GB2322382A - A coated superalloy article - Google Patents
A coated superalloy article Download PDFInfo
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- GB2322382A GB2322382A GB9703704A GB9703704A GB2322382A GB 2322382 A GB2322382 A GB 2322382A GB 9703704 A GB9703704 A GB 9703704A GB 9703704 A GB9703704 A GB 9703704A GB 2322382 A GB2322382 A GB 2322382A
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- United Kingdom
- Prior art keywords
- coating
- superalloy article
- chromium
- platinum
- layer
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 121
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims abstract description 194
- 238000000576 coating method Methods 0.000 claims abstract description 166
- 239000011248 coating agent Substances 0.000 claims abstract description 157
- 229910052697 platinum Inorganic materials 0.000 claims abstract description 97
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 86
- 239000010703 silicon Substances 0.000 claims abstract description 86
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 73
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 72
- 239000011651 chromium Substances 0.000 claims abstract description 72
- 229910000951 Aluminide Inorganic materials 0.000 claims abstract description 41
- 239000000919 ceramic Substances 0.000 claims abstract description 37
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 37
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 36
- 238000000151 deposition Methods 0.000 claims abstract description 36
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 36
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 36
- 239000010936 titanium Substances 0.000 claims abstract description 36
- 229910021332 silicide Inorganic materials 0.000 claims abstract description 35
- 239000012720 thermal barrier coating Substances 0.000 claims abstract description 35
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims abstract description 28
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 18
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims abstract description 18
- 229910052691 Erbium Inorganic materials 0.000 claims abstract description 14
- UYAHIZSMUZPPFV-UHFFFAOYSA-N erbium Chemical compound [Er] UYAHIZSMUZPPFV-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000005254 chromizing Methods 0.000 claims abstract description 8
- 238000007750 plasma spraying Methods 0.000 claims abstract description 7
- 238000004544 sputter deposition Methods 0.000 claims abstract description 7
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 6
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 40
- 238000000034 method Methods 0.000 claims description 39
- 229910052782 aluminium Inorganic materials 0.000 claims description 37
- 239000004411 aluminium Substances 0.000 claims description 37
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 37
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 30
- 229910052759 nickel Inorganic materials 0.000 claims description 22
- 239000000377 silicon dioxide Substances 0.000 claims description 15
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 claims description 12
- QDOXWKRWXJOMAK-UHFFFAOYSA-N dichromium trioxide Chemical compound O=[Cr]O[Cr]=O QDOXWKRWXJOMAK-UHFFFAOYSA-N 0.000 claims description 11
- 238000009792 diffusion process Methods 0.000 claims description 11
- 229910052702 rhenium Inorganic materials 0.000 claims description 9
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 claims description 9
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 8
- 238000005468 ion implantation Methods 0.000 claims description 7
- 239000013078 crystal Substances 0.000 claims description 6
- 238000005328 electron beam physical vapour deposition Methods 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 229910052706 scandium Inorganic materials 0.000 claims description 6
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 claims description 6
- 238000005240 physical vapour deposition Methods 0.000 claims description 4
- 238000009713 electroplating Methods 0.000 claims description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 abstract description 83
- 230000015572 biosynthetic process Effects 0.000 abstract description 5
- 230000007797 corrosion Effects 0.000 abstract description 2
- 238000005260 corrosion Methods 0.000 abstract description 2
- 239000011253 protective coating Substances 0.000 abstract description 2
- UMUXBDSQTCDPJZ-UHFFFAOYSA-N chromium titanium Chemical compound [Ti].[Cr] UMUXBDSQTCDPJZ-UHFFFAOYSA-N 0.000 abstract 1
- 230000003647 oxidation Effects 0.000 abstract 1
- 238000007254 oxidation reaction Methods 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 70
- 229910021357 chromium silicide Inorganic materials 0.000 description 17
- 239000002002 slurry Substances 0.000 description 10
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 8
- 229910017052 cobalt Inorganic materials 0.000 description 7
- 239000010941 cobalt Substances 0.000 description 7
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 7
- 239000000758 substrate Substances 0.000 description 6
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 6
- 229910001011 CMSX-4 Inorganic materials 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 229910000995 CMSX-10 Inorganic materials 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 230000002939 deleterious effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 229910052735 hafnium Inorganic materials 0.000 description 3
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 3
- 229910052721 tungsten Inorganic materials 0.000 description 3
- 239000010937 tungsten Substances 0.000 description 3
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- ZXGIFJXRQHZCGJ-UHFFFAOYSA-N erbium(3+);oxygen(2-) Chemical compound [O-2].[O-2].[O-2].[Er+3].[Er+3] ZXGIFJXRQHZCGJ-UHFFFAOYSA-N 0.000 description 2
- VQCBHWLJZDBHOS-UHFFFAOYSA-N erbium(III) oxide Inorganic materials O=[Er]O[Er]=O VQCBHWLJZDBHOS-UHFFFAOYSA-N 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052750 molybdenum Inorganic materials 0.000 description 2
- 239000011733 molybdenum Substances 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000011863 silicon-based powder Substances 0.000 description 2
- 238000010290 vacuum plasma spraying Methods 0.000 description 2
