WO2007033650A1 - Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection - Google Patents
Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection Download PDFInfo
- Publication number
- WO2007033650A1 WO2007033650A1 PCT/DE2006/001636 DE2006001636W WO2007033650A1 WO 2007033650 A1 WO2007033650 A1 WO 2007033650A1 DE 2006001636 W DE2006001636 W DE 2006001636W WO 2007033650 A1 WO2007033650 A1 WO 2007033650A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- protective layer
- component
- protective coating
- structuring
- resistant
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 19
- 239000011253 protective coating Substances 0.000 title abstract 10
- 239000000306 component Substances 0.000 title description 2
- 238000005260 corrosion Methods 0.000 claims abstract description 13
- 230000007797 corrosion Effects 0.000 claims abstract description 13
- 229910052751 metal Inorganic materials 0.000 claims abstract description 8
- 239000002184 metal Substances 0.000 claims abstract description 8
- 238000007751 thermal spraying Methods 0.000 claims abstract description 8
- 239000000919 ceramic Substances 0.000 claims abstract description 6
- 239000002356 single layer Substances 0.000 claims abstract description 3
- 239000011241 protective layer Substances 0.000 claims description 84
- 239000010410 layer Substances 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 8
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 239000002245 particle Substances 0.000 claims description 4
- 230000008439 repair process Effects 0.000 claims description 4
- 239000011159 matrix material Substances 0.000 claims description 3
- 230000003647 oxidation Effects 0.000 claims description 3
- 238000007254 oxidation reaction Methods 0.000 claims description 3
- 229910052582 BN Inorganic materials 0.000 claims description 2
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 2
- UFGZSIPAQKLCGR-UHFFFAOYSA-N chromium carbide Chemical compound [Cr]#C[Cr]C#[Cr] UFGZSIPAQKLCGR-UHFFFAOYSA-N 0.000 claims description 2
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims description 2
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 claims description 2
- 229910003470 tongbaite Inorganic materials 0.000 claims description 2
- 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 claims description 2
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 claims description 2
- 229910001928 zirconium oxide Inorganic materials 0.000 claims description 2
- 238000010285 flame spraying Methods 0.000 description 2
- 238000007750 plasma spraying Methods 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 229910002441 CoNi Inorganic materials 0.000 description 1
- 229910003266 NiCo Inorganic materials 0.000 description 1
- 229910052769 Ytterbium Inorganic materials 0.000 description 1
- 239000012790 adhesive layer Substances 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010283 detonation spraying Methods 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 229910052763 palladium Inorganic materials 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- 229910052726 zirconium Inorganic materials 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]
Definitions
- the present invention relates to a method for producing a wear-resistant, temperature and corrosion-resistant protective layer for a component, in particular for components of a gas turbine, by means of thermal spraying.
- the invention further relates to a protective layer, namely a wear-resistant, temperature and corrosion-resistant protective layer for a component, in particular for components of a gas turbine, with an abrasive surface.
- the invention relates to a component, in particular a component of a gas turbine, with a protective layer.
- Such corrosion and oxidation protection layers are known and are used in particular in parts of turbines or aircraft engines as well as combustion chambers.
- hot corrosion protective layers so-called MCrAlY support layers are used, as described for example in US-A-4080486, EP-Bl-0486489 and US-A-4585481.
- these MCrAlY support layers can be used as a primer or as an adhesive layer between the metallic substrate to which the protective layer is applied and a ceramic cover layer.
- the application of the protective layer is carried out in particular by thermal spraying method, such. As flame spraying, high-speed flame spraying, detonation spraying, plasma spraying, arc spraying, laser spraying or Schmelzbadspritzen.
- DE-A1-10260462 and DE-A1-10351168 disclose further processes for producing a wear-resistant layer by means of thermal spraying.
- OS-A-5935407 also describes the application of an MCrAlY base layer to a workpiece by means of a plasma spraying method.
- a wear-resistant, temperature- and corrosion-resistant protective layer is applied by thermal spraying on a component, in particular on a component of a gas turbine, wherein during the application of the consisting of ceramic and / or a hard-metal combination protective layer on the Component for generating an abrasive surface of a structuring of the remote from the component surface of the protective layer is carried out.
- the wear-resistant layer in one operation d. H. single-layer
- the structuring of the component-remote surface of the protective layer takes place. Since no further operations are necessary for the production of the protective layer, the process can be carried out inexpensively, simply and quickly.
- the structuring is produced by a Abdeckmasktechnik during the application of the protective layer. But it is also possible that the structuring is produced by a segmented application of the protective layer or individual protective layer elements. Furthermore, it is possible that the structuring is produced by a different thickness order of the protective layer on the component.
- the Type of structuring can be predetermined and adapted to the corresponding requirements for the component or the requirements of the protective layer.
- a protective layer according to the invention namely a wear-resistant, ter ⁇ pe- ratur- corrosion resistant protective layer for a component, in particular for components of a gas turbine has an abrasive surface, wherein the protective layer is formed ein Anlagenig and applied by thermal spraying on the corresponding component, wherein during the application the protective layer consisting of ceramic and / or a hard metal / metal combination is structured on the component for producing the abrasive surface, structuring the surface of the protective layer facing away from the component.
