical patent/EP0386618B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Definitions

  • the invention relates to a component made of a base material based on nickel or cobalt with a protective layer against oxidation, corrosion and thermal fatigue.
  • High temperature resistant super alloys based on nickel or cobalt were developed for use in turbine construction.
  • the blade material is exposed to particularly high loads, which not only withstand the high temperatures (above 950 ° C) in the turbine, but also must have a high creep resistance.
  • the blade material made of superalloys in particular is grown in large crystalline form and partly with a columnar structure using appropriate casting and crystallization techniques.
  • grain boundary deposits of easily oxidizable alloy additives such as vanadium or titanium are disadvantageously formed for the corrosion resistance. This adversely affects the surface properties, such as resistance to oxidation and corrosion, and the thermal fatigue resistance.
  • Diffusion processes have a disadvantage due to the different concentration on both sides of the boundary layer between the layer surface and the coating, which lead to diffusion pores in the region near the boundary layer, so that the protective layer flakes off at locations of high diffusion pore density when thermal voltages are superimposed.
  • the MCrAlX, Y layers tend to suffer from thermal fatigue, since there is a mismatch in the thermal expansion behavior between the base material alloy and the MCrAlYX layer and the MCrAlX, Y layers are very ductile compared to the base material.
  • chromium and / or aluminum-rich diffusion layers on the surface of the base material by powder pack cementing and / or gas diffusion coating.
  • Such layers form oxidation-resistant intermetallic phases with the base material. Due to the higher hardness of these layers with intermetallic phases, the fatigue strength of the components is disadvantageously reduced by up to 30%. Since the thermal expansion behavior is not adapted to the base material, there is a high risk of microcracks for the component, which increases with increasing layer thickness. Therefore, the layer thickness must be limited disadvantageously to less than 100 microns.
  • the components of the base material such as vanadium and titanium, which are sensitive to oxidation and corrosion are avoided and stable oxide formers, such as aluminum, for example up to 20% and chromium, for example up to 40%, are added.
  • stable oxide formers such as aluminum, for example up to 20% and chromium, for example up to 40%.
  • the object of the invention is to provide a component made of a base material based on nickel or cobalt with a protective layer, which has a higher thermal fatigue, oxidation and corrosion resistance at temperatures above 800 ° C than components with previously known coatings and the disadvantages of these Overcomes coatings and specify a method for producing such a component.
  • the invention solves the problems and disadvantages as they exist in the prior art by using the material of the base material for a coating of the same type, so that diffusion processes do not occur and adhesion problems do not occur on the oxide-free surface of the base material.
  • a chipping of protective layer particles is hereby overcome.
  • a uniform, stable and protective oxide layer is advantageously formed on the grain surface when such components are used in the oxidizing hot gas stream from, for example, turbines. Since the grain boundaries of this coating have fewer grain boundary deposits than the base material, the grain boundary corrosion is advantageously reduced.
  • the similarity of the coating material with the base material means that there are no thermal expansion differences between the layer and base material and thus no thermal stresses are induced.
  • the layer thickness is therefore advantageously not limited to less than 100 ⁇ m.
  • the base and coating material is preferably composed of the following elements: 13 to 17% by weight of Co 8 to 11% by weight of Cr 5 to 6 wt.% Al 4.5 to 5% by weight of Ti 2 to 4 wt.% Mo 0.7 to 1.2 wt% V 0.15 to 0.2 wt% C 0.01 to 0.02 wt% B 0.03 to 0.09% by weight of Zr Rest Ni
  • This superalloy is commercially available under the name IN 100, so that both the base material and the coating material are available at low cost.
  • the grain volume of the coating is preferably smaller by at least three powers of ten than the grain volume of the base material.
  • the grain boundaries of the preferred base material IN 100 have titanium and vanadium-containing grain boundary deposits, which form unstable or low-melting oxides.
  • the coating therefore preferably has fewer precipitations at the grain boundaries than the base material, which advantageously improves the resistance to oxidation and corrosion.