- XRZCZVQJHOCRCR-UHFFFAOYSA-N [Si].[Pt] Chemical compound [Si].[Pt] XRZCZVQJHOCRCR-UHFFFAOYSA-N 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- ZCDOYSPFYFSLEW-UHFFFAOYSA-N chromate(2-) Chemical compound [O-][Cr]([O-])(=O)=O ZCDOYSPFYFSLEW-UHFFFAOYSA-N 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 239000010955 niobium Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 239000002694 phosphate binding agent Substances 0.000 description 1
- 239000000049 pigment Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 description 1
Classifications
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- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5806—Thermal treatment
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
- C23C14/165—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon by cathodic sputtering
-
- 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
-
- 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
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)
- Thermal Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
A superalloy article 20 has a multilayer coating 22 comprising a MCrAIY bond coating 24, a chromium titanium and/or tantalum and silicon enriched MCrAIY layer 26, a platinum aluminide coating 28, an alumina layer 30 and a ceramic thermal barrier coating 32 The platinum aluminide coating 28 is a very good corrosion and oxidation protective coating for the superalloy article 20. The MCrAIY bond coating 24 and the chromium and silicon enriched MCrAIY layer 26 prevents silicon in the platinum aluminide-silicide coating diffusing to the superalloy article 20 to minimise the formation of silicon rich topologically close packed phases at the interface between the superalloy article 20 and the multilayer coating 22. The system forms a good bond coating for the ceramic thermal barrier coating 32. The bond coating may be applied by plasma spraying. The chromium, titanium and/or tantalum may be applied by chromising or sputtering. Additional steps include depositing yttrium, zirconium or erbium.
Description
A COATED SUPERALLOY ARTICLE AND A METHOD OF COATING
A SUPERALLOY ARTICLE
The present invention relates to coated superalloy articles and to methods of coating superalloy articles, particularly nickel and cobalt superalloy turbine blades or turbine vanes.
It is known to produce aluminide-silicide protective coatings on superalloy turbine blades or turbine vanes to extend the service lives of the turbine blades or turbine vanes.
It is known to produce aluminide-silicide coatings on a superalloy article by depositing a silicon filled organic slurry on the superalloy article and then pack aluminising as described in US4310574. The aluminium carries the silicon from the slurry with it as it diffuses into the superalloy.
Another method of producing aluminide-silicide coatings is by depositing a slurry containing elemental aluminium and silicon metal powders on a superalloy article and then heating to above 7600C to melt the aluminium and silicon in the slurry, such that they react with the superalloy and diffuse into the superalloy article as described in
US3248251. A further method of producing aluminide-silicide coatings is by repeatedly applying the aluminium and silicon containing slurry and heat treating as described in US5547770. Another method of producing aluminide- silicide coatings is by applying a slurry of an eutectic aluminiumsilicon or a slurry of elemental aluminium and silicon metal powders on a superalloy article and diffusion heat treating to form a surface layer of increased thickness and reduced silicon content, and a layering layer which comprises alternate interleaved layers of aluminide and silicide phases and a diffusion interface layer as described in published
European patent application No. 0619856A.
It is also known to produce platinum aluminide-silicide coatings on a superalloy article by coating the superalloy article with platinum, then heat treating to diffuse the platinum into the superalloy article and then simultaneously diffusing aluminium and silicon from the molten state into the platinum enriched superalloy article as described in published International patent application No. W095/23243A.
Another method of producing platinum aluminide-silicide coatings on a superalloy article is by coating the superalloy article with platinum, then heat treating to diffuse the platinum into the superalloy article, a silicon layer is applied and is then aluminised as described in published
European patent application No. 0654542A. It is also possible to diffuse the silicon into the superalloy article with the platinum as described in EP0654542A. A further method of producing platinum aluminide-silicide coatings on superalloy articles is by electrophoretically depositing platinum- silicon powder onto the superalloy article, heat treating to diffuse platinum and silicon into the superalloy article, then electrophoretically depositing aluminium and chromium powder and then heat treating to diffuse the aluminium and chromium into the superalloy article as described in US5057196.
It has been found that if a platinum aluminide- silicide coating is produced on a superalloy article that the silicon tends to diffuse to the interface between the substrate and the coating and this results in the formation of very brittle phases, topologically close packed phases (TCP phases), with the superalloy substrate. These brittle TCP phases are needle like silicon rich phases which extend into the substrate. The TCP phases are undesirable because they destroy the mechanical properties of the substrate. Also these silicon rich phases may have lower melting points than the superalloy substrate. Thus the use of a platinum aluminide-silicide coating directly onto a superalloy article is not practical because these TCP phases increase the stress concentrations in the superalloy substrate leading to premature failure of the superalloy article.
The invention therefore seeks to provide a platinum aluminide-silicide on a superalloy article without the formation of the brittle phases.
Accordingly the present invention provides a method of coating a superalloy article comprising the steps of :
(a) applying a bond coating to the superalloy article,
(b) applying a coating comprising at least one of chromium, titanium and tantalum to the bond coating and diffusing at least one of the chromium, titanium and tantalum into the bond coating to produce a layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum,
(c) and depositing a platinum aluminide-silicide coating on the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum.
