Classifications

• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
  • C22C29/02—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides
  • C22C29/06—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds
  • C22C29/067—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds comprising a particular metallic binder
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C1/00—Making non-ferrous alloys
  • C22C1/04—Making non-ferrous alloys by powder metallurgy
  • C22C1/05—Mixtures of metal powder with non-metallic powder
  • C22C1/059—Making alloys comprising less than 5% by weight of dispersed reinforcing phases
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
  • C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
  • C22C32/0052—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents only carbides
• • 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
• • 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
  • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]
• • 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.]
  • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
  • Y10T428/12576—Boride, carbide or nitride component

Definitions

• the present invention relates to a new corrosion-resistant and wear-resistant high-temperature composite material based on an alloy of the type MCrAlY as matrix metal with platinum and / or rhodium as alloying elements in amounts of 5 to 15% by weight, a method for producing this high-temperature Composite material and its use.
• MCrAlY alloys The use of materials with the general designation MCrAlY alloys is known from the field of gas turbine construction, in particular aircraft engines, where M is a metal from the group of iron, cobalt and nickel or combinations of these elements. Materials of this type are described in US-A-3 874 901, US-A-53 928 026, US-A-3 542 530 and US-A-3 754 903.
• MCrAlY alloys with the aim of corrosion resistance to increase has led to alloy types containing precious metals.
• An MCrAlY alloy with 3 to 12% by weight of platinum or rhodium is described in US Pat. No. 3,918,139.
• Platinum-containing NiCrAl-based coating alloys have proven excellent corrosion resistance in many cases in the past.
• hard materials such as oxides and nitrides can be added to the base alloys in accordance with US Pat. Nos. 3,879,831 and 4,124,737. It is also known from US Pat. No. 4,275,124 to increase the wear behavior of MCrAlY alloys by carbides formed in situ or by alloyed carbides.
• the carbides embedded in the MCrAlY matrix react more or less strongly in the matrix due to the physical and chemical properties of this composite system under the operating temperatures that occur.
• the reaction rate increases with increasing temperature zu and carbides of the 6th subgroup (eg Cr3C2) are broken down faster at the same temperature than that of the 4th subgroup (eg TiC, NbC). Since the efficiency of many systems operating at high temperatures can be increased further by increasing the temperature, high-temperature stable, corrosion and wear-resistant materials are required.
• the object of the invention is therefore to improve the high-temperature stability of the composite materials made of MCrAlY matrix and hard materials in order to overcome the disadvantages of the known material combinations. Accordingly, temperature-stable, corrosion-resistant and wear-resistant alloys should be made available, which can be used at temperatures of 600 to 1100 ° C.
• the additional positive effect of platinum in this context is known to be an improvement in the corrosion behavior through improved oxide adhesion on the surface.
• the platinum content of the MCrAlY matrix can be up to 15% by weight, the carbide content can vary between 0.01 and 75% by weight.
• This invention thus relates to a corrosion-resistant and wear-resistant high-temperature composite material based on an alloy of the type MCrAlY as a matrix metal with platinum and / or rhodium as alloying elements in amounts of 5 to 15% by weight, with hard material particles in the form of the matrix metal carbides of the elements vanadium, niobium, tantalum, titanium, zirconium, hafnium, chromium, molybdenum and / or tungsten and / or mixtures thereof in amounts of 0.01 to 75% by weight, preferably 5 to 75% by weight, based on the high-temperature composite material.
• the carbide particle size is less than 50 ⁇ m.
• the carbide particles contained are compact.
• Corresponding matrix alloys of the MCrAlY type with platinum and / or rhodium additives in powder form as matrix materials for composite materials with dispersed hard material powders have hitherto not been disclosed.
• the MCrAlY hard alloys according to the invention can preferably by suspension spraying, mechanical alloying or mixing of composite powders of MCrAlY, platinum and / or rhodium and hard materials such as carbides of the elements vanadium, niobium, tantalum, titanium, zirconium, hafnium, chromium, molybdenum and / or tungsten and / or mixtures thereof, which are produced from 5 to 15% by weight of platinum and / or rhodium and 0.01 to 75% by weight, preferably 5 to 75% by weight, of metal carbide content can be obtained.
• the invention also relates to the use of the high-temperature composite materials for the production of surface protective layers.
• the powders are processed to form the surface protective layers, preferably by means of build-up welding or thermal spraying processes such as plasma spraying, powder plasma build-up welding, high-speed flame spraying or laser coating.
• This invention also relates to the use of the high-temperature composite materials according to the invention for the production of compact components which are obtained by compacting the powdery starting materials into component blanks or components.
• Compacting processes such as sintering, hot isostatic pressing or injection molding make it possible to manufacture high-temperature-resistant, abrasion-resistant components.
• Very dense, well-adhering composite layers were produced by vacuum plasma spraying. They have been tested for corrosion resistance and adhesive strength by cyclical heating to 900 ° C and cooling to 200 ° C the. The heating, tempering and cooling cycle lasted 80 minutes. A nickel-based superalloy was used as the base material.
• Layers with different hard material contents were produced by powder plasma deposition welding and plasma spraying, and the abrasion wear behavior against SiC disks of 600 grit as the counter body was determined. All matrix-hard material combinations showed a similar behavior improved compared to the hard material-free matrix layer. The addition of 75% by volume of hard material results in a significant reduction in the wear rate, regardless of the type of hard material. Depending on the type of hard material, wear is only 55 to 70% of the wear rate of the pure matrix alloy.
• MCrAlY-platinum-hard material composite powders have been processed into compact bodies by hot isostatic pressing (HIP).
• HIP hot isostatic pressing

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• Chemical & Material Sciences (AREA)
• Engineering & Computer Science (AREA)
• Organic Chemistry (AREA)
• Materials Engineering (AREA)
• Mechanical Engineering (AREA)
• Metallurgy (AREA)
• Chemical Kinetics & Catalysis (AREA)
• Dispersion Chemistry (AREA)
• Physics & Mathematics (AREA)
• Plasma & Fusion (AREA)
• Coating By Spraying Or Casting (AREA)
• Manufacture Of Metal Powder And Suspensions Thereof (AREA)
• Powder Metallurgy (AREA)
• Manufacture Of Alloys Or Alloy Compounds (AREA)

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• 1989
  • 1989-06-06 DE DE3918380A patent/DE3918380A1/de not_active Withdrawn
• 1990
  • 1990-05-24 DE DE90109913T patent/DE59003581D1/de not_active Expired - Fee Related
  • 1990-05-24 EP EP90109913A patent/EP0401611B1/fr not_active Expired - Lifetime
  • 1990-05-29 US US07/529,583 patent/US5141821A/en not_active Expired - Fee Related
  • 1990-06-04 KR KR1019900008178A patent/KR910001079A/ko not_active Withdrawn
  • 1990-06-05 CA CA002018254A patent/CA2018254A1/fr not_active Abandoned
  • 1990-06-05 JP JP2145558A patent/JPH0344456A/ja active Pending

Patent Citations (4)

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