EP1831428B1 - Composants de moteur a turbine avec revetements protecteurs contenant du silicium et du chrome sans aluminure et procedes de fabrication de tels revetements protecteurs sans aluminure - Google Patents
Composants de moteur a turbine avec revetements protecteurs contenant du silicium et du chrome sans aluminure et procedes de fabrication de tels revetements protecteurs sans aluminure Download PDFInfo
- Publication number
- EP1831428B1 EP1831428B1 EP05858676A EP05858676A EP1831428B1 EP 1831428 B1 EP1831428 B1 EP 1831428B1 EP 05858676 A EP05858676 A EP 05858676A EP 05858676 A EP05858676 A EP 05858676A EP 1831428 B1 EP1831428 B1 EP 1831428B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- silicon
- turbine engine
- chromium
- fluid composition
- containing fluid
- 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.)
- Active
Links
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 title claims abstract description 97
- 229910052710 silicon Inorganic materials 0.000 title claims abstract description 96
- 239000010703 silicon Substances 0.000 title claims abstract description 96
- 239000011253 protective coating Substances 0.000 title claims abstract description 83
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 title claims abstract description 52
- 229910052804 chromium Inorganic materials 0.000 title claims abstract description 51
- 239000011651 chromium Substances 0.000 title claims abstract description 51
- 229910000951 Aluminide Inorganic materials 0.000 title claims abstract description 32
- 238000000034 method Methods 0.000 title abstract description 8
- 239000000203 mixture Substances 0.000 claims abstract description 74
- 239000012530 fluid Substances 0.000 claims abstract description 39
- 238000010438 heat treatment Methods 0.000 claims abstract description 22
- 238000000576 coating method Methods 0.000 claims description 48
- 229910000601 superalloy Inorganic materials 0.000 claims description 32
- BLRPTPMANUNPDV-UHFFFAOYSA-N Silane Chemical compound [SiH4] BLRPTPMANUNPDV-UHFFFAOYSA-N 0.000 claims description 28
- 229910000077 silane Inorganic materials 0.000 claims description 28
- 239000011248 coating agent Substances 0.000 claims description 24
- 239000000758 substrate Substances 0.000 claims description 23
- 239000000126 substance Substances 0.000 claims description 20
- 239000002019 doping agent Substances 0.000 claims description 19
- 239000007788 liquid Substances 0.000 claims description 19
- 239000000463 material Substances 0.000 claims description 16
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 15
- 239000000654 additive Substances 0.000 claims description 8
- 239000012298 atmosphere Substances 0.000 claims description 8
- 239000011230 binding agent Substances 0.000 claims description 8
- 239000012190 activator Substances 0.000 claims description 7
- 229910052759 nickel Inorganic materials 0.000 claims description 7
- 229910052727 yttrium Inorganic materials 0.000 claims description 7
- 230000000996 additive effect Effects 0.000 claims description 6
- 229910052735 hafnium Inorganic materials 0.000 claims description 6
- 230000001590 oxidative effect Effects 0.000 claims description 6
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims description 6
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims description 5
- 239000003701 inert diluent Substances 0.000 claims description 5
- 239000000470 constituent Substances 0.000 claims description 4
- 239000000843 powder Substances 0.000 claims description 4
- BPQQTUXANYXVAA-UHFFFAOYSA-N Orthosilicate Chemical compound [O-][Si]([O-])([O-])[O-] BPQQTUXANYXVAA-UHFFFAOYSA-N 0.000 claims description 3
- 229910021357 chromium silicide Inorganic materials 0.000 claims description 3
- 150000004820 halides Chemical class 0.000 claims description 3
- UOUJSJZBMCDAEU-UHFFFAOYSA-N chromium(3+);oxygen(2-) Chemical class [O-2].[O-2].[O-2].[Cr+3].[Cr+3] UOUJSJZBMCDAEU-UHFFFAOYSA-N 0.000 claims description 2
- 230000003028 elevating effect Effects 0.000 claims 2
- 230000008569 process Effects 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 89
- 239000007789 gas Substances 0.000 description 49
- 230000007797 corrosion Effects 0.000 description 18
- 238000005260 corrosion Methods 0.000 description 18
- 239000002002 slurry Substances 0.000 description 18
- 239000000243 solution Substances 0.000 description 15
- 238000005486 sulfidation Methods 0.000 description 13
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 11
- 229910052717 sulfur Inorganic materials 0.000 description 11
- 239000011593 sulfur Substances 0.000 description 11
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 10
- 150000001875 compounds Chemical class 0.000 description 9
- 230000003647 oxidation Effects 0.000 description 9
- 238000007254 oxidation reaction Methods 0.000 description 9
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 8
- 238000001816 cooling Methods 0.000 description 8
- QTBSBXVTEAMEQO-UHFFFAOYSA-N Acetic acid Chemical compound CC(O)=O QTBSBXVTEAMEQO-UHFFFAOYSA-N 0.000 description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 7
- -1 diesel Substances 0.000 description 7
- 239000001301 oxygen Substances 0.000 description 7
- 229910052760 oxygen Inorganic materials 0.000 description 7
- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 description 6
- YXFVVABEGXRONW-UHFFFAOYSA-N Toluene Chemical compound CC1=CC=CC=C1 YXFVVABEGXRONW-UHFFFAOYSA-N 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 5
- 150000002363 hafnium compounds Chemical class 0.000 description 5
- 229910052697 platinum Inorganic materials 0.000 description 5
- 239000002904 solvent Substances 0.000 description 5
- 238000000151 deposition Methods 0.000 description 4
- 230000008021 deposition Effects 0.000 description 4
- 238000009792 diffusion process Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 239000011521 glass Substances 0.000 description 4
- 239000003446 ligand Substances 0.000 description 4
- 150000004756 silanes Chemical class 0.000 description 4
- 229960000583 acetic acid Drugs 0.000 description 3
- 239000011324 bead Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 238000007598 dipping method Methods 0.000 description 3
- 239000011241 protective layer Substances 0.000 description 3
- 238000005507 spraying Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- KFZMGEQAYNKOFK-UHFFFAOYSA-N Isopropanol Chemical compound CC(C)O KFZMGEQAYNKOFK-UHFFFAOYSA-N 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 2
- 230000001680 brushing effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 239000012362 glacial acetic acid Substances 0.000 description 2
- PDPJQWYGJJBYLF-UHFFFAOYSA-J hafnium tetrachloride Chemical compound Cl[Hf](Cl)(Cl)Cl PDPJQWYGJJBYLF-UHFFFAOYSA-J 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- NFSAPTWLWWYADB-UHFFFAOYSA-N n,n-dimethyl-1-phenylethane-1,2-diamine Chemical compound CN(C)C(CN)C1=CC=CC=C1 NFSAPTWLWWYADB-UHFFFAOYSA-N 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- BDERNNFJNOPAEC-UHFFFAOYSA-N propan-1-ol Chemical compound CCCO BDERNNFJNOPAEC-UHFFFAOYSA-N 0.000 description 2
- NREVZTYRXVBFAQ-UHFFFAOYSA-N propan-2-ol;yttrium Chemical compound [Y].CC(C)O.CC(C)O.CC(C)O NREVZTYRXVBFAQ-UHFFFAOYSA-N 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- DJYGUVIGOGFJOF-UHFFFAOYSA-N trimethoxy(trimethoxysilylmethyl)silane Chemical compound CO[Si](OC)(OC)C[Si](OC)(OC)OC DJYGUVIGOGFJOF-UHFFFAOYSA-N 0.000 description 2
- 150000003748 yttrium compounds Chemical class 0.000 description 2
- VRSLNAUKODUVCP-UHFFFAOYSA-K 2,2,2-trifluoroacetate;yttrium(3+);hydrate Chemical compound O.[Y+3].[O-]C(=O)C(F)(F)F.[O-]C(=O)C(F)(F)F.[O-]C(=O)C(F)(F)F VRSLNAUKODUVCP-UHFFFAOYSA-K 0.000 description 1
- AGOMHFKGCMKLDA-UHFFFAOYSA-K 2-ethylhexanoate;yttrium(3+) Chemical compound [Y+3].CCCCC(CC)C([O-])=O.CCCCC(CC)C([O-])=O.CCCCC(CC)C([O-])=O AGOMHFKGCMKLDA-UHFFFAOYSA-K 0.000 description 1
- OBOSXEWFRARQPU-UHFFFAOYSA-N 2-n,2-n-dimethylpyridine-2,5-diamine Chemical compound CN(C)C1=CC=C(N)C=N1 OBOSXEWFRARQPU-UHFFFAOYSA-N 0.000 description 1
- KEDNSMBVYXSBFC-UHFFFAOYSA-N 6-bromo-2-chloroquinoline-4-carbonyl chloride Chemical compound C1=C(Br)C=C2C(C(=O)Cl)=CC(Cl)=NC2=C1 KEDNSMBVYXSBFC-UHFFFAOYSA-N 0.000 description 1