Preferably step (b) comprises chromising the bond coating. Alternatively step (b) may comprise sputtering titanium, tantalum or titanium and tantalum onto the bond coating and diffusing into the bond coating.
Preferably step (a) comprises plasma spraying the bond coating onto the superalloy article.
Preferably step (a) comprises applying a MCrAlY coating, a MCrAl coating, a MCr coating or a MA1 coating to the superalloy article, where M is at least one of Ni, Co and Fe.
Preferably step (c) comprises depositing the platinum onto the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum, heat treating to diffuse the platinum, simultaneously diffusing aluminium and silicon from the molten state into the coated superalloy article.
Alternatively step (c) may comprise depositing the platinum onto the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum, heat treating to diffuse the platinum, depositing silicon and then depositing aluminium and diffusing the silicon and aluminium into the coated superalloy article.
Preferably the platinum is deposited by electroplating.
Preferably the platinum is heat treated at a temperature greater than 100 ooh. More preferably the platinum is heat treated at a temperature of 11200C for 1 to 2 hours to diffuse the platinum. Preferably the platinum is deposited to a thickness between 5 and 15 micrometers.
Preferably the chromising is at a temperature of 11000C for 5 hours.
Preferably the diffusion of aluminium and silicon is at a temperature in the range 7500C to 1120 0C.
Preferably the simultaneous diffusion of aluminium and silicon from the molten state is repeated at least once more.
There may be after step (c) an additional step of:
(d) applying a ceramic thermal barrier coating.
Alternatively there may be after step (c) the additional steps of:
(d) forming alumina on the platinum aluminide- silicide coating,
(e) applying a ceramic thermal barrier coating by physical vapour deposition.
Preferably the ceramic thermal barrier coating is deposited by electron beam physical vapour deposition.
There may be after step (b) and before step (c) an additional step of:
depositing at least one of yttrium, scandium or erbium onto the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum. Preferably the yttrium, scandium or erbium is deposited by ion implantation.
There may be after step (c) and before step (d) an additional step of
depositing at least one of yttrium or yttrium and zirconium.
There may be after step (c) and before step (d) an additional step of :
depositing at least one of chromia, silica or alumina.
This may be by depositing the chrornia, depositing the silica onto the chromia and depositing the alumina onto the silica.
There may be after step (c) and before step (d) an additional step of :
depositing erbium. Preferably the erbium is deposited by ion implantation.
The present invention also provides a coated superalloy article comprising a bond coating on the superalloy article, a layer enriched in at least one of chromium, titanium and tantalum on the bond coating, the layer enriched in at least one of chromium, titanium and tantalum having silicide phases and a platinum aluminide coating on the layer enriched in at least one of chromium, titanium and tantalum.
There may be a ceramic thermal barrier coating on the platinum aluminide coating.
Alternatively there may be an alumina layer on the platinum aluminide coating and a ceramic thermal barrier coating on the alumina layer.
Preferably the ceramic thermal barrier coating has columnar grains.
The superalloy article may be a nickel based superalloy.
The superalloy article may be a high rhenium containing nickel based superalloy article. The superalloy article may be a single crystal superalloy article.
The superalloy article may be a turbine blade or a turbine vane.
Preferably the bond coating comprises a MCrAlY coating, a MCrAl coating, a MCr coating or a MAl coating, where M is at least one of Ni, Co and Fe.
The platinum aluminide coating may comprise some silicide phases, the layer enriched in at least one of chromium, titanium and tantalum comprises some platinum aluminide and the bond coating comprises some silicide phases.
The present invention will be more fully described by way of example with reference to the accompanying drawings, in which:
Figure 1 is a cross-sectional view through a coated superalloy article according to the present invention.
Figure 2 is a cross-sectional view through a further coated superalloy article according to the present invention.
A superalloy article 10, for example a gas turbine engine turbine blade or turbine vane, has a multilayer coating 12 as shown in figure 1. The multilayer coating'lea comprises a MCrAlY bond coating 14 arranged on the superalloy article 10, a chromium and silicon enriched MCrAlY layer 16 on the MCrAlY bond coating 14 and a platinum aluminide coating 18 on the chromium and silicon enriched MCrAlY layer 16. The chromium and silicon enriched MCrAlY layer 16 generally has a greater percentage of chromium than the
MCrAlY coating 14 and also has the silicon present in the form of chromium silicide phases, additionally the chromium and silicon enriched MCrAlY layer 16 may have some platinum aluminide. The platinum aluminide coating 18 comprises platinum aluminide with some chromium silicide phases.
Additionally there may be some chromium silicide phases in the MCrAlY bond coating 14.
It is believed that the provision of the MCrAlY bond coating 14 and the chromium and silicon enriched MCrAlY layer 16 between the superalloy article 10 and the platinum aluminide coating 18 prevents the silicon in a platinum aluminide-silicide coating diffusing to the superalloy article 10. It is postulated that this is due to the chromium in the chromium enriched MCrAlY layer 16 reacting with the silicon to form chromium silicides which prevents the silicon diffusing to the superalloy article 10.