  • a particularly preferred embodiment of the protective layer is that the protective layer is a plasma spray layer which, owing to the high rate of solidification, advantageously crystallizes extremely fine-grained and has a low excretion rate.
  • This method has the advantage that it is suitable for mass production.
  • the surface preparation is carried out by plasma etching with an argon plasma.
  • This preparation has the advantage of being free from contamination and is compatible with a low-pressure plasma spraying process, so that both the surface preparation and the coating of the base material can be carried out on a component with an assembly process. This advantageously improves the quality, since it is not necessary to move it to another plant and there are no residence times in a normal atmosphere.
  • the surface preparation is carried out by means of chemical removal, so that a high throughput is advantageously achieved.
  • Abrasive beam processing is preferably used as surface ablation, since this method advantageously allows large-area components such as rotor disks to be prepared for a subsequent coating.
  • the coating by means of plasma spraying with a plasma spraying material in the same chemical composition as the base material can be carried out with high demands on the quality in the low pressure plasma spraying process and with large parts and / or high demands on economy by means of plasma spraying under protective gas.
  • Optimal growth of the coating on the base material is achieved by epitaxial recrystallization at a solution annealing temperature between 1150 ° C and 1250 ° C.
  • the lowest layer of the fine-grained coating recrystallizes in the transition area between the base material and the coating in the same crystal orientation as the large-volume crystallites of the base material at the coating boundary, so that an intensive interlocking between the fine-grain coating and the coarse-grained base material advantageously results, which significantly increases the adhesion compared to conventional non-proprietary coatings .
  • the coated component can then be cooled to 1000 ° C to 800 ° C at 30 ° C / min to 80 ° C / min and subjected to a multi-stage heat treatment.
  • a two-stage aging process has preferably been used to form a suitable ⁇ / ⁇ ′-structure at 1080 ° C. to 1120 ° C. for 2 hours to 6 hours, followed by 900 ° C. to 980 ° C. for Proven for 10 hours to 20 hours with intermediate cooling to 750 to 800 ° C.
  • a heat treatment With such a heat treatment, the properties of the base material which have been changed by the solution annealing are regenerated, and the strength values of the layer are advantageously increased.
  • Mechanical post-treatment of the surface of the protective layer improves the hardness by preferably shot-peening and serves to smooth the surface.
  • the surface can also be smoothed by pressure flow machining or vibratory finishing.
  • a diffusion coating as aftertreatment of the surface can preferably be carried out on the fine-grained coating.
  • This has the advantage that deep diffusions like them along the grain boundary precipitations of the base material, in which fine-grained coating with fewer grain boundary precipitations does not occur.
  • the diffusion zone in the fine-grained coating is thus advantageously more uniform and homogeneous with z.
  • the aluminum doping z. B. increases the oxidation resistance up to temperatures of 1250 ° C.
  • a coarsely crystalline turbine blade made of In 100 as the base material which is composed of the following elements: 13 to 17% by weight of Co 8 to 11% by weight of Cr 5 to 6 wt.% Al 4.5 to 5% by weight of Ti 2 to 4 wt.% Mo 0.7 to 1.2 wt% V 0.15 to 0.2 wt% C 0.01 to 0.02 wt% B 0.03 to 0.09% by weight of Zr Rest Ni the surface of the base material is removed by an average of 0.5 to 10 ⁇ m by means of argon plasma etching at a pressure of 2 kPa to 4 kPa.
  • the base material is coated with plasma spray material with the same chemical composition as the base material at a pressure of 4 kPa and a temperature of the base material of 900 ° C. for 120 seconds.
  • epitaxial recrystallization is carried out in a high vacuum furnace.
  • the component is kept at a solution annealing temperature of 1200 ° C for 4 hours and cooled to 800 ° C at a cooling rate of 60 ° C / min.
  • a two-stage heat treatment is carried out in a high vacuum at 1100 ° C for 4 hours and at 950 ° C for 16 hours with intermediate cooling at 60 ° C / min to 800 ° C.
  • the surface of the component is smoothed and solidified by blasting with zirconium oxide balls of 0.5 mm to 1 mm in diameter.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP90103963A 1989-03-09 1990-03-01 Elément à couche de recouvrement à base de nickel ou de cobalt Expired - Lifetime EP0386618B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3907625 1989-03-09
DE3907625A DE3907625C1 (fr) 1989-03-09 1989-03-09