- MIMUSZHMZBJBPO-UHFFFAOYSA-N 6-methoxy-8-nitroquinoline Chemical compound N1=CC=CC2=CC(OC)=CC([N+]([O-])=O)=C21 MIMUSZHMZBJBPO-UHFFFAOYSA-N 0.000 description 1
- 239000002028 Biomass Substances 0.000 description 1
- 229910001011 CMSX-4 Inorganic materials 0.000 description 1
- OERDTMGWLSPIOH-UHFFFAOYSA-N C[Si](O[SiH](C)O[Si](C)(C)C)(C)C.C[Si](O[SiH](CC)O[Si](C)(C)C)(C)C.C[Si](O[SiH](O[SiH](C)O[Si](C)(C)C)C)(C)C.CO[Si](OC)(OC)CC Chemical compound C[Si](O[SiH](C)O[Si](C)(C)C)(C)C.C[Si](O[SiH](CC)O[Si](C)(C)C)(C)C.C[Si](O[SiH](O[SiH](C)O[Si](C)(C)C)C)(C)C.CO[Si](OC)(OC)CC OERDTMGWLSPIOH-UHFFFAOYSA-N 0.000 description 1
- 241000870659 Crassula perfoliata var. minor Species 0.000 description 1
- 241000501667 Etroplus Species 0.000 description 1
- 229910017665 NH4HF2 Inorganic materials 0.000 description 1
- 239000007983 Tris buffer Substances 0.000 description 1
- 150000001298 alcohols Chemical class 0.000 description 1
- 125000000217 alkyl group Chemical group 0.000 description 1
- 238000005269 aluminizing Methods 0.000 description 1
- 239000007864 aqueous solution Substances 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 239000010953 base metal Substances 0.000 description 1
- UCRXQUVKDMVBBM-UHFFFAOYSA-N benzyl 2-amino-3-(4-phenylmethoxyphenyl)propanoate Chemical compound C=1C=CC=CC=1COC(=O)C(N)CC(C=C1)=CC=C1OCC1=CC=CC=C1 UCRXQUVKDMVBBM-UHFFFAOYSA-N 0.000 description 1
- 230000001588 bifunctional effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- DFOMPYFFBAELGP-UHFFFAOYSA-N butan-1-ol;yttrium Chemical compound [Y].CCCCO.CCCCO.CCCCO DFOMPYFFBAELGP-UHFFFAOYSA-N 0.000 description 1
- 239000004568 cement Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910052681 coesite Inorganic materials 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 229910052906 cristobalite Inorganic materials 0.000 description 1
- 239000008367 deionised water Substances 0.000 description 1
- 229910021641 deionized water Inorganic materials 0.000 description 1
- 239000011928 denatured alcohol Substances 0.000 description 1
- QDOXWKRWXJOMAK-UHFFFAOYSA-N dichromium trioxide Chemical class O=[Cr]O[Cr]=O QDOXWKRWXJOMAK-UHFFFAOYSA-N 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000005247 gettering Methods 0.000 description 1
- FEEFWFYISQGDKK-UHFFFAOYSA-J hafnium(4+);tetrabromide Chemical compound Br[Hf](Br)(Br)Br FEEFWFYISQGDKK-UHFFFAOYSA-J 0.000 description 1
- QHEDSQMUHIMDOL-UHFFFAOYSA-J hafnium(4+);tetrafluoride Chemical compound F[Hf](F)(F)F QHEDSQMUHIMDOL-UHFFFAOYSA-J 0.000 description 1
- YCJQNNVSZNFWAH-UHFFFAOYSA-J hafnium(4+);tetraiodide Chemical compound I[Hf](I)(I)I YCJQNNVSZNFWAH-UHFFFAOYSA-J 0.000 description 1
- TZNXTUDMYCRCAP-UHFFFAOYSA-N hafnium(4+);tetranitrate Chemical class [Hf+4].[O-][N+]([O-])=O.[O-][N+]([O-])=O.[O-][N+]([O-])=O.[O-][N+]([O-])=O TZNXTUDMYCRCAP-UHFFFAOYSA-N 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229960004592 isopropanol Drugs 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 229910044991 metal oxide Inorganic materials 0.000 description 1
- 150000004706 metal oxides Chemical class 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000013110 organic ligand Substances 0.000 description 1
- RYSGCDWGRPPZSJ-UHFFFAOYSA-N oxalic acid;yttrium;hydrate Chemical compound O.[Y].[Y].OC(=O)C(O)=O.OC(=O)C(O)=O.OC(=O)C(O)=O RYSGCDWGRPPZSJ-UHFFFAOYSA-N 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000002243 precursor Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- FZHAPNGMFPVSLP-UHFFFAOYSA-N silanamine Chemical class [SiH3]N FZHAPNGMFPVSLP-UHFFFAOYSA-N 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 239000011863 silicon-based powder Substances 0.000 description 1
- 125000003808 silyl group Chemical group [H][Si]([H])([H])[*] 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 229910052682 stishovite Inorganic materials 0.000 description 1
- 230000001131 transforming effect Effects 0.000 description 1
- 125000005369 trialkoxysilyl group Chemical group 0.000 description 1
- 229910052905 tridymite Inorganic materials 0.000 description 1
- FOQJQXVUMYLJSU-UHFFFAOYSA-N triethoxy(1-triethoxysilylethyl)silane Chemical compound CCO[Si](OCC)(OCC)C(C)[Si](OCC)(OCC)OCC FOQJQXVUMYLJSU-UHFFFAOYSA-N 0.000 description 1
- IZRJPHXTEXTLHY-UHFFFAOYSA-N triethoxy(2-triethoxysilylethyl)silane Chemical compound CCO[Si](OCC)(OCC)CC[Si](OCC)(OCC)OCC IZRJPHXTEXTLHY-UHFFFAOYSA-N 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
- 229940105965 yttrium bromide Drugs 0.000 description 1
- 229940105963 yttrium fluoride Drugs 0.000 description 1
- 229940105970 yttrium iodide Drugs 0.000 description 1
- GRTBAGCGDOYUBE-UHFFFAOYSA-N yttrium(3+) Chemical compound [Y+3] GRTBAGCGDOYUBE-UHFFFAOYSA-N 0.000 description 1
- JRKVGRAQLBXGQB-UHFFFAOYSA-K yttrium(3+);triacetate;hydrate Chemical compound O.[Y+3].CC([O-])=O.CC([O-])=O.CC([O-])=O JRKVGRAQLBXGQB-UHFFFAOYSA-K 0.000 description 1
- LFWQXIMAKJCMJL-UHFFFAOYSA-K yttrium(3+);triiodide Chemical compound I[Y](I)I LFWQXIMAKJCMJL-UHFFFAOYSA-K 0.000 description 1
- QBAZWXKSCUESGU-UHFFFAOYSA-N yttrium(3+);trinitrate;hexahydrate Chemical compound O.O.O.O.O.O.[Y+3].[O-][N+]([O-])=O.[O-][N+]([O-])=O.[O-][N+]([O-])=O QBAZWXKSCUESGU-UHFFFAOYSA-N 0.000 description 1
- XRKAJAPEZSHSLG-UHFFFAOYSA-N yttrium(3+);trinitrate;tetrahydrate Chemical compound O.O.O.O.[Y+3].[O-][N+]([O-])=O.[O-][N+]([O-])=O.[O-][N+]([O-])=O XRKAJAPEZSHSLG-UHFFFAOYSA-N 0.000 description 1
- IYECSZYJKQPOOA-UHFFFAOYSA-K yttrium(3+);triperchlorate;hexahydrate Chemical compound O.O.O.O.O.O.[Y+3].[O-]Cl(=O)(=O)=O.[O-]Cl(=O)(=O)=O.[O-]Cl(=O)(=O)=O IYECSZYJKQPOOA-UHFFFAOYSA-K 0.000 description 1
- RBORBHYCVONNJH-UHFFFAOYSA-K yttrium(iii) fluoride Chemical compound F[Y](F)F RBORBHYCVONNJH-UHFFFAOYSA-K 0.000 description 1
Images
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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
- C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
- C23C18/125—Process of deposition of the inorganic material
- C23C18/1279—Process of deposition of the inorganic material performed under reactive atmosphere, e.g. oxidising or reducing atmospheres
-
- 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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
- C23C18/06—Coating on selected surface areas, e.g. using masks
-
- 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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
- C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
- C23C18/1204—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material inorganic material, e.g. non-oxide and non-metallic such as sulfides, nitrides based compounds
- C23C18/1208—Oxides, e.g. ceramics
- C23C18/1212—Zeolites, glasses
-
- 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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
- C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
- C23C18/1229—Composition of the substrate
- C23C18/1241—Metallic substrates
-
- 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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
- C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
- C23C18/125—Process of deposition of the inorganic material
- C23C18/1275—Process of deposition of the inorganic material performed under inert atmosphere
-
- 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
- C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C22/05—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions
- C23C22/06—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH less than 6
- C23C22/48—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH less than 6 not containing phosphates, hexavalent chromium compounds, fluorides or complex fluorides, molybdates, tungstates, vanadates or oxalates
-
- 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
- C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C22/73—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process
- C23C22/74—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process for obtaining burned-in conversion coatings
Definitions
- the present invention relates to coated metal components and, more particularly, turbine engine components with a non-aluminide protective coating containing silicon and chromium and methods of forming such protective coatings on turbine engine components.