Additionally any silicon diffusing through the chromium enriched MCrAlY layer 16 will react with the chromium in the
MCrAlY bond coating 14 to form chromium silicides which reduces the amount of silicon diffusing to the superalloy article 10 and thus minimises the amount of the deleterious brittle TCP phases formed in the superalloy article 10.
Preferably the chromium enriched MCrAlY layer 16 and the
MCrAlY bond coating 14 prevent silicon diffusing to the superalloy article 10.
Thus the chromium and silicon enriched MCrAlY layer 16 may be considered to be a chromium silicide layer as this forms the majority of the layer 16. Chromium is a very strong silicide and forms a very stable chromium silicide intermetallic.
The multi layer coating 12 is produced on the superalloy article 10 by depositing a MCrAlY bond coating 14 on the superalloy article 10 by vacuum plasma spraying, argon shrouded plasma spraying, physical vapour deposition for example electron beam physical vapour deposition, or any other suitable method. The MCrAlY bond coatings are alloys generally comprising 10 to 50wt% chromium, 4 to 3Owt% aluminium, 0 to 3wt% yttrium and the balance is at least one of nickel, cobalt or iron.
A chromium coating is then deposited onto the MCrAlY bond coating 14 and the chromium is then heat treated to diffuse the chromium into the MCrAlY bond coating 14 to form the chromium enriched MCrAlY layer 16 on the MCrA1Y bond coating 14. The chromium is deposited and diffused preferably by pack chromising or out of pack vapour chromising. The chromising process requires a temperature of 11000C for 5 hours.
A platinum layer is then deposited on the chromium enriched MCrAlY layer 16 and the platinum is then heat treated to diffuse the platinum into the chromium enriched
MCrAlY layer 16. The platinum is deposited to a thickness of 5 to 15 micrometers by electroplating, physical vapour deposition or other suitable means. The platinum is heat treated at a temperature greater than 10000C, for example 1 hour at 1120 0C followed by gas fan quenching and ageing for 24 hours at 8450C.
Aluminium and silicon are then deposited and the aluminium and silicon are heat treated to diffuse the aluminium and silicon into the platinum to form the platinum aluminide-silicide coating 18. The aluminium and silicon is deposited using a slurry comprising aluminium and silicon powders dispersed in a chromate/phosphate binder and the slurry is cured to a solid matrix which holds the metal pigments in contact with the metal surface during the heat treatment. The aluminium and silicon is heat treated at a temperature in the range 7500C to 1120 0C to simultaneously diffuse the aluminium and silicon from the molten state as described in US3248251 incorporated herein by reference. The silicon may be deposited first by spraying a silicon filled slurry and then pack aluminising. The aluminium diffusing into the platinum carries the silicon with it as described in
US4310574 incorporated herein by reference. Other suitable methods of depositing and diffusing the aluminium and silicon may be used.
It may be beneficial to repeat the deposition of the aluminium and silicon and the diffusion heat treatment steps to provide a plurality of bands rich in silicon and a plurality of bands rich in aluminium with the silicon rich bands and aluminium rich bands arranged alternately through the depth of the platinum aluminide-silicide coating. This technique is described more fully in published International
Patent application No. W093/23247.
During the diffusion of the silicon and aluminium into the chromium and platinum coated MCrAlY bond coating the aluminium reacts with the platinum to form a platinum aluminide coating 18 and the silicon diffuses through the platinum to the chromium enriched MCrAlY layer to form the chromium silicide coating 16. Thus the chromium enriched
MCrAlY layer stops the silicon diffusing to the superalloy article 10.
Another superalloy article 20, for example a gas turbine engine turbine blade or turbine vane, according to the present invention has a multilayer coating 22 as shown in figure 2. The multilayer coating 22 comprises a MCrAlY bond coating 24 arranged on the superalloy article 20, a chromium and silicon enriched MCrAlY layer 26 on the MCrAlY bond coating 24, a platinum aluminide coating 28 on the chromium and silicon enriched MCrA1Y layer 26 and an alumina layer 30 on the platinum aluminide coating 28 and a ceramic thermal barrier coating 32 on the alumina layer 30. The chromium and silicon enriched MCrAlY layer 26 generally has a greater percentage of chromium than the MCrAlY bond coating 24 and also has the silicon present in the form of chromium silicide phases, additionally the chromium and silicon enriched MCrAlY layer 26 may have some platinum aluminide. The platinum aluminide coating 28 comprises platinum aluminide with some chromium silicide phases. Additionally there may be some chromium silicide phases in the MCrAlY bond coating 24.
It is believed that the provision of the MCrAlY bond coating 24 and the chromium and silicon enriched MCrAlY layer 26 between the superalloy article 20 and the platinum aluminide coating 28 prevents the silicon in a platinum aluminide-silicide coating diffusing to the superalloy article 20. It is postulated that this is due to the chromium in the chromium enriched MCrA1Y layer 26 reacting with the silicon to form chromium silicides which prevents the silicon diffusing to the superalloy article 20.
Additionally any silicon diffusing through the chromium enriched MCrAlY layer 26 will react with the chromium in the
MCrAlY bond coating 24 to form chromium silicides which reduces the amount of silicon diffusing to the superalloy article 20 and thus minimises the amount of the deleterious brittle TCP phases formed in the superalloy article 20.
