WO1989007159A1 - Metallic object, in particular gas turbine blade with protective coating - Google Patents
Metallic object, in particular gas turbine blade with protective coating Download PDFInfo
- Publication number
- WO1989007159A1 WO1989007159A1 PCT/DE1989/000023 DE8900023W WO8907159A1 WO 1989007159 A1 WO1989007159 A1 WO 1989007159A1 DE 8900023 W DE8900023 W DE 8900023W WO 8907159 A1 WO8907159 A1 WO 8907159A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- layer
- coating layer
- metal object
- object according
- chromium
- Prior art date
Links
- 239000011253 protective coating Substances 0.000 title abstract description 3
- 239000010410 layer Substances 0.000 claims abstract description 60
- 239000011247 coating layer Substances 0.000 claims abstract description 36
- 230000007797 corrosion Effects 0.000 claims abstract description 21
- 238000005260 corrosion Methods 0.000 claims abstract description 21
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 18
- 238000009792 diffusion process Methods 0.000 claims abstract description 16
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 13
- 239000011651 chromium Substances 0.000 claims abstract description 13
- 230000004888 barrier function Effects 0.000 claims abstract description 11
- 229910052742 iron Inorganic materials 0.000 claims abstract description 9
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 8
- 238000007750 plasma spraying Methods 0.000 claims abstract description 8
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 7
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052751 metal Inorganic materials 0.000 claims description 23
- 239000002184 metal Substances 0.000 claims description 23
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 16
- 239000000203 mixture Substances 0.000 claims description 11
- 229910052759 nickel Inorganic materials 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 6
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 5
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 5
- 229910017052 cobalt Inorganic materials 0.000 claims description 5
- 239000010941 cobalt Substances 0.000 claims description 5
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 5
- 229910052735 hafnium Inorganic materials 0.000 claims description 5
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 229910052758 niobium Inorganic materials 0.000 claims description 5
- 239000010955 niobium Substances 0.000 claims description 5
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 5
- 229910052706 scandium Inorganic materials 0.000 claims description 5
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 5
- 239000010703 silicon Substances 0.000 claims description 5
- 229910052715 tantalum Inorganic materials 0.000 claims description 5
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 5
- 229910052726 zirconium Inorganic materials 0.000 claims description 5
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims description 3
- NRTOMJZYCJJWKI-UHFFFAOYSA-N Titanium nitride Chemical compound [Ti]#N NRTOMJZYCJJWKI-UHFFFAOYSA-N 0.000 claims description 2
- 229910052702 rhenium Inorganic materials 0.000 claims description 2
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 claims description 2
- 239000000919 ceramic Substances 0.000 claims 1
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 claims 1
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 claims 1
- 229910052761 rare earth metal Inorganic materials 0.000 claims 1
- 229910001928 zirconium oxide Inorganic materials 0.000 claims 1
- 239000011241 protective layer Substances 0.000 abstract description 7
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 abstract 1
- 239000004411 aluminium Substances 0.000 abstract 1
- 229910052748 manganese Inorganic materials 0.000 abstract 1
- 239000011572 manganese Substances 0.000 abstract 1
- 238000000576 coating method Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 9
- 230000007246 mechanism Effects 0.000 description 7
- 239000011248 coating agent Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 229910001385 heavy metal Inorganic materials 0.000 description 3
- 150000003841 chloride salts Chemical class 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000003915 air pollution Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003034 coal gas Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- -1 for example Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000008263 liquid aerosol Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 239000008275 solid aerosol Substances 0.000 description 1
- 229910052717 sulfur Inorganic materials 0.000 description 1
- 239000011593 sulfur Substances 0.000 description 1
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
- C23C28/023—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material only coatings of metal elements only
Definitions
- Metal object in particular gas turbine blade with protective coating
- the present invention relates to a metal object, in particular a component of a gas turbine plant, for. B.
- a blade according to the preamble of claim 1.
- Many components which are exposed to hot gas, in particular in gas turbines, are subject to thermal, mechanical and erosive stresses and are also to a large extent corrosive influences. Coverings that form from salts, the origin of which can be attributed to fuel and air pollution, together with some gaseous substances lead to corrosive damage by high-temperature corrosion (HTK).
- HTK high-temperature corrosion
- the corrosion exciters can be very heterogeneous.
- the type and origin of the fuels and, on the other hand, the composition of the combustion air determine the different forms of attack that come about through different chemical mechanisms.
- the combustion air may contain heavy metals, alkalis and / or chlorides.
- coating layers including multiple coatings for components exposed to hot gas, are known from the literature in large numbers for different purposes.
- DE-C-28 26 910 it is known from DE-C-28 26 910 to provide metal objects with a graduated coating.