- Intermetallic layers and coatings are often formed on a surface of a metal component to protect the underlying metal substrate of the component and to extend its useful life during operation.
- many superalloy components in gas turbine engines like turbine blades, vanes, shrouds, and nozzle guides, include an aluminide coating on airflow or gas washed surfaces that protect the underlying superalloy base metal from high temperature oxidation and corrosion.
- gas turbine engines are used as aircraft or jet engines (e.g., turbofans), as industrial gas turbine engines for power generation, as part of mechanical drive units for items such as
- gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel, such as, but not limited to, jet fuel, natural gas, diesel, biomass waste gases, naptha and gasified coal gases, the mixture is subsequently ignited.
- fuel such as, but not limited to, jet fuel, natural gas, diesel, biomass waste gases, naptha and gasified coal gases
- the engine also includes a turbine blade assembly for producing power.
- gas turbine engines operate by drawing air into the front of the engine. The air is then compressed, mixed with fuel, and combusted. Hot exhaust gases from the combusted mixture pass through a turbine, which causes the turbine to spin and thereby powers the compressor.
- Aircraft gas turbine engines referred to herein as jet engines, propel the attached aircraft forward in response to the thrust provided by the flow of the hot exhaust gases from the gas turbine engine. Rotation of the turbine in industrial gas turbine engines generates electrical power.
- Air flow surfaces of certain turbine engine components are directly contacted by the hot exhaust gases.
- the hot exhaust gases heat these components to high temperatures and expose them to impurity elements like sulfur originating from the combusted fuel.
- Superalloys in particular, are susceptible to severe oxidation and corrosion in such harsh enviromnents, particularly when the superalloy components of the gas turbine engine are heated by the hot exhaust gas stream created in a jet engine.
- Superalloy turbine engine components experience sulfidation when exposed at low temperatures to sulfur originating from the hot exhaust gases and other environmental sources. Generally, sulfidation increases the corrosion rate of superalloys and, in particular, the hot corrosion rate of nickel-based superalloys. Sulfidation is most often observed on portions of superalloy gas turbine components that are heated to temperatures below about 1500°F (815°C) during service. Often, superalloy gas turbine components are cooled by a stream of lower temperature air directed through a hollow interior region.
- Sulfidation may occur on portions of superalloy gas turbine components that are shielded from direct exposure to the exhaust gas stream, but nevertheless operate at temperatures less than about 1500°F (815°C) and are exposed to sulfur from the hot exhaust gases that bypass sealing surfaces.
- certain gas turbine blades include an airfoil segment that is heated to a temperature greater than 1500°F (815°C) when exposed to an exhaust gas stream, a root used to secure the gas turbine blade to a turbine disk of the gas turbine engine, and a platform that separates the airfoil segment from the root.
- the root which is not directly exposed to the exhaust gas stream, is heated by conduction from the airfoil segment and also cooled to less than 1500°F by heat transfer to the more massive turbine disk.
- the area of the gas turbine blade beneath the platform is particularly susceptible to sulfidation attack.
- Aluminide coatings have been disfavored on certain surfaces of turbine engine components. Most aluminide coatings embrittle the surface of the superalloy material used to manufacture turbine engine components, which may cause a loss of surface ductility because the aluminide coating is not ductile.
- Aluminide coatings may unwantedly alter the tight dimensional tolerances required on certain components. For example, areas below the platform, including the root of gas turbine blades, must maintain tight dimensional tolerances to properly couple the airfoil with the turbine disk. As a result, measures are routinely taken to avoid forming aluminide layers on machined pressure faces or root fixing surfaces below the platform when aluminiding the surfaces of the airfoil segment. Nevertheless, areas below the platform remain susceptible to corrosion enhanced by mechanisms like sulfidation.
- Platinum aluminides have been proposed as a solution for averting sulfidation attack of regions of the superalloy turbine engine, components below the platform,
- platinum aluminide coatings under certain operating conditions may be susceptible to cracking, which provides a path for the migration of sulfur and other corrosive elements to the unprotected superalloy surface.
- the platinum aluminide coating may spall and delaminate, which is not acceptable during operation of the gas turbine engine.
- EP1111192 discloses a turbine engine component for use with a gas turbine engine, comprising a substrate having a first section with an airflow surface and a second section used to secure the first section to the gas turbine engine and a protective coating on at least a portion of the second section.
- US 2002/0179191 A1 discloses a process for applying a silicon-containing fluid composition on the airflow surface of a jet engine metal component.
- the silicon-containing fluid composition e.g. silane, is cured and heated after deposition.
- the present invention provides a component and process as claimed in Claims 1 and 3.
- the present invention provides, in one aspect, a non-aluminide protective coating for a turbine engine component having a nickel-based superalloy substrate, in which a fluid composition layer containing silicon and other elements, such as chromium, is applied to the surface and heated to a temperature sufficient to form the protective coating which includes chromium that diffuses from the substrate.
- the fluid composition layer may be a liquid composition layer or a slurry composition.
- the protective coating may be effective for reducing the risk of corrosion and sulfidation of the underlying superalloy material.
- the turbine engine component may be a turbine blade, such as a jet engine or industrial gas turbine blade, having an airfoil segment and a root fixing integral with the airfoil segment for coupling the airfoil segment with the gas turbine engine.
- the turbine engine component may be a vane, a shroud, a nozzle guide, or any other part requiring protection from oxidation and corrosion when operating in a gas turbine engine.
- the turbine engine component may be hollow to permit air cooling or hollow for weight reduction.
- Protective coatings that are predominately ⁇ chromium are believed to not embrittle the superalloy material surface, as do most aluminide coatings.
- the protective coating is believed to be effective at preventing, or at the least reducing or delaying, corrosion and sulfidation of the underlying superalloy material and, preferably, does not significantly alter the component dimensions.
- Protective coatings that are predominately ⁇ chromium are believed to have a relatively low susceptibility to cracking, in contrast to conventional platinum aluminide coatings.
- Fig. 1 is a perspective view of a turbine engine component with a fluid composition being applied to a portion of the turbine engine component in accordance with the principles of the present invention
- Fig. 2 is a diagrammatic cross-sectional view of a portion of the turbine engine component of Fig. 1 that includes a silicon-containing layer formed by the application of the fluid composition;
- Fig. 3 is a diagrammatic cross-sectional view similar to Fig. 2 after the silicon-containing layer is converted to a protective coating.
- a silicon-containing layer 20 is applied to at least portion of an original surface 39 of a turbine engine component 10, such as a gas turbine blade.
- the silicon-containing layer 20 may be applied as a fluid composition (e.g., liquid composition, solution, or slurry) and then dried to form a pre-coating resident on the turbine engine component 10 before heating to a temperature sufficient to form a non-aluminide protective coating 14 ( Fig. 3 ).
- the turbine engine component 10 of the representative construction includes an airfoil segment 28 designed to be in the high-pressure, hot airflow path, as indicated by arrows 31.
- the airfoil segment 28 of turbine engine component 10 includes a pair of airflow surfaces 34, 35 extending between a trailing edge 36 and a curved leading edge 41 and which constitute portions of the surface 39.