Preferably the chromium enriched MCrAlY layer 26 and the
MCrAlY bond coating 24 prevent silicon diffusing to the superalloy article 20.
Thus the chromium and silicon enriched MCrAlY layer 26 may be considered to be a chromium silicide layer as this forms the majority of the layer 26. Chromium is a very strong silicide and forms a very stable chromium silicide intermetallic.
The ceramic thermal barrier coating comprises for example yttria stabilised zirconia, although other suitable ceramics may be used. Preferably the ceramic thermal barrier coating comprises columnar grains.
The multi layer coating 22 is produced on the superalloy article 20 using the same processes as described to produce the multilayer coating 12 on the superalloy article 10.
The alumina layer 30 is formed on the platinum aluminide coating 28 by heating the article in an oxygen containing atmosphere to a sufficiently high temperature to oxidise the surface of the platinum aluminide coating 28 to form alumina.
The ceramic thermal barrier coating 32 is deposited onto the alumina layer 30 by placing the superalloy article 20 into an electron beam physical vapour deposition chamber and depositing the ceramic onto the alumina layer 30 by electron beam physical vapour deposition to form a columnar grained ceramic thermal barrier coating 32. It is likely that the alumina layer 30 forms on the platinum aluminide coating 28 while the superalloy article 20 is heated in the electron beam physical vapour deposition chamber as some oxygen Is present.
Alternatively it is possible to deposit a ceramic thermal barrier coating onto the platinum aluminide coating by vacuum plasma spraying or argon shrouded plasma spraying and an alumina layer may not be formed on the platinum aluminide coating.
In the case of a multi layer coating comprising a ceramic thermal barrier coating it may be beneficial to deposit yttrium or yttrium and zirconium onto the platinum aluminide coating before depositing the ceramic thermal barrier coating. It is believed that the yttrium or yttrium and zirconium diffuses into the platinum aluminide to form fingers of yttria or yttria stabilised zirconia in the subsequently formed alumina to key the ceramic thermal barrier coating onto the platinum aluminide coating. The yttria or yttria and zirconia fingers match the yttria stabilised ceramic thermal barrier coating. The yttrium or yttrium and zirconium may be deposited by ion implantation or sputtering.
Also in the case of a multi layer coating comprising a ceramic thermal barrier coating it may be beneficial to deposit mixed oxides of chromia, silica and alumina onto the platinum aluminide coating before depositing the ceramic thermal barrier coating. It is believed that the addition of chromia, silica and alumina will key the ceramic thermal barrier coating onto the platinum aluminide coating because the chromia and silica beneficially alter the activity of the alumina. The chromia, silica and alumina may be arranged in a single layer or in three layers with a chromia layer on the platinum aluminide coating, a silica layer on the chromia layer and an alumina layer on the silica layer. The mixed oxides may be deposited by plasma spraying a balanced mixture of the oxides or sequentially plasma spraying the three oxides.
Additionally if the multilayer coating comprises a ceramic thermal barrier coating it may be beneficial to deposit erbium onto the platinum aluminide coating before depositing the ceramic thermal barrier coating. It Is believed that the addition of erbium will oxidise to form erbia to key the ceramic thermal barrier coating onto the platinum aluminide coating. It is believed that the erbia beneficially alters the activity of the alumina. The erbium may be deposited by ion implantation or sputtering.
Finally if the multilayer coating comprises a ceramic thermal barrier coating it may be beneficial to deposit yttrium, scandium or erbium onto the chromium enriched MCrAlY layer before the platinum is deposited and heat treated. The yttrium, scandium or erbium may be deposited by ion implantation or sputtering.
The ceramic thermal barrier coating 32 adheres well to the alumina layer 30 formed on the platinum aluminide coating 28. It is believed, in operation, that when all the available aluminium, for formation of an alumina layer, in the platinum aluminide coating 28 is exhausted that the silicon in the platinum aluminide coating 28 and silicon in the chromium silicide layer 26 forms a silica layer and that the ceramic thermal barrier coating 32 adheres well to the silica layer. It is believed that the silica reacts with the zirconia in the ceramic thermal barrier coating to form zirconium silicate which increases the adhesion of the ceramic thermal barrier coating 28.
We believe that the platinum in the platinum aluminidesilicide coating increases the diffusion activity of the silicon making the silicon seek out strong silicide forming elements and thus the silicon diffuses into the superalloy article to find these elements.
In tests we have deposited a platinum aluminide-silicide coating onto a low rhenium containing nickel based single crystal superalloy, for example CMSX4, and found that the silicon rich TCP phases are formed at the interface with the superalloy article. CMSX4 is produced by the Cannon-Muskegon
Corporation of 2875 Lincoln Street, Muskegon, Michigan, MI 49433-0506, USA. CMSX4 has a nominal composition of 6.4wit% tungsten, 9.5wit% cobalt, 6.5wt% chromium, 3.Owt% rhenium, 5 . 6wit% aluminium, 6 . 5wit% tantalum, 1.0wtk titanium, 0.1wit hafnium, 0.6wt% molybdenum, 0.006wt% carbon and the balance is nickel.