- the innermost layer is a diffusion layer mainly containing chromium.
- the graded coating described is generally intended to protect the metal object against heat corrosion, in which case corrosion tests at temperatures of about 925 ° C. are described.
- DE-C-28 26 909 discloses a further double layer for metal objects subjected to such loads, an inner partial layer containing portions of the elements aluminum, chromium and yttrium.
- US Pat. No. 3,649,225 also describes double layers which are intended to prevent high-temperature corrosion.
- the lower, generally thin layer does not itself serve as protection against external attack, but only improves the durability and adhesion of the upper layer.
- the known layer systems protect a component against oxidation and corrosion at very high temperatures, but intensive studies have shown that the known layers do not simultaneously protect against a different type of corrosion attack at temperatures between 600 "and 800" C. As can be seen from FIG. 1 of the drawing, there are 2 different types of attack for high-temperature corrosion after investigations which have become known.
- Fig. 1 shows that in addition to the high-temperature corrosion already mentioned in the range of approximately 850 ° C. (hereinafter referred to as HTKI), whereas the known protective layers are designed, there is another strong corrosion mechanism which has a maximum in the range of approximately 700 * C.
- Fig. 1 shows a diagram in which the rate of corrosion versus temperature is plotted.
- the object of the present invention is therefore to create a combination of protective layers which makes a metal object resistant to both known attack techniques e ⁇ , HTKI and HTKII and thus increases the service life of the component.
- a metal object with the coatings according to the characterizing features of claim 1 is proposed. Then the component is first provided with a layer which, owing to its thickness or composition, has great resistance to attack mechanisms at temperatures of 600 ° to 800 ° C. Furthermore, a second coating layer is applied, which is particularly resistant to attacks at 800 "to 900" C.
- This structure is based on the knowledge that components which are exposed to hot gas are generally cooled internally, so that there is a temperature gradient from the outermost layer to the interior of the component inner layer against the attack mechanism designed at lower temperatures, while the outer layer should protect against corrosion at high temperatures.
- a component does not in principle have to be completely provided with both layers, provided that the temperature load of individual areas is different.
- the invention should therefore of course also include the double coating only in partial areas of the metal objects.
- the proposed arrangement of the layers has the advantage that the service life of a component is increased in any case, even if the average prevailing attack mechanism is different at different locations on the component and is not necessarily known. If, for example, a special one well-cooled part of the component is mainly in the temperature range around 700 ° C even during full load operation, so the outermost protective layer, which is not optimized for this type of attack, is gradually destroyed, but subsequently protects the layer underneath.
- FIG. 2 shows an example of the effects of the double layer on the operating time in a diagram.
- the consumption is plotted against the operating time and typical consumption curves for different temperature stresses of different parts of a component are shown.
- FIG. 3 shows the effect of a thermal barrier layer over a corrosion protection layer in an internally cooled component.
- the diagram shows two typical temperature profiles inside and outside the component and the protective layers.
- a diffusion layer applied to the metal object with a chromium content greater than 50% is suitable as the first coating layer.
- Such diffusion layers are known per se according to the prior art, in particular from DE-C-28 26 910. However, their beneficial effect compared to HTKII when combined with a second coating layer against HTKI was not recognized.
- An additional amount of iron or manganese, e.g. B. 10 to 30% (all the following data are percentages by weight) the thickness of such a diffusion layer can be increased to over 0.130 mm, the possible layer thickness also increasing with increasing proportion of iron or manganese, which of course reduces the service life HTKII conditions increased.
- a support layer can also be provided. which can be applied, for example, by low-pressure plasma spraying.
- This layer should contain 30 to 55%, preferably about 40%, chromium and 0.5 to 2%, preferably about 1%, of at least one of the elements from the group of rare earths, yttrium, scandium, hafnium, zirconium, Niobium, tantalum, silicon. If at all, aluminum should only be present in small amounts, namely less than 5%, preferably even less than 3.
- the rest of the layer consists of one or a mixture of the elements iron, cobalt, nickel, in which case production-related impurities can be added.
- the chromium content can be chosen lower, namely between 15 and 50%, to achieve an equally good effect. , preferably between about 20 and 30%.
- Claim 5 teaches that the second coating layer should belong to the MCrAlY type.
- Such layers are also known per se according to the prior art, e.g. B. again from DE-C 28 26 910.
- this combination in particular results in a particularly long service life of the metal objects at different temperatures.
- the second coating layer should have the following composition: 15 to 40% chromium, preferably approximately 20 to 30%; 3 to 15% aluminum, preferably about 7 to 12%; 0.2 to 3% of at least one element from the group of rare earths, yttrium, tantalum, hafnium, scandium, zirconium, niobium, rhenium, silicon, preferably about 0.7%, rest of at least one of the elements made of cobalt, nickel, and manufacturing-related impurities.