- Cooling holes 37 intersect airflow surfaces 34, 35 so as to permit cooling air to pass through the interior of airfoil segment 28 while turbine engine component 10 is in service on the gas turbine engine.
- Integral with airfoil segment 28 is a dovetail, root, or root fixing 32 used to secure turbine engine component 10 to an air-cooled turbine disk (not shown) of a gas turbine engine (not shown) and a platform 33 separating the airfoil segment 28 from the root 32.
- Surface 39 extends across the root 32 below the platform 33.
- the root 32 further includes pressure faces 42 that face toward the airfoil segment 28 and that are used to mechanically engage the turbine engine component 10 with the turbine disk.
- a region 44 of surface 39 is directly beneath the platform 33 and has an intervening position between the pressure face 42 nearest to the platform 33 and the platform 33. Region 44, which may be referred to as a pocket as understood by a person having ordinary skill in the art, is also present on the opposite side of the root 32 that is not visible in Fig. 1 .
- combustion gases in the airflow path 31 may have a temperature as high as 3000°F (1650°C). Although this promotes heating of the airfoil segment 28, gas cooling of the airfoil segment 28 limits operating temperatures to 1800°F (980°C) or less.
- the temperature of the root 32 is elevated by heat transfer from airfoil segment 28 and other heat sources in the gas turbine engine but is not directly contacted by the combustion gases in airflow path 31.
- the root 32 may be cooled by a flow of cooling air supplied to the root 32 at a temperature of about 1100°F (590°C).
- the root 32 is significantly cooler than the airfoil segment 28 during operation and, frequently, is at a temperature of less than 1500°F (815°C) when the component 10 is in service, which makes the root 32 and, in particular, region 44 of surface 39 susceptible to sulfidation and corrosion.
- the silicon-containing layer 20 may be applied to surface 39 in region 44, such as by hand application with a paint brush B ( Fig. 1 ) as if being painted, by spraying, of by dipping with any excess poured off as the fluid composition is applied.
- the silicon-containing layer 20 may be optionally applied to other portions of surface 39 outside of region 44.
- the silicon-containing layer 20 is applied in a liquid form as a fluid or liquid composition and, thereafter, air dried with optional heating to form a solid or semi-solid coating.
- Other methods of applying the liquid composition are apparent to a person having ordinary skill in the art, such as dipping the root 32 of turbine engine component 10 into a bath (not shown) of the liquid composition to form silicon-containing layer 20 or spraying the liquid composition in a controlled manner onto only region 44.
- the turbine engine component 10 coated with the layer 20 which may advantageously first be dried and heated at a temperature insufficient to form a protective layer, may be placed into a heated environment and heated to a temperature at which protective coating 14 will be formed on at least region 44 to an engineered thickness.
- a particular fluid or liquid composition that may be selected for use in forming layer 20 is a silicon-containing substance or liquid such as a silane.
- Silanes suitable for use in the present invention may have mono-, bis-, or tri-functional trialkoxy silane.
- the silane may be a bifunctional trialkoxy silyl, preferably trimethoxy, or triethoxy silyl groups.
- Amino silanes may also be used, although thio silanes may not be desired due to their sulfur content.
- Bisfunctional silane compounds are well known to persons having ordinary skill in the art, and two preferred for use in the present invention are bis(triethoxysilyl) ethane and bis(trimethoxysilyl) methane.
- silanes include, but are not limitd to, 1, 2- Bis(tetramethyldisoloxanyl) Ethane 1, 9- Bis(triethoxysilyl) Nonane Bis(triethoxysilyl) Octane Bis(trimethoxysilyl Ethane 1, 3- Bis(trimethylsiloxy)-1, 3- Dimethyl Disiloxane Bis(trimethylsiloxy) Ethylsilane Bis(trimethylsiloxy) Methylsilane Al-501 available from AG Chemetall (Frankfurt Germany)
- the silane may be neat, in an aqueous solution, or diluted in an aqueous/alcohol solvent solution.
- a solvent for the latter type of diluted solution may contain from about 1% to 2% by volume to about 30% by volume deionized water with the remainder being a monohydric alcohol such as methanol, ethanol, n- or iso-propanol, or the like. Ethanol and methanol are preferred monohydric alcohols.
- the solvent is combined with the silane and glacial acetic acid to preferably establish a pH of about 4-6.
- the silane concentration in the solution may be limited to a maximum concentration for which the silane remains in solution during application. Generally, the solution will consist of about 1% to about 20% silane, wherein the percentage may be measured either by volume or by weight.
- a particularly useful silane for use in providing layer 20 may be an organofunctional silane such as BTSE 1,2 bis(triethoxysilyl) ethane or BTSM 1,2 bis(trimethoxysilyl) methane.
- the silane may be dissolved in a mixture of water and acetic acid at a pH of five (5), then in denatured alcohol and glacial acetic acid to establish a silane solution.
- the silane concentration in the solution is between about 1% and 10% by volume and, advantageously, about 5% by volume.
- This silane solution readily forms the silicon-containing layer 20, which may have a more or less hard consistency, at temperatures readily achieved and at a temperature insufficient to form the protective coating 14.
- the liquid composition is applied to all or a portion of surface 39 across region 44 to define the silicon-containing layer 20.
- the liquid composition applied to region 44 is allowed to dry, with optional heating, such as with a heat gun (not shown) or even in a conventional oven (not shown), to about 250°F (121°C) for about 15 to 25 minutes, to form the silicon-containing layer 20.
- the liquid composition may first be allowed to air dry, such as underneath a lamp (not shown) or with warm air, to release solvent.
- the liquid composition forming the silicon-containing layer 20 is applied in an amount of about 0.01 g/cm 2 to about 2.0 g/cm 2 .
- the silicon-containing layer 20 may refer to either the initially applied layer of liquid composition, or without limitation to the dried layer.
- the silicon-containing layer 20 may have a thickness in the range of about 40 nm to about 200 nm, although the invention is not so limited.
- Silicon-containing layer 20 which may be applied to all or a portion of region 44, is heated to a temperature and for a duration effective to transform layer 20 into protective coating 14 across the portion of region 44 to which layer 20 is applied.
- the conversion temperature is hotter than a curing temperature for layer 20 and cooler than aluminizing temperatures (i.e., about 1850°F (1010°C)).
- a heating temperature greater than about 400°F (205°C) may be sufficient to convert the silicon-containing layer 20 to protective coating 14.
- the temperature to which silicon-containing layer 20 is heated to cause the transformation to protective coating 14 will depend, among other things, upon the composition and characteristics of the liquid composition used to form layer 20 and the composition of the substrate alloy.
- the silicon-containing layer 20 may be heated in various different atmospheres and under various different conditions to form the protective coating 14.
- layer 20 may be heated in an ambient environment suitable to form the non-aluminide protective coating 14 that contains silicon from layer 20 and a concentration of one or more elements from the constituent superalloy material of the turbine engine component 10.
- the turbine engine component 10 and layer 20 may be heated to a temperature sufficient to cause diffusion of one or more elements from the component 10 into silicon-containing layer 20 for forming a protective layer 14 that contains these elements.
- the protective layer 14 may contain chromium and silicon, such as a chromium silicide or a silicon-modified chromium oxide, wherein the chromium originates from the superalloy material of the turbine engine component 10 or a separately deposited beta ( ⁇ ) chromium coating onto the surface of the turbine blade.
- the ambient environment may be oxygen-depleted, such as a non-oxidizing ambient gas environment created by evacuating a heating chamber and filling the evacuated chamber with an inert gas.
- the silicon-containing layer 20 may be heated in an oxygen-containing atmosphere to supply oxygen for creating a protective coating 14 containing oxygen, silicon, and optional elements from the material constituting the turbine engine component 10.
- the protective coating 20 may be a silicate, or may comprise a mixture of metal oxides formed from the superalloy matrix that is covered by a thin silicon-enriched outer layer.
- the transformation from the silicon-containing layer 20 to the protective coating 14 may be accomplished by placing the turbine engine component 10 into a heated enclosure, like an oven or furnace.
- the curing step to form the silicon-containing layer 20, and the subsequent step transforming the cured layer 20 into protective coating 14, may be conducted in the same heated enclosure or by placing the turbine engine component 10 into separate heated enclosures.
- the silicon-containing layer 20 will cure at a lower temperature than the temperature required to transform layer 20 into protective coating 14.
- the turbine engine component 10 with silicon-containing layer 20 may be placed into a heated deposition environment equipped to form, for example, an aluminide layer (not shown) on the airflow surfaces 34, 35 of airfoil segment 28.