In tests we have deposited a platinum aluminide-silicide coating onto a high rhenium containing nickel based single crystal superalloy, for example CMSX10, and found that the silicon rich TCP phases are formed at the interface with the superalloy article. CMSX10 is produced by the Cannon
Muskegon Corporation of 2875 Lincoln Street, Muskegon,
Michigan, MI 49433-0506, USA. CMSX4 has a nominal composition range of 3.5 to 6.5wit% tungsten, 2.0 to 5.Owt% cobalt, 1.8 to 3.Owt% chromium, 5.5 to 6.5wit% rhenium, 5.3 to 6.Swt% aluminium, 8.0 to 10.Owt% tantalum, 0.2 to 0.8wt% titanium, 0.25 to 1.5wit% molybdenum, 0.02 to 0.05wt% hafnium, o to 0.03wt% niobium, 0 to 0.04wit% carbon and the balance is nickel.
In tests we have deposited a platinum aluminide-silicide coating onto a low rhenium containing nickel based single crystal superalloy, for example MAR-M002, and found that the silicon rich TCP phases are formed at the interface with the superalloy article. MAR-M002 is produced by the Martin
Marietta Corporation of Bethesda, Maryland, USA. MAR-M002 has a nominal composition of 10wit% tungsten, 10wt% cobalt, 9wt chromium, 5.5wit% aluminium, 2.5wt% tantalum, 1.5wt% titanium, 1.5wit% hafnium, 0.015wit% carbon and the balance is nickel.
Thus the use of the MCrAlY bond coating and the chromium enriched layer prevents the silicon in a platinum aluminidesilicide coating diffusing to the superalloy article by forming stable chromium silicide intermetallic phases. Thus the formation of deleterious silicon rich TCP phases at the superalloy article interface is minimised. A further benefit of using the chromium and MCrAlY bond coating is that this further improves the hot corrosion resistance of the coating.
The invention has been described with reference to a
MCrA1Y bond coating, it is also possible to use a MCrAl bond coating, a MCr bond coating or a MAl bond coating where M is at least one of nickel, cobalt or iron, however the MCrAlY is preferred. Any of these bond coatings provide environmental protection, those with chromium also provide additional protection to minimise the silicon diffusing to the superalloy article.
The invention has been described with reference to a chromium and silicon enriched coating on the bond coating, it is also possible to have a titanium and silicon, a tantalum and silicon or a titanium, tantalum and silicon enriched layer on the bond coating. In these cases the titanium and tantalum form stable silicide phases with the silicon to minimise the diffusion of the silicon to the superalloy article. However, the chromium enriched layer is preferred because chromium is a stronger silicide former than titanium and tantalum. The thickness of the titanium and tantalum layers may need to be relatively thick to provide sufficient concentration to react with the silicon after diffusion into the bond coating. The titanium and tantalum are preferably deposited onto the bond coating by sputtering, but other suitable processes may be possible.
The superalloy article may be a nickel based superalloy article or a cobalt based superalloy. The nickel based superalloy may be a high rhenium content nickel based superalloy for example CMSX10, allow rhenium content nickel based superalloy for example CMSX4 or any other nickel based single crystal superalloy. The superalloy article may be a gas turbine blade or gas turbine vane.
Claims (36)
1. A method of coating a superalloy article comprising the steps of :
(a) applying a bond coating to the superalloy article,
(b) applying a coating comprising at least one of chromium, titanium and tantalum to the bond coating and diffusing at least one of the chromium, titanium and tantalum into the bond coating to produce a layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum,
(c) and depositing a platinum aluminide-silicide coating on the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum.
2. A method as claimed in claim 1 wherein step (b) comprises chromising the bond coating.
3. A method as claimed in claim 1 wherein step (b) comprises sputtering titanium, tantalum or titanium and tantalum onto the bond coating and diffusing into the bond coating.
4. A method as claimed in claim 1, claim 2 or claim 3 wherein step (a) comprises plasma spraying the bond coating onto the superalloy article.
5. A method as claimed in any of claims 1 to 4 wherein step (a) comprises applying a MCrAlY coating, a MCrAl coating, a
MCr coating or a MAl coating to the superalloy article, where
M is at least one of Ni, Co and Fe.
6. A method as claimed in any of claims 1 to 5 wherein step (c) comprises depositing the platinum onto the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum, heat treating to diffuse the platinum, simultaneously diffusing aluminium and silicon from the molten state into the coated superalloy article.
7. A method as claimed in any of claims 1 to 5 wherein step (c) comprises depositing the platinum onto the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum, heat treating to diffuse the platinum, depositing silicon and then depositing aluminium and diffusing the silicon and aluminium into the coated superalloy article.
8. A method as claimed in claim 6 or claim 7 wherein the platinum is deposited by electroplating.
9. A method as claimed in claim 6, claim 7 or claim 8 wherein the platinum is heat treated at a temperature greater than 10000C.
10. A method as claimed in claim 9 wherein the platinum is heat treated at a temperature of 11200C for 1 to 2 hours to diffuse the platinum.