- the second coating layer should be applied by plasma spraying, in particular low-pressure plasma spraying.
- a diffusion barrier layer can significantly increase the service life.
- Such a layer can consist, for example, of titanium nitride or titanium carbide.
- one possibility of protection against particularly high temperatures is to prevent the temperatures from reaching the metallic layers.
- This can be achieved by thermal barrier layers on the outside of the metal object. These layers have the effect that the underlying metallic layers only have temperatures against which they are designed.
- it can be advantageous according to claim 9 to oxidize the surface of the second coating layer before the thermal barrier layer is applied.
- a total coating thickness of over 0.3 mm can be achieved.
- a component 1 has a first metallic coating layer 2, which is optimized against HTKII or is resistant due to its thickness. Above it is a second coating layer 3, which is resistant to HTKI. If necessary, there may be diffusion barrier layers 4, 5 between the base material 1 and the first coating layer 2 and / or between the first coating layer 2 and the second coating layer 3, which hinder the concentration compensation of individual elements by diffusion. Finally, a thermal barrier layer 6, which protects against particularly high temperatures, can also be attached on the very outside.
- the multiple coatings according to the invention are particularly suitable for blades and parts of gas turbines in which individual, e.g. B. cooled components, locally different temperatures occur, such as in systems that are operated at times at full load and sometimes only at partial load.
- thick multiple protective layers can be applied to such components, which usually consist of nickel-based alloys, which considerably extend the service life of the components, in particular of the blades.
- the coatings described can, as far as this is economically justifiable, be supplemented by further similar or different coatings.
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP89501389A JPH03503184A (ja) | 1988-02-05 | 1989-01-19 | 金属対象物、特に保護被覆を有するガスタービン翼 |
| DE8989901530T DE58904084D1 (de) | 1988-02-05 | 1989-01-19 | Metallgegenstand, insbesondere gasturbinenschaufel mit schutzbeschichtung. |
| IN91/CAL/89A IN171444B (enrdf_load_stackoverflow) | 1988-02-05 | 1989-01-30 |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE3803517 | 1988-02-05 | ||
| DEP3803517.0 | 1988-02-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO1989007159A1 true WO1989007159A1 (en) | 1989-08-10 |
Family
ID=6346731
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/DE1989/000023 WO1989007159A1 (en) | 1988-02-05 | 1989-01-19 | Metallic object, in particular gas turbine blade with protective coating |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0397731B1 (enrdf_load_stackoverflow) |
| JP (1) | JPH03503184A (enrdf_load_stackoverflow) |
| DE (1) | DE58904084D1 (enrdf_load_stackoverflow) |
| IN (1) | IN171444B (enrdf_load_stackoverflow) |
| WO (1) | WO1989007159A1 (enrdf_load_stackoverflow) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996012049A1 (de) * | 1994-10-14 | 1996-04-25 | Siemens Aktiengesellschaft | Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung |
| WO1996035825A1 (en) * | 1995-05-08 | 1996-11-14 | Helmut Tannenberger | Workpiece for high-temperature uses and process for producing it |
| WO1997005299A1 (de) * | 1995-07-25 | 1997-02-13 | Siemens Aktiengesellschaft | Erzeugnis mit einem metallischen grundkörper mit kühlkanälen und dessen herstellung |
| EP0949410A2 (de) | 1998-04-07 | 1999-10-13 | GHH BORSIG Turbomaschinen GmbH | Beschichteter Überströmkanal für eine Gasturbine |
| EP1260602A1 (de) * | 2001-05-23 | 2002-11-27 | Sulzer Metco AG | Verfahren zum Erzeugen eines wärmedämmenden Schichtsystems auf einem metallischen Substrat |
| WO2006061431A3 (en) * | 2004-12-11 | 2006-08-24 | Siemens Ag | A method of protecting a component against hot corrosion |
| US8475598B2 (en) | 2005-11-22 | 2013-07-02 | United Technologies Corporation | Strip process for superalloys |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1524334A1 (de) * | 2003-10-17 | 2005-04-20 | Siemens Aktiengesellschaft | Schutzschicht zum Schutz eines Bauteils gegen Korrosion und Oxidation bei hohen Temperaturen und Bauteil |