- aluminide layer not shown
- the portion of the turbine engine component 10 below platform 33 to which the silicon-containing layer 20 is applied is substantially shielded or covered from the heated deposition environment such that aluminide is not formed thereupon.
- the elevated temperature of the turbine engine component 10 during the aluminiding process causes the shielded layer 20 on at least region 44 of surface 39 to transform into protective coating 14.
- the silicon-containing layer 20 may be applied to at least region 44 and protective coating 14 may be formed on region 44 of surface 39 from layer 20 after an aluminide layer (not shown) is formed in a heated deposition environment on the airflow surfaces 34, 35 of airfoil segment 28.
- the silicon-containing layer 20 may be advantageously applied to surfaces that are not shielded from the combustion gases in the airflow path 31.
- the silicon-containing layer 20 may be applied to the airflow surfaces 34, 35 of the airfoil segment 28 and/or a surface 38 of platform 33 facing the airfoil segment 28 and heated to extend the protective coating 14 to cover these surfaces 34, 35, 38, as well as region 44.
- the protective coating 14 is believed to operate to reduce oxidation and corrosion of the superalloy material, when the component 10 is in service in a gas turbine engine, by passivating or shielding the covered portion of region 44 of surface 39 and, optionally, surfaces 34, 35, 38, and/or the remainder of surface 39.
- the silicon-containing layer 20 may further include an additive that is incorporated as an optional dopant into protective coating 14.
- Suitable additives generally include any compound of the dopant that is dissolvable in the particular silane solution, although additives containing sulfur ligands and/or oxygen ligands may be disfavored. If the dopant is, for example, yttrium, suitable yttrium compounds include, but are not limited to, yttrium halides, such as yttrium chloride, yttrium bromide, yttrium iodide, and yttrium fluoride.
- yttrium compounds include, but are not limited to, yttrium acetate, yttrium acetate hydrate, yttrium 2-ethylhexanoate, yttrium perchlorate solution (e.g., 40 wt. % in water), yttrium nitrate hexahydrate, yttrium nitrate tetrahydrate, yttrium isopropoxide oxide, yttrium isopropoxide solution (e.g., 25 wt.
- suitable hafnium compounds include, but are not limited to, hafnium halides, such as hafnium chloride, hafnium bromide, hafnium iodide, and hafnium fluoride.
- hafnium compounds include, but are not limited to, any hafnium compound with an organic ligand, such as hafnium tert-butoxide, and hafnium nitrates. Permitted hafnium compounds generally exclude compounds with either sulfur ligands or oxide ligands. These, and other, yttrium and hafnium compounds are commercially available, for example, from Sigma-Aldrich (St. Louis, Missouri).
- one or more of the candidate dopant compounds is dissolved in or combined with the silane or silane solution. Before combining, the added amount of the dopant compound is measured for accurately regulating the concentration of dopant in the silicon-containing layer 20 and, subsequently, in the protective coating 14. Typically, a single additive or dopant compound will be combined with the silane to form a fluid composition, which is applied to all or a portion of at least region 44 of the turbine engine component 10.
- the present invention is generally applicable to turbine engine components 10 used in jet engine gas turbines and industrial gas turbines.
- the present invention is applicable for protecting turbine blades in such turbines.
- the protective coating 14 may be also applied to surfaces of a vane, a shroud, a nozzle guide, or any other part formed of a superalloy or another metal requiring protection from oxidation and corrosion while operating in a jet engine or while operating in an industrial gas turbine engine.
- the protected surfaces on these components may be exposed to the combustion gases in the airflow path 31 or shielded from the airflow path 31 during service in the aircraft or industrial gas turbine engine.
- the turbine engine component 10 includes a metallic substrate 12 and the protective coating 14 on the region 44 of the substrate 12.
- the metallic substrate 12 may be made of any nickel-, cobalt-, or iron-based high temperature superalloy from which such turbine engine components 10 are commonly made.
- the base element typically nickel or cobalt, is proportionally by weight the largest elemental constituent in the superalloy of substrate 12.
- substrate 12 may be the nickel-based superalloy Inconel 795 Mod5A or CMSX-4.
- the present invention is, however, not intended to be limited to any particular turbine engine component 10, which may be a turbine blade, a vane, a shroud, a nozzle guide, or any other part requiring protection from oxidation and corrosion while operating in a jet engine or while operating in an industrial gas turbine engine.
- the protective coating 14, which protects the underlying metal of the component 10 against oxidation and corrosion, is typically applied to portions of the turbine engine component 10 that are not heated above about 1500°F (815°C) when the component 10 is in service.
- the protective coating 14 may be an additive layer 15 or, more typically, may include a concentration of one or more elements from substrate 12 because of interdiffusion between the applied silicon-containing layer 20 and the superalloy material of the substrate 12.
- the protective coating 14 will be generally characterized by a diffusion zone 13 in addition to the additive layer 15 that overlies the diffusion zone 13.
- the interdiffusion advantageously introduces a concentration of one or more additional elements, such as chromium, from the substrate 12 into the protective coating 14 that ultimately endow the coating 14 with beneficial protective capabilities.
- the protective coating 14 may be an alloy containing silicon and chromium, such as chromium silicide, that is effective to prevent or significantly reduce sulfidation, oxidation, and corrosion on the protected region 44 ( Fig. 1 ).
- the chromium may originate from the superalloy material of the substrate 12 or from a pre-existing chromide or ⁇ chromium coating 16 on the region 44 that melts during heating to supply a source of chromium for the protective coating 14.
- the protective coating 14 may be a compound containing silicon and oxygen.
- the compound containing the silicon and oxygen may be a glass precursor of silicon, such as SiO 2 , a silicate, or a silicon-modified chrome oxide.
- the protective coating 14 may further include a dopant, such as yttrium and/or hafnium that, if present, is believed to operate as a getter or trap for the impurity or tramp element sulfur in the protective coating 14.
- a dopant such as yttrium and/or hafnium that, if present, is believed to operate as a getter or trap for the impurity or tramp element sulfur in the protective coating 14.
- the presence of the dopant is believed to reduce the transport of sulfur across the thickness of the protective coating 14 to the substrate 12 and thereby shield the superalloy material of the substrate 12 from sulfur.
- the protective coating 14 may, either alternatively or in addition to yttrium and/or hafnium, include other beneficial dopants that are believed to inhibit or prevent corrosion and, in particular, other beneficial dopants capable of inhibiting or preventing corrosion enhancement by the sulfidation mechanism.
- the protective coating 14 has a thickness extending from the surface of the turbine engine component 10 to an exposed working surface 18.
- the optional dopant may be present with a uniform concentration through the protective coating 14 or may be present with a concentration gradient between the working surface 18 and surface 39 in the region 44.
- the peak concentration of the gradient of the dopant may be at, or near, the working surface 18. If the protective coating 14 is eroded, the dopant is preferably distributed in protective coating 14 so that the protective coating 14 will continuously have a dopant concentration effective for gettering or trapping sulfur.
- the silicon-containing layer 20 may be applied, and the resulting protective coating 14 formed, directly as an additive layer on an existing coating, such as a platinum aluminide or a ⁇ chromium coating 16, on at least region 44 of surface 39 ( Fig. 1 ).
- an existing coating such as a platinum aluminide or a ⁇ chromium coating 16
- any existing coating may be stripped from region 44 and, optionally, from airflow surfaces 34, 35 of the airfoil segment 28 before the silicon-containing layer 20 is applied for forming the protective coating 14.
- the protective coating 14 may be formed on region 44 before the turbine engine component 10 has been placed into service and either before machining or after machining with airflow surfaces 34, 35 masked. It may be desirable to mask the portion of surface 39 extending across the pressure faces 42 so that protective coating 14 is formed only across region 44 below platform 33 or any thickness of coating 14 formed on the pressure faces 42 is negligible.
- the protective coating 14 may be also applied to surfaces of a vane, a shroud, a nozzle guide, or any other part requiring protection from oxidation and corrosion while operating in a gas turbine engine. These surfaces may be exposed to the combustion gases in the airflow path 31 or shielded from the airflow path 31 during use.
- the silicon-containing layer 20 may comprise a fluid or slurry composition that contains amounts of a silicon-containing material or substance, a chromium-containing material or substance, an inert diluent, a halide activator, and an optional inorganic binder.
- the chromium-containing substance, inert diluent, and activator of the slurry composition are preferably in a particulate or powder form.
- the silicon-containing substance may be a silane
- the chromium-containing substance may be chromium powder
- the inert diluent may be alumina (Al 2 O 3 ) particles
- the halide activator may be ammonium bifluoride (NH 4 HF 2 ).