11. A method as claimed in claim 6, claim 7, claim 8, claim 9 or claim 10 wherein the platinum is deposited to a thickness between 5 and 15 micrometers.
12. A method as claimed in claim 2 wherein the chromising is 0 at a temperature of 1100 C for 5 hours.
13. A method as claimed in claim 6, claim 8, claim 9, claim 10 or claim 11 wherein the diffusion of aluminium and silicon is at a temperature in the range 7500C to 11200C.
14. A method as claimed in claim 6, claim 8, claim 9, claim 10, claim 11 or claim 13 wherein the simultaneous diffusion of aluminium and silicon from the molten state is repeated at least once more.
15. A method as claimed in any of claims 1 to 14 comprising after step (c) an additional step of:
(d) applying a ceramic thermal barrier coating.
16. A method as claimed in any of claims 1 to 14 comprising after step (c) the additional steps of:
(d) forming alumina on the platinum aluminide- silicide coating,
(e) applying a ceramic thermal barrier coating by physical vapour deposition.
17. A method as claimed in claim 16 wherein the ceramic thermal barrier coating is deposited by electron beam physical vapour deposition.
18. A method as claimed in any of claims 1 to 17 comprising after step (b) and before step (c) an additional step of:
depositing at least one of yttrium, scandium or erbium onto the layer on the bond coating which is enriched in at least one of chromium, titanium and tantalum.
19. A method as claimed in claim 18 wherein the yttrium, scandium or erbium is deposited by ion implantation.
20. A method as claimed in any of claims 15 to 19 comprising after step (c) and before step (d) an additional step of :
depositing at least one of yttrium or yttrium and zirconium.
21. A method as claimed in any of claims 15 to 19 comprising after step (c) and before step (d) an additional step of
depositing at least one of chromia, silica or alumina.
22. A method as claimed in claim 21 comprising depositing the chromia, depositing the silica onto the chromia and depositing the alumina onto the silica.
23. A method as claimed in any of claims 15 to 19 comprising after step (c) and before step (d) an additional step of
depositing erbium.
24. A method as claimed in claim 23 wherein the erbium is deposited by ion implantation.
25. A method of coating a superalloy article substantially as hereinbefore described with reference to the accompanying drawings.
26. A coated superalloy article comprising a bond coating on the superalloy article, a layer enriched in at least one of chromium, titanium and tantalum on the bond coating, the layer enriched in at least one of chromium, titanium and tantalum having silicide phases and a platinum aluminide coating on the layer enriched in at least one of chromium, titanium and tantalum.
27. A coated superalloy article as claimed in claim 26 wherein there is a ceramic thermal barrier coating on the platinum aluminide coating.
28. A coated superalloy article as claimed in claim 26 wherein there is an alumina layer on the platinum aluminide coating and a ceramic thermal barrier coating on the alumina layer.
29. A coated superalloy article as claimed in claim 28 wherein the ceramic thermal barrier coating has columnar grains.
30. A coated superalloy article as claimed in any of claims 26 to 29 wherein the superalloy article is a nickel based superalloy article.
31. A coated superalloy article as claimed in claim 30 wherein the superalloy article is a high rhenium containing nickel based superalloy article.
32. A coated superalloy article as claimed in claim 31 wherein the superalloy article is a single crystal superalloy article.
33. A coated superalloy article as claimed in any of claims 26 to 32 wherein the superalloy article is a turbine blade or a turbine vane.
34. A coated superalloy article as claimed in any of claims 26 to 33 wherein the bond coating comprises a MCrAlY coating, a MCrA1 coating, a MCr coating or a MAl coating, where M is at least one of Ni, Co and Fe.
35. A coated superalloy article as claimed in any of claims 26 to 34 wherein the platinum aluminide coating comprises some silicide phases, the layer enriched in at least one of chromium, titanium and tantalum comprises some platinum aluminide and the bond coating comprises some silicide phases.