| ES2342552T3 (es) * | 2006-08-23 | 2010-07-08 | Siemens Aktiengesellschaft | Alabe de turbina con un sistema de recubrimiento. |
| EP2206805A1 (de) * | 2009-01-08 | 2010-07-14 | Siemens Aktiengesellschaft | MCrAIX-Schicht mit unterschiedlichen Chrom- und Aluminiumgehalten |
| EP2557201A1 (de) | 2011-08-09 | 2013-02-13 | Siemens Aktiengesellschaft | Legierung, Schutzschicht und Bauteil |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3649225A (en) * | 1969-11-17 | 1972-03-14 | United Aircraft Corp | Composite coating for the superalloys |
| FR2207198A1 (enrdf_load_stackoverflow) * | 1972-10-23 | 1974-06-14 | Onera (Off Nat Aerospatiale) | |
| FR2444559A1 (fr) * | 1978-12-21 | 1980-07-18 | Bbc Brown Boveri & Cie | Couche de protection contre la corrosion, en plusieurs epaisseurs, resistant aux temperatures elevees |
| DE3104581A1 (de) * | 1980-02-11 | 1982-01-28 | United Technologies Corp., 06101 Hartford, Conn. | Mit einer deckschicht versehener gegenstand aus einer superlegierung und verfahren zu seiner herstellung |
-
1989
- 1989-01-19 DE DE8989901530T patent/DE58904084D1/de not_active Expired - Fee Related
- 1989-01-19 WO PCT/DE1989/000023 patent/WO1989007159A1/de active IP Right Grant
- 1989-01-19 EP EP89901530A patent/EP0397731B1/de not_active Expired - Lifetime
- 1989-01-19 JP JP89501389A patent/JPH03503184A/ja active Pending
- 1989-01-30 IN IN91/CAL/89A patent/IN171444B/en unknown
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3649225A (en) * | 1969-11-17 | 1972-03-14 | United Aircraft Corp | Composite coating for the superalloys |
| FR2207198A1 (enrdf_load_stackoverflow) * | 1972-10-23 | 1974-06-14 | Onera (Off Nat Aerospatiale) | |
| FR2444559A1 (fr) * | 1978-12-21 | 1980-07-18 | Bbc Brown Boveri & Cie | Couche de protection contre la corrosion, en plusieurs epaisseurs, resistant aux temperatures elevees |
| DE3104581A1 (de) * | 1980-02-11 | 1982-01-28 | United Technologies Corp., 06101 Hartford, Conn. | Mit einer deckschicht versehener gegenstand aus einer superlegierung und verfahren zu seiner herstellung |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1996012049A1 (de) * | 1994-10-14 | 1996-04-25 | Siemens Aktiengesellschaft | Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung |
| US5993980A (en) * | 1994-10-14 | 1999-11-30 | Siemens Aktiengesellschaft | Protective coating for protecting a component from corrosion, oxidation and excessive thermal stress, process for producing the coating and gas turbine component |
| WO1996035825A1 (en) * | 1995-05-08 | 1996-11-14 | Helmut Tannenberger | Workpiece for high-temperature uses and process for producing it |
| WO1997005299A1 (de) * | 1995-07-25 | 1997-02-13 | Siemens Aktiengesellschaft | Erzeugnis mit einem metallischen grundkörper mit kühlkanälen und dessen herstellung |
| EP0949410A2 (de) | 1998-04-07 | 1999-10-13 | GHH BORSIG Turbomaschinen GmbH | Beschichteter Überströmkanal für eine Gasturbine |
| EP0949410A3 (de) * | 1998-04-07 | 2000-11-02 | MAN Turbomaschinen AG GHH BORSIG | Beschichteter Überströmkanal für eine Gasturbine |
| US6226978B1 (en) | 1998-04-07 | 2001-05-08 | Ghh Borsig Turbomaschinen Gmbh | Hot gas-carrying gas collection pipe of gas turbine |
| EP1260602A1 (de) * | 2001-05-23 | 2002-11-27 | Sulzer Metco AG | Verfahren zum Erzeugen eines wärmedämmenden Schichtsystems auf einem metallischen Substrat |
| US8168261B2 (en) | 2001-05-23 | 2012-05-01 | Sulzer Metco A.G. | Process for applying a heat shielding coating system on a metallic substrate |
| WO2006061431A3 (en) * | 2004-12-11 | 2006-08-24 | Siemens Ag | A method of protecting a component against hot corrosion |
| US8475598B2 (en) | 2005-11-22 | 2013-07-02 | United Technologies Corporation | Strip process for superalloys |
Also Published As
| Publication number | Publication date |
|---|---|
| IN171444B (enrdf_load_stackoverflow) | 1992-10-17 |
| DE58904084D1 (de) | 1993-05-19 |
| EP0397731B1 (de) | 1993-04-14 |
| EP0397731A1 (de) | 1990-11-22 |
| JPH03503184A (ja) | 1991-07-18 |
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