- the inert diluent prevents sintering of the chromium-containing substance in the silicon-containing layer 20 when the layer 20 is heated to form protective coating 14.
- the turbine engine component 10 and silicon-containing layer 20 are heated in a non-oxidizing atmosphere or vacuum to a temperature that is maintained for a duration sufficient to form protective coating 14.
- the heating conditions may be, for example, a temperature of about 1975°F (1080°C) for four hours in an inert (e.g., argon) atmosphere.
- the slurry composition may be applied to at least region 44 of surface 39 to form silicon-containing layer 20 by methods such as brushing, spraying, and dipping.
- silane in the slurry composition may be replaced by a different silicon-containing substance, such as colloidal silicon or elemental silicon powder.
- the slurry composition may contain a dopant compound, such as yttrium acetate or hafnium chloride, as described herein.
- the amount of slurry composition applied is controlled because the thickness of the resulting protective coating 14 is proportional to the amount of slurry composition applied in layer 20 to at least region 44 of surface 39.
- the slurry composition is applied as layer 20 to region 44 with a substantially uniform thickness.
- the slurry composition may comprise, by weight percent, about 1% to about 20% of the powdered chromium-containing substance, greater than 2% of the activator powder, about 60% to about 90% of the inert filler powder, and balance binder and neat silane.
- the specific slurry composition may be tailored to provide a desired composition for the protective coating 14, as well as other processing variables such as time and temperature, and the coating thickness and composition desired for protective coating 14.
- the chromium in protective coating 14 does not originate from the substrate 12 of the component 10, the superalloy material of substrate 12 does not have to operate as a chromium source and the chromium-containing protective coating 14 may be formed regardless of the chromium content of the substrate 12. However, minor amounts of substrate elements may diffuse into the protective coating 14.
- the binder may comprise any suitable conventional binder known to a person having ordinary skill in the art. Suitable binders include NICOBRAZ ® cements commercially available from Wall Colmonoy Corporation (Madison Heights, MI). Alternatively, the binder may be omitted from the slurry composition forming layer 20 if another substance in the layer 20, such as the silane, can operate as a binder for adhering the slurry composition to the surface 39 of component 10.
- the slurry composition is directly applied to all or a portion of region 44 of surface 39 of the root 32 of turbine engine component 10 to form silicon-containing layer 20.
- the silicon-containing layer 20 is heated in an inert or evacuated atmosphere (i.e., non-oxidizing) to a temperature sufficient to vaporize the activator in the layer 20.
- the vaporized activator reacts with the chromium-containing substance in the layer 20 to promote chemical reactions that liberate chromium from the substance to participate in forming protective coating 14.
- the heating conditions may be, for example, a temperature in the range of 1875°F (1025°C) to 1900°F (1040°C) for four hours in an inert atmosphere.
- unreacted slurry residues may be removed by, for example, brushing or blasting with glass beads such as BALLOTINI® impact glass beads commercially available from Potters Brothers, Inc. (Carlstadt, New Jersey).
- the invention further contemplates that the fluid compositions described herein may be introduced into cooling holes 37 or other internal passages of the turbine engine component 10 for purposes of forming a protective coating 14 on the internal surfaces bordering the cooling holes 37.
- the silicon-containing fluid composition is introduced into the cooling holes 37 to form silicon-containing layer 20 and heated to form the protective coating 14 on these internal surfaces.
- the silicon-containing layer 20 may be applied in stages to form the protective coating 14.
- the silane may be omitted from the slurry composition initially applied as a first portion of layer 20 to all or a portion of region 44 of surface 39.
- Heating layer 20 results in the formation of a chromium-rich layer (e.g. ⁇ chromium layer) on region 44 to which the first portion of layer 20 is applied.
- the turbine engine component 10 is grit blasted using, for example, impact glass beads or aluminum oxide 220 grit.
- Silane is then applied, as described above, on region 44 with the chromium-rich layer as a second portion of the layer 20.
- Protective coating 14 is formed by heating, for example, at 250°C for 30 minutes to react the silane with the chromium-rich layer to form the protective coating 14. Silicon from the silicon-containing layer 20 diffuses into the ⁇ chromium layer. Chromium from the ⁇ chromium coating also diffuses into the non-aluminide protective coating 14.
- any of the different liquid or slurry compositions forming silicon-containing layers 20 may be used in combination with chromium that originates from the superalloy material of the substrate 12 or from a pre-existing P chromium coating 16 on the region 44.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- General Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Thermal Sciences (AREA)
- Physics & Mathematics (AREA)
- Inorganic Chemistry (AREA)
- Ceramic Engineering (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
- Chemically Coating (AREA)
Abstract
Claims (17)
- Composant de moteur à turbine (10) destiné à être utilisé avec une turbine à gaz, comprenant :un substrat en superalliage à base de nickel (12) comportant une première section (28) à surface aérodynamique (34) et une seconde section (32) utilisée pour fixer la première section (28) à la turbine à gaz ; etun revêtement protecteur sans aluminure (14) sur au moins une partie de la seconde section (32), le revêtement protecteur sans aluminure (14) comportant du chrome qui se diffuse depuis le substrat en superalliage à base de nickel (12) et du silicium de telle sorte que le revêtement protecteur sans aluminure (14) contienne un siliciure de chrome, un oxyde de chrome modifié au silicium, ou un silicate contenant du chrome.
- Composant de moteur à turbine (10) selon la revendication 1, dans lequel le revêtement protecteur (14) comporte en outre un dopant sélectionné dans le groupe consistant en yttrium, hafnium, et des combinaisons de ceux-ci.
- Processus de revêtement pour protéger un composant de moteur à turbine (10) comportant une première section (28) à surface aérodynamique (34) et une seconde section (32) utilisée pour fixer la première section (28) à la turbine à gaz ; le processus de revêtement comprenant :l'application d'une couche (20) d'une composition fluide contenant du silicium comprenant un liquide de silane sur au moins une partie de la seconde section (32) du composant de moteur à turbine (10) ;le durcissement de la composition fluide contenant du silicium après l'application de la couche (20) sur la seconde section (32) du composant de moteur à turbine (10) ; etle chauffage de la composition fluide contenant du silicium à une température efficace pour former un revêtement protecteur sans aluminure (14) sur la seconde section (32) du composant de moteur à turbine (10) qui comporte du silicium provenant de la composition fluide contenant du silicium durcie et qui comporte en outre du chrome diffusé depuis le composant de moteur à turbine (10).
- Processus de revêtement selon la revendication 3, dans lequel le composant de moteur à turbine (10) comprend un matériau de superalliage à base de nickel.
- Processus de revêtement selon la revendication 3 ou 4, comprenant en outre l'application d'une substance contenant du chrome sur au moins une partie de la seconde section (32) du composant de moteur à turbine (10).
- Processus de revêtement selon la revendication 5, dans lequel l'application de la substance contenant du chrome comprend en outre l'application de la substance contenant du chrome sur au moins la partie de la seconde section (32) comme constituant de la composition fluide contenant du silicium dans la couche (20).
- Processus de revêtement selon la revendication 6, dans lequel l'application de la substance contenant du chrome comprend en outre l'application d'un activateur d'halogénure, d'une poudre diluante inerte, et d'un liant inorganique optionnel sur au moins la partie de la seconde section (32) comme constituants de la composition fluide contenant du silicium dans la couche (20).
- Processus de revêtement selon la revendication 6 ou 7, dans lequel le chauffage de la composition fluide contenant du silicium durcie comprend en outre le chauffage de la composition fluide contenant du silicium jusqu'à une température et pendant une durée suffisantes pour combiner la substance contenant du chrome au silicium provenant de la composition fluide contenant du silicium durcie de telle sorte que la substance contenant du chrome et le silicium participent à la formation du revêtement protecteur sans aluminure (14).
- Processus de revêtement selon l'une quelconque des revendications 5 à 8, dans lequel la substance contenant du chrome comprend un revêtement de chrome β, et l'application de la substance contenant du chrome comprend en outre l'application du revêtement de chrome β sur au moins la partie du composant de moteur à turbine (10) avant l'application de la couche (20).
- Processus de revêtement selon la revendication 9, dans lequel le chauffage de la composition fluide contenant du silicium durcie comprend en outre le chauffage de la composition fluide contenant du silicium durcie et du revêtement de chrome β jusqu'à une température et pendant une durée suffisantes pour faire fondre le revêtement de chrome β et combiner le silicium provenant de la composition fluide contenant du silicium durcie au revêtement de chrome β fondu pour participer à la formation du revêtement protecteur sans aluminure (14).