Publications (2)

Publication Number Publication Date
EP0386618A1 true EP0386618A1 (fr) 1990-09-12
EP0386618B1 EP0386618B1 (fr) 1994-02-16

Family

ID=6375923

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90103963A Expired - Lifetime EP0386618B1 (fr) 1989-03-09 1990-03-01 Elément à couche de recouvrement à base de nickel ou de cobalt

Country Status (4)

Country Link
EP (1) EP0386618B1 (fr)
JP (1) JPH02277760A (fr)
CA (1) CA2011753A1 (fr)
DE (1) DE3907625C1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0532150A1 (fr) * 1991-09-09 1993-03-17 General Electric Company Revêtements protecteurs consolidés pour super-alliages
WO1997005299A1 (fr) * 1995-07-25 1997-02-13 Siemens Aktiengesellschaft Produit avec un corps de base metallique pourvu de canaux de refroidissement et sa fabrication
EP0863072A3 (fr) * 1997-03-05 2001-06-27 United Technologies Corporation Gaine protectrice électroformée et construction d'un élément aerodynamique profilé
EP1162284A1 (fr) * 2000-06-05 2001-12-12 Alstom (Switzerland) Ltd Procédé de réparation d'un composant revêtu
EP1805344B1 (fr) * 2004-10-16 2011-03-16 MTU Aero Engines AG Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2950436B2 (ja) * 1990-03-15 1999-09-20 株式会社東芝 複合化材料の製造方法
DE102011087159B3 (de) * 2011-11-25 2013-03-28 Mtu Aero Engines Gmbh Haftgrundvorbereitung für das Kaltgasspritzen und Kaltgasspritzvorrichtung
PL3050997T3 (pl) * 2013-09-25 2018-12-31 The Chugoku Electric Power Co., Inc. Sposób powlekania dyfuzujnego żaroodpornego elementu metalowego materiałem wzmacniającym przed pełzaniem, oraz żaroodporny element metalowy o zwiększonej wytrzymałości na pełzanie
KR102182690B1 (ko) * 2014-11-11 2020-11-25 (주) 코미코 플라즈마 처리 장치용 내부재 및 이의 제조 방법
KR102182699B1 (ko) * 2014-11-11 2020-11-25 (주) 코미코 플라즈마 처리 장치용 내부재 및 이의 제조 방법

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH653375A5 (de) * 1981-08-05 1985-12-31 United Technologies Corp Beschichtungsmaterial.
EP0207874A2 (fr) * 1985-05-09 1987-01-07 United Technologies Corporation Revêtements protecteurs pour superalliages, bien adaptés aux substrats
DE3246507C2 (de) * 1982-12-16 1987-04-09 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Hochtemperaturschutzschicht

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4532191A (en) * 1982-09-22 1985-07-30 Exxon Research And Engineering Co. MCrAlY cladding layers and method for making same
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
DE3426201A1 (de) * 1984-07-17 1986-01-23 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Verfahren zum aufbringen von schutzschichten
DE3522646A1 (de) * 1985-06-25 1987-01-08 Wiederaufarbeitung Von Kernbre Formkoerper aus schlecht schweissbarem werkstoff

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH653375A5 (de) * 1981-08-05 1985-12-31 United Technologies Corp Beschichtungsmaterial.
DE3246507C2 (de) * 1982-12-16 1987-04-09 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Hochtemperaturschutzschicht
EP0207874A2 (fr) * 1985-05-09 1987-01-07 United Technologies Corporation Revêtements protecteurs pour superalliages, bien adaptés aux substrats

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0532150A1 (fr) * 1991-09-09 1993-03-17 General Electric Company Revêtements protecteurs consolidés pour super-alliages
US5316866A (en) * 1991-09-09 1994-05-31 General Electric Company Strengthened protective coatings for superalloys
WO1997005299A1 (fr) * 1995-07-25 1997-02-13 Siemens Aktiengesellschaft Produit avec un corps de base metallique pourvu de canaux de refroidissement et sa fabrication
US5967755A (en) * 1995-07-25 1999-10-19 Siemens Aktiengesellschaft Product with a metallic basic body and method for manufacturing a product
US6156133A (en) * 1995-07-25 2000-12-05 Siemens Aktiengesellschaft Method for manufacturing a product with a metallic basic body
EP0863072A3 (fr) * 1997-03-05 2001-06-27 United Technologies Corporation Gaine protectrice électroformée et construction d'un élément aerodynamique profilé
EP1162284A1 (fr) * 2000-06-05 2001-12-12 Alstom (Switzerland) Ltd Procédé de réparation d'un composant revêtu
US6569492B2 (en) 2000-06-05 2003-05-27 Alstom Ltd Process for repairing a coated component
EP1805344B1 (fr) * 2004-10-16 2011-03-16 MTU Aero Engines AG Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure
US8920881B2 (en) 2004-10-16 2014-12-30 MTU Aero Engines AG Method for producing a component covered with a wear-resistant coating

Also Published As

Publication number Publication date
EP0386618B1 (fr) 1994-02-16
CA2011753A1 (fr) 1990-09-09
DE3907625C1 (fr) 1990-02-15
JPH02277760A (ja) 1990-11-14

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