- a protective layer is simple and inexpensive to produce. In particular, repairs to damaged protective layers can also be carried out very quickly.
- this has a thickness of 10 .mu.m-6 mm, in particular 30 .mu.m-300 .mu.m.
- the hard material or substances consist of boron nitride, titanium carbide, tungsten carbide, chromium carbide or zirconium oxide particles or a mixture thereof.
- the hard materials may have a particle size of 0.1 microns - 200 microns.
- the hard materials are arranged in a matrix of metal or a metal alloy.
- this may be formed as a continuous or segmented layer. It is also possible that the protective layer has different thicknesses, is cut-shaped or has a plurality of projections on the surface facing away from the component. These projections may be formed, for example, tooth, cutting or tip-shaped.
- the mentioned structuring possibilities of the protective layer according to the invention serve to form the abovementioned abrasive surface.
- An inventive component in particular a component of a gas turbine, in particular a rotor blade, has at least in a partial area, in particular the blade tip, a protective layer according to the features described above.
- the wear-resistant, high-temperature, oxidation-resistant and corrosion-resistant protective layer according to the invention is used in particular in the coating and / or repair of turbine and engine parts, in particular of gas turbines in aircraft engines.
- Figure 1 is a schematic representation of a first embodiment of a component according to the invention with a protective layer according to the invention
- Figure 2 is a schematic representation of a second embodiment of a component according to the invention with a protective layer according to the invention.
- FIGS. 3a to 3c schematically show side views of further exemplary embodiments of components according to the invention, each with a protective layer according to the invention.
- FIG. 1 shows a schematic representation of a first exemplary embodiment of a component 10 with a protective layer 12.
- the illustrated component 10 is a turbine blade 20 with a blade root 22 and a blade tip 18 opposite the blade root 22. It can be seen that at the blade tip 18, the protective layer 12 is formed.
- the protective layer 12 is intended to be wear-resistant, temperature-resistant and corrosion-resistant and is usually referred to as blade tip armor.
- the protective layer 12 is structured on the surface facing away from the component 10. The structuring takes place during the application of the protective layer 12 to the component 10.
- the protective layer 12 has a plurality of protrusions 16 on the surface 14 facing away from the component 10.
- FIG. 2 shows a schematic representation of a second embodiment of a component 10 with a protective layer 12.
- the component 10 is likewise a turbine. Shovel 20.
- the protective layer 12 is formed as a continuous layer. Abrasive properties of the protective layer 12 are achieved in this embodiment by different thicknesses of the protective layer 12 or by a blade-shaped design of the protective layer 12 (see Figure 3c).
- FIGS. 3 a to 3 c show schematically illustrated side views of further exemplary embodiments of components 10, each with a protective layer 12.
- the components 10 are again turbine blades 20. It can be seen that the blade tips 18 are each covered at least partially with the protective layer 12.
- the protective layer 12 shown in FIG. 3a is segmented (see also FIG. 1).
- the protective layers 12 shown in FIGS. 3b and 3c have cross-sections tapering outwards. This results in cutting edges 24, which leads to the formation of the abrasive property of the protective layer 12 on the component 10 opposite surface 14.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L'invention concerne un procédé pour produire par thermo-injection une couche de protection résistant à l'usure, à la chaleur et à la corrosion, cette couche de protection étant destinée à un composant, en particulier à des composants d'une turbine à gaz. Ce procédé se caractérise en ce que, lorsque la couche de protection constituée de céramique et/ou d'une combinaison matériau dur/métal est appliquée sur le composant pour produire une surface abrasive, la surface de la couche de protection opposée au composant fait l'objet d'une texturation. L'invention concerne en outre une couche de protection, notamment une couche de protection résistant à l'usure, à la chaleur et à la corrosion, cette couche de protection étant destinée à un composant, en particulier à des composants d'une turbine à gaz, et présentant une surface abrasive. Cette couche de protection est conçue en une seule couche et elle est produite par le procédé selon l'invention. L'invention concerne par ailleurs un composant, en particulier un composant d'une turbine à gaz, pourvu d'une couche de protection.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/067,274 US20090169372A1 (en) | 2005-09-21 | 2006-09-16 | Method of producing a protective coating, protective coating, and component with a protective coating |