- Processus de revêtement selon la revendication 3, dans lequel la partie de composant de moteur à turbine (10) est recouverte par un revêtement existant, et l'application de la couche (20) de la composition fluide contenant du silicium comprend en outre l'application de la composition fluide contenant du silicium comme couche additive (20) sur le revêtement existant de telle sorte que le revêtement protecteur sans aluminure (14) soit formé sur le revêtement existant.
- Processus de revêtement selon l'une quelconque des revendications précédentes, dans lequel la seconde section (32) du composant de moteur à turbine (10) comporte un passage interne, et l'application de la couche (20) de la composition fluide contenant du silicium comprend en outre l'introduction de la composition fluide contenant du silicium dans le passage interne.
- Processus de revêtement selon l'une quelconque des revendications précédentes, comprenant en outre le placement de la composition fluide contenant du silicium dans une atmosphère oxydante avant de chauffer la composition fluide contenant du silicium durcie.
- Processus de revêtement selon l'une quelconque des revendications 3 à 13, comprenant en outre le placement de la composition fluide contenant du silicium dans une atmosphère non oxydante avant de chauffer la composition fluide contenant du silicium durcie.
- Processus de revêtement selon l'une quelconque des revendications 3 à 14, dans lequel le chauffage de la composition fluide contenant du silicium durcie comprend en outre l'élévation de la température de la composition fluide contenant du silicium durcie au-delà d'une température de durcissement.
- Processus de revêtement selon l'une quelconque des revendications 3 à 14, dans lequel le chauffage de la composition fluide contenant du silicium durcie comprend en outre l'élévation de la température de la composition fluide contenant du silicium durcie au-delà d'environ 205°C (400°F).
- Processus de revêtement selon l'une quelconque des revendications 3 à 16, comprenant en outre l'ajout d'un dopant sélectionné dans le groupe consistant en yttrium, hafnium et des combinaisons de ceux-ci au liquide de silane.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL05858676T PL1831428T3 (pl) | 2004-12-13 | 2005-12-12 | Elementy silnika turbinowego z nie-aluminidowymi powłokami ochronnymi zawierającymi krzem oraz chrom i sposoby wytwarzania takich nie-aluminidowych powłok ochronnych |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2004/041896 WO2006036171A1 (fr) | 2004-09-16 | 2004-12-13 | Composants de reacteur en superalliage a revetements de protection et procede de formation de ces revetements de protection sur des composants de reacteur en superalliage |
PCT/US2005/044843 WO2007067185A2 (fr) | 2004-12-13 | 2005-12-12 | Composants de moteur a turbine avec revetements protecteurs contenant du silicium et du chrome sans aluminure et procedes de fabrication de tels revetements protecteurs sans aluminure |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1831428A2 EP1831428A2 (fr) | 2007-09-12 |
EP1831428B1 true EP1831428B1 (fr) | 2011-06-22 |
Family
ID=36405882
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05858676A Active EP1831428B1 (fr) | 2004-12-13 | 2005-12-12 | Composants de moteur a turbine avec revetements protecteurs contenant du silicium et du chrome sans aluminure et procedes de fabrication de tels revetements protecteurs sans aluminure |
EP16171410.0A Active EP3095895B1 (fr) | 2004-12-13 | 2005-12-12 | Procédé de formation des revêtements protecteurs au silicium sur composants métalliques |
EP05853894.3A Active EP1834009B1 (fr) | 2004-12-13 | 2005-12-12 | Composants metalliques avec revetements protecteurs au silicium et procedes de formation de ces revetements protecteurs |
Family Applications After (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16171410.0A Active EP3095895B1 (fr) | 2004-12-13 | 2005-12-12 | Procédé de formation des revêtements protecteurs au silicium sur composants métalliques |
EP05853894.3A Active EP1834009B1 (fr) | 2004-12-13 | 2005-12-12 | Composants metalliques avec revetements protecteurs au silicium et procedes de formation de ces revetements protecteurs |
Country Status (4)
Country | Link |
---|---|
EP (3) | EP1831428B1 (fr) |
ES (1) | ES2368436T3 (fr) |
PL (2) | PL3095895T3 (fr) |
WO (2) | WO2006065819A2 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2103713A1 (fr) * | 2008-03-20 | 2009-09-23 | Münch Chemie International GmbH | Couche de protection contre la corrosion |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB893397A (en) * | 1959-07-29 | 1962-04-11 | Dow Corning | Improvements in or relating to coating metals |
CA1004964A (en) * | 1972-05-30 | 1977-02-08 | Union Carbide Corporation | Corrosion resistant coatings and process for making the same |
CH597364A5 (fr) * | 1974-04-11 | 1978-03-31 | Bbc Sulzer Turbomaschinen | |
GB1529441A (en) * | 1976-01-05 | 1978-10-18 | Bp Chem Int Ltd | Protective surface films of oxide or silicide |
JPS5754282A (ja) * | 1980-09-17 | 1982-03-31 | Mitsubishi Heavy Ind Ltd | Tainetsugokinnohyomenshorihoho |
US4500364A (en) * | 1982-04-23 | 1985-02-19 | Exxon Research & Engineering Co. | Method of forming a protective aluminum-silicon coating composition for metal substrates |
US4774149A (en) * | 1987-03-17 | 1988-09-27 | General Electric Company | Oxidation-and hot corrosion-resistant nickel-base alloy coatings and claddings for industrial and marine gas turbine hot section components and resulting composite articles |
EP0327311B1 (fr) * | 1988-02-02 | 1994-09-14 | Hitachi Chemical Co., Ltd. | Fluide de revêtement pour la formation d'une couche d'oxyde |
US6503347B1 (en) * | 1996-04-30 | 2003-01-07 | Surface Engineered Products Corporation | Surface alloyed high temperature alloys |
US5721061A (en) * | 1996-11-15 | 1998-02-24 | General Electric Company | Oxidation-resistant coating for niobium-base alloys |
US5750197A (en) * | 1997-01-09 | 1998-05-12 | The University Of Cincinnati | Method of preventing corrosion of metals using silanes |
GB9821748D0 (en) * | 1998-10-07 | 1998-12-02 | Rolls Royce Plc | A titanium article having a protective coating and a method of applying a protective coating to a titanium article |
ATE303503T1 (de) | 1999-12-20 | 2005-09-15 | United Technologies Corp | Gegenstände mit korrosionsbeständigen beschichtungen |
WO2002024344A2 (fr) * | 2000-09-25 | 2002-03-28 | Chemetall Gmbh | Procede de pretraitement et d'enduction de surfaces metalliques, avant leur façonnage, au moyen d'un revetement ressemblant a de la peinture, et utilisation de substrats ainsi enduits |
US6521356B2 (en) * | 2001-02-02 | 2003-02-18 | General Electric Company | Oxidation resistant coatings for niobium-based silicide composites |
US6605161B2 (en) * | 2001-06-05 | 2003-08-12 | Aeromet Technologies, Inc. | Inoculants for intermetallic layer |
WO2003035942A2 (fr) * | 2001-08-03 | 2003-05-01 | Elisha Holding Llc | Procede electrolytique et autocatalytique de traitement de surfaces metalliques et produits traites selon ce procede |
US20060057418A1 (en) * | 2004-09-16 | 2006-03-16 | Aeromet Technologies, Inc. | Alluminide coatings containing silicon and yttrium for superalloys and method of forming such coatings |
-
2005
- 2005-12-12 ES ES05858676T patent/ES2368436T3/es active Active
- 2005-12-12 WO PCT/US2005/045078 patent/WO2006065819A2/fr active Application Filing
- 2005-12-12 WO PCT/US2005/044843 patent/WO2007067185A2/fr active Application Filing
- 2005-12-12 PL PL16171410T patent/PL3095895T3/pl unknown
- 2005-12-12 EP EP05858676A patent/EP1831428B1/fr active Active
- 2005-12-12 PL PL05858676T patent/PL1831428T3/pl unknown
- 2005-12-12 EP EP16171410.0A patent/EP3095895B1/fr active Active
- 2005-12-12 EP EP05853894.3A patent/EP1834009B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
EP3095895B1 (fr) | 2019-05-01 |
PL3095895T3 (pl) | 2019-10-31 |
WO2007067185A3 (fr) | 2007-08-02 |
ES2368436T3 (es) | 2011-11-17 |
EP1834009A2 (fr) | 2007-09-19 |
EP1831428A2 (fr) | 2007-09-12 |
PL1831428T3 (pl) | 2012-03-30 |
WO2006065819A2 (fr) | 2006-06-22 |
EP1834009B1 (fr) | 2016-07-20 |
EP3095895A1 (fr) | 2016-11-23 |
WO2006065819A3 (fr) | 2006-11-30 |
WO2007067185A2 (fr) | 2007-06-14 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US9133718B2 (en) | Turbine engine components with non-aluminide silicon-containing and chromium-containing protective coatings and methods of forming such non-aluminide protective coatings | |
US7901739B2 (en) | Gas turbine engine components with aluminide coatings and method of forming such aluminide coatings on gas turbine engine components | |
US6616969B2 (en) | Apparatus and method for selectively coating internal and external surfaces of an airfoil | |
EP1989399B1 (fr) | Revêtement rugosifié pour composants de moteur de turbine à gaz | |