36. A coated article substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9703704A GB2322382A (en) | 1997-02-22 | 1997-02-22 | A coated superalloy article |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9703704A GB2322382A (en) | 1997-02-22 | 1997-02-22 | A coated superalloy article |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9703704D0 GB9703704D0 (en) | 1997-04-09 |
| GB2322382A true GB2322382A (en) | 1998-08-26 |
Family
ID=10808126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9703704A Withdrawn GB2322382A (en) | 1997-02-22 | 1997-02-22 | A coated superalloy article |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2322382A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001061067A1 (en) * | 2000-02-17 | 2001-08-23 | Anatoly Nikolaevich Paderov | Combined protective coating of parts made of heat resisting alloys |
| GB2378452A (en) * | 2001-08-09 | 2003-02-12 | Rolls Royce Plc | A metallic article having a protective coating and a method therefor |
| RU2212473C1 (en) * | 2002-01-24 | 2003-09-20 | Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" | Method for depositing of coatings on alloys |
| RU2228387C2 (en) * | 2002-07-22 | 2004-05-10 | Падеров Анатолий Николаевич | Method of application of multi-layer on metal articles |
| WO2006038826A1 (en) * | 2004-03-02 | 2006-04-13 | Anatoly Nikolaevich Paderov | Method for applying multilayer coatings to metal products |
| US7060366B2 (en) * | 2003-02-19 | 2006-06-13 | General Electric Company | Article including a substrate with a metallic coating and a chromium-aluminide protective coating thereon, and its preparation and use in component restoration |
| SG137661A1 (en) * | 2004-01-19 | 2007-12-28 | Sony Corp | A multi-layer composite film and a method for forming a multi-layer composite film |
| US7547478B2 (en) * | 2002-12-13 | 2009-06-16 | General Electric Company | Article including a substrate with a metallic coating and a protective coating thereon, and its preparation and use in component restoration |
| WO2010097577A1 (en) * | 2009-02-25 | 2010-09-02 | The University Of Birmingham | Thermal barrier coatings |
| RU2402639C1 (en) * | 2009-04-01 | 2010-10-27 | Общество с ограниченной ответственностью Научно-производственное предприятие "Эверест-124" | Procedure for application of combined heat insulated coating on parts out of heat resistant alloys |
| WO2010138096A1 (en) * | 2009-05-26 | 2010-12-02 | Siemens Aktiengesellschaft | Layered coating system with a mcralx layer and a chromium rich layer and a method to produce it |
| EP3470543A1 (en) * | 2017-10-12 | 2019-04-17 | General Electric Company | Coated component and method of preparing a coated component |
| US11092019B2 (en) | 2018-10-12 | 2021-08-17 | General Electric Company | Coated component and method of preparing a coated component |
| US11686208B2 (en) | 2020-02-06 | 2023-06-27 | Rolls-Royce Corporation | Abrasive coating for high-temperature mechanical systems |
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| EP0587341A1 (en) * | 1992-09-05 | 1994-03-16 | ROLLS-ROYCE plc | High temperature corrosion resistant composite coatings |
| EP0654542A1 (en) * | 1993-11-19 | 1995-05-24 | Walbar Inc. | Improved platinum group silicide modified aluminide coating process and products |
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| EP0587341A1 (en) * | 1992-09-05 | 1994-03-16 | ROLLS-ROYCE plc | High temperature corrosion resistant composite coatings |
| EP0654542A1 (en) * | 1993-11-19 | 1995-05-24 | Walbar Inc. | Improved platinum group silicide modified aluminide coating process and products |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001061067A1 (en) * | 2000-02-17 | 2001-08-23 | Anatoly Nikolaevich Paderov | Combined protective coating of parts made of heat resisting alloys |
| GB2378452A (en) * | 2001-08-09 | 2003-02-12 | Rolls Royce Plc | A metallic article having a protective coating and a method therefor |
| RU2212473C1 (en) * | 2002-01-24 | 2003-09-20 | Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" | Method for depositing of coatings on alloys |
| RU2228387C2 (en) * | 2002-07-22 | 2004-05-10 | Падеров Анатолий Николаевич | Method of application of multi-layer on metal articles |
| US7547478B2 (en) * | 2002-12-13 | 2009-06-16 | General Electric Company | Article including a substrate with a metallic coating and a protective coating thereon, and its preparation and use in component restoration |
| US7060366B2 (en) * | 2003-02-19 | 2006-06-13 | General Electric Company | Article including a substrate with a metallic coating and a chromium-aluminide protective coating thereon, and its preparation and use in component restoration |
| SG137661A1 (en) * | 2004-01-19 | 2007-12-28 | Sony Corp | A multi-layer composite film and a method for forming a multi-layer composite film |
| WO2006038826A1 (en) * | 2004-03-02 | 2006-04-13 | Anatoly Nikolaevich Paderov | Method for applying multilayer coatings to metal products |
| WO2010097577A1 (en) * | 2009-02-25 | 2010-09-02 | The University Of Birmingham | Thermal barrier coatings |
| CN102325924A (en) * | 2009-02-25 | 2012-01-18 | 伯明翰大学 | Thermal coating |
| RU2402639C1 (en) * | 2009-04-01 | 2010-10-27 | Общество с ограниченной ответственностью Научно-производственное предприятие "Эверест-124" | Procedure for application of combined heat insulated coating on parts out of heat resistant alloys |
| WO2010138096A1 (en) * | 2009-05-26 | 2010-12-02 | Siemens Aktiengesellschaft | Layered coating system with a mcralx layer and a chromium rich layer and a method to produce it |
| CN102459685B (en) * | 2009-05-26 | 2014-11-19 | 西门子公司 | Layered coating system with a MCrAlX layer and a chromium-rich layer and method for the production thereof |
| US9222163B2 (en) | 2009-05-26 | 2015-12-29 | Siemens Aktiengesellschaft | Layered coating system with a MCrAlX layer and a chromium rich layer and a method to produce it |
| EP3470543A1 (en) * | 2017-10-12 | 2019-04-17 | General Electric Company | Coated component and method of preparing a coated component |
| US11092019B2 (en) | 2018-10-12 | 2021-08-17 | General Electric Company | Coated component and method of preparing a coated component |
| US11686208B2 (en) | 2020-02-06 | 2023-06-27 | Rolls-Royce Corporation | Abrasive coating for high-temperature mechanical systems |
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| GB9703704D0 (en) | 1997-04-09 |
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