JP5698896B2 (ja) | スラリー状拡散アルミナイド被覆方法 | |
US6273678B1 (en) | Modified diffusion aluminide coating for internal surfaces of gas turbine components | |
EP1199377B1 (fr) | Protection de la surface d'un article à base de nickel par une couche en alliage d'aluminium résistante à la corrosion | |
US7056555B2 (en) | Method for coating an internal surface of an article with an aluminum-containing coating | |
EP3055445B1 (fr) | Revêtement en alliage d'aluminium dotés d'inhibiteurs de corrosion de type terres rares et métaux de transition | |
US7163718B2 (en) | Method of selective region vapor phase aluminizing | |
US8039116B2 (en) | Nb-Si based alloys having an Al-containing coating, articles, and processes | |
US20100136240A1 (en) | Process for Forming an Outward Grown Aluminide Coating | |
EP1831428B1 (fr) | Composants de moteur a turbine avec revetements protecteurs contenant du silicium et du chrome sans aluminure et procedes de fabrication de tels revetements protecteurs sans aluminure | |
JP4907072B2 (ja) | 選択的領域気相アルミナイズ方法 | |
EP3293281A1 (fr) | Procédé de formation d'un revêtement de diffusion sur un substrat | |
US6896488B2 (en) | Bond coat process for thermal barrier coating | |
EP1802784B1 (fr) | Composants de moteur de turbine a gaz a revetements en aluminiure et procede de realisation de ces revetements sur les composants en question | |
US6893737B2 (en) | Low cost aluminide process for moderate temperature applications | |
CA2483232C (fr) | Methode d'aluminiage selectif en phase vapeur d'une region |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20070620 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
17Q | First examination report despatched |
Effective date: 20071019 |
|
DAX | Request for extension of the european patent (deleted) | ||
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SIEMENS INDUSTRIAL TURBOMACHINERY GMBH Owner name: MT COATINGS, LLC |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602005028693 Country of ref document: DE Effective date: 20110811 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PUEA Owner name: SIEMENS AKTIENGESELLSCHAFT Free format text: SIEMENS INDUSTRIAL TURBOMACHINERY GMBH#WOLFGANG-REUTER-PLATZ#47053 DUISBURG (DE) $ MT COATINGS, LLC#3064 COLERAIN AVENUE#CINCINNATI, OH 45225 (US) -TRANSFER TO- SIEMENS AKTIENGESELLSCHAFT#WITTELSBACHERPLATZ 2#80333 MUENCHEN (DE) $ MT COATINGS, LLC#3064 COLERAIN AVENUE#CINCINNATI, OH 45225 (US) Ref country code: CH Ref legal event code: NV Representative=s name: BOVARD AG |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: VDEP Effective date: 20110622 |
|
RAP2 | Party data changed (patent owner data changed or rights of a patent transferred) |
Owner name: SIEMENS AKTIENGESELLSCHAFT Owner name: MT COATINGS, LLC |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2368436 Country of ref document: ES Kind code of ref document: T3 Effective date: 20111117 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110923 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R082 Ref document number: 602005028693 Country of ref document: DE Representative=s name: MEISSNER & MEISSNER, DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: BE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 |
|
REG | Reference to a national code |
Ref country code: HU Ref legal event code: AG4A Ref document number: E012091 Country of ref document: HU |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20111024 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20111022 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: MT COATINGS, LLC, CINCINNATI, US Free format text: FORMER OWNER: AEROMET TECHNOLOGIES, INC., SIEMENS INDUSTRIAL TURBOMACHINE, , US Effective date: 20110622 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: SIEMENS AKTIENGESELLSCHAFT, DE Free format text: FORMER OWNER: AEROMET TECHNOLOGIES, INC., SIEMENS INDUSTRIAL TURBOMACHINE, , US Effective date: 20110622 Ref country code: DE Ref legal event code: R082 Ref document number: 602005028693 Country of ref document: DE Representative=s name: MEISSNER & MEISSNER, DE Effective date: 20111209 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: MT COATINGS, LLC, CINCINNATI, US Free format text: FORMER OWNER: MT COATINGS, LLC, SIEMENS INDUSTRIAL TURBOMACHINE, , US Effective date: 20111209 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: SIEMENS AKTIENGESELLSCHAFT, DE Free format text: FORMER OWNER: MT COATINGS, LLC, SIEMENS INDUSTRIAL TURBOMACHINE, , US Effective date: 20111209 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: SIEMENS AKTIENGESELLSCHAFT, DE Free format text: FORMER OWNERS: MT COATINGS, LLC, CINCINNATI, OHIO, US; SIEMENS INDUSTRIAL TURBOMACHINERY GMBH, 47053 DUISBURG, DE Effective date: 20111209 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: MT COATINGS, LLC, CINCINNATI, US Free format text: FORMER OWNERS: MT COATINGS, LLC, CINCINNATI, OHIO, US; SIEMENS INDUSTRIAL TURBOMACHINERY GMBH, 47053 DUISBURG, DE Effective date: 20111209 Ref country code: DE Ref legal event code: R082 Ref document number: 602005028693 Country of ref document: DE Representative=s name: ANWALTSKANZLEI MEISSNER & MEISSNER, DE Effective date: 20111209 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: SIEMENS AKTIENGESELLSCHAFT, DE Free format text: FORMER OWNERS: AEROMET TECHNOLOGIES, INC., SANDY, UTAH, US; SIEMENS INDUSTRIAL TURBOMACHINERY GMBH, 47053 DUISBURG, DE Effective date: 20110622 Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: MT COATINGS, LLC, CINCINNATI, US Free format text: FORMER OWNERS: AEROMET TECHNOLOGIES, INC., SANDY, UTAH, US; SIEMENS INDUSTRIAL TURBOMACHINERY GMBH, 47053 DUISBURG, DE Effective date: 20110622 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 |
|
REG | Reference to a national code |
Ref country code: PL Ref legal event code: T3 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20120323 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602005028693 Country of ref document: DE Effective date: 20120323 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111231 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20120830 AND 20120905 Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111212 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111212 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110922 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110622 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 11 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 12 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20151212 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20151212 |
|
PGRI | Patent reinstated in contracting state [announced from national office to epo] |
Ref country code: IT Effective date: 20170710 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PCOW Free format text: NEW ADDRESS: 3064 COLERAIN AVENUE, CINCINNATI, OH 45225 (US) $ SIEMENS AKTIENGESELLSCHAFT, WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE) |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 13 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: HU Payment date: 20171127 Year of fee payment: 13 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: PL Payment date: 20171121 Year of fee payment: 13 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: SIEMENS SCHWEIZ AG, CH Ref country code: CH Ref legal event code: PUEA Owner name: SIEMENS AKTIENGESELLSCHAFT, DE Free format text: FORMER OWNER: MT COATINGS, LLC, DE |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20180102 Year of fee payment: 13 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20181213 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20200203 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20181213 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20181212 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20220908 AND 20220914 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE Free format text: FORMER OWNERS: MT COATINGS, LLC, CINCINNATI, OHIO, US; SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE Ref country code: DE Ref legal event code: R081 Ref document number: 602005028693 Country of ref document: DE Owner name: MT COATINGS, LLC, CINCINNATI, US Free format text: FORMER OWNERS: MT COATINGS, LLC, CINCINNATI, OHIO, US; SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE Ref country code: DE Ref legal event code: R082 Ref document number: 602005028693 Country of ref document: DE Representative=s name: ROTH, THOMAS, DIPL.-PHYS. DR., DE |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20231219 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20231221 Year of fee payment: 19 Ref country code: FR Payment date: 20231226 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20231227 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20240102 Year of fee payment: 19 |