| EP06805298A EP1929060A1 (fr) | 2005-09-21 | 2006-09-16 | Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102005044991.3 | 2005-09-21 | ||
| DE102005044991A DE102005044991A1 (de) | 2005-09-21 | 2005-09-21 | Verfahren zur Herstellung einer Schutzschicht, Schutzschicht und Bauteil mit einer Schutzschicht |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2007033650A1 true WO2007033650A1 (fr) | 2007-03-29 |
Family
ID=37450740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/DE2006/001636 WO2007033650A1 (fr) | 2005-09-21 | 2006-09-16 | Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20090169372A1 (fr) |
| EP (1) | EP1929060A1 (fr) |
| DE (1) | DE102005044991A1 (fr) |
| WO (1) | WO2007033650A1 (fr) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007026271A1 (de) * | 2007-06-05 | 2008-12-11 | Mtu Aero Engines Gmbh | Abdeckklebebänder und Verfahren zum Beschichten und/oder Ausbessern von Bauteilen |
| EP2177643A1 (fr) * | 2008-10-07 | 2010-04-21 | Siemens Aktiengesellschaft | Procédé de réparation d'un superalliage à l'aide de la même poudre de superalliage et de céramique |
| DE102008056652A1 (de) | 2008-11-10 | 2010-05-12 | Mtu Aero Engines Gmbh | Maske für das kinetische Kaltgaskompaktieren |
| IT1396884B1 (it) * | 2009-12-15 | 2012-12-20 | Nuovo Pignone Spa | Inserti in carburo di tungsteno e metodo |
| CN102418065B (zh) * | 2011-12-12 | 2013-07-03 | 中国矿业大学 | 复合金属碳化物耐磨涂层及其制备工艺 |
| US9827735B2 (en) | 2012-03-09 | 2017-11-28 | United Technologies Corporation | Erosion resistant and hydrophobic article |
| EP3216980A1 (fr) | 2016-03-08 | 2017-09-13 | Siemens Aktiengesellschaft | Procede de fabrication ou de reparation d'une aube et/ou d'un carter d'une turbomachine |
| EP3222812A1 (fr) | 2016-03-24 | 2017-09-27 | Siemens Aktiengesellschaft | Procede de fabrication ou de reparation d'une aube directrice, aube directrice, procede de fabrication ou de reparation d'un boitier d'une turbomachine et boitier |
| CN117328013B (zh) * | 2023-11-30 | 2024-01-26 | 西安致远航空科技有限公司 | 一种航空拉刀表面涂层及其制备工艺 |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2117269A (en) * | 1982-03-11 | 1983-10-12 | Rolls Royce | Thermal barrier coating |
| DE19840966A1 (de) * | 1998-09-08 | 2000-03-09 | Impreglon International L L C | Oberflächenbeschichtung für ein Substrat und Verfahren zur Ausbildung einer Oberflächenbeschichtung |
| EP1070769A1 (fr) * | 1999-07-22 | 2001-01-24 | ALSTOM POWER (Schweiz) AG | Procédé de revêtement d'un composant localement sollicité d'une façon différente |
| WO2001009405A1 (fr) * | 1999-07-30 | 2001-02-08 | Chromalloy Holland B.V. | Reduction de la force de resistance pour les composants des moteurs a turbine a gaz |
| EP0702130B1 (fr) * | 1994-09-16 | 2003-04-23 | MTU Aero Engines GmbH | Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs |
| WO2003083160A2 (fr) * | 2002-03-27 | 2003-10-09 | Applied Materials, Inc. | Evaluation d'un composant de chambre a revetement texture |
| US20040086689A1 (en) * | 2002-10-31 | 2004-05-06 | Tosoh Corporation | Island projection-modified part, method for producing the same, and apparatus comprising the same |
| US20040115351A1 (en) * | 2002-12-17 | 2004-06-17 | Yuk-Chiu Lau | High temperature abradable coatings |
| US20040258842A1 (en) * | 2003-06-19 | 2004-12-23 | Noriaki Hamaya | Coated member and method of manufacture |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3199836A (en) * | 1964-05-04 | 1965-08-10 | Gen Electric | Axial flow turbo-machine blade with abrasive tip |
| US4232995A (en) * | 1978-11-27 | 1980-11-11 | General Electric Company | Gas seal for turbine blade tip |
| US4610698A (en) * | 1984-06-25 | 1986-09-09 | United Technologies Corporation | Abrasive surface coating process for superalloys |
| DE3918380A1 (de) * | 1989-06-06 | 1990-12-20 | Starck Hermann C Fa | Hochtemperatur-verbund-werkstoff, verfahren zu seiner herstellung sowie dessen verwendung |
| US5264011A (en) * | 1992-09-08 | 1993-11-23 | General Motors Corporation | Abrasive blade tips for cast single crystal gas turbine blades |
| US5952110A (en) * | 1996-12-24 | 1999-09-14 | General Electric Company | Abrasive ceramic matrix turbine blade tip and method for forming |
| JPH11343564A (ja) * | 1998-05-28 | 1999-12-14 | Mitsubishi Heavy Ind Ltd | 高温機器 |
| US5997248A (en) * | 1998-12-03 | 1999-12-07 | Sulzer Metco (Us) Inc. | Silicon carbide composition for turbine blade tips |
| US6059530A (en) * | 1998-12-21 | 2000-05-09 | General Electric Company | Twin rib turbine blade |
| US6833203B2 (en) * | 2002-08-05 | 2004-12-21 | United Technologies Corporation | Thermal barrier coating utilizing a dispersion strengthened metallic bond coat |
| US20050014010A1 (en) * | 2003-04-22 | 2005-01-20 | Dumm Timothy Francis | Method to provide wear-resistant coating and related coated articles |
-
2005
- 2005-09-21 DE DE102005044991A patent/DE102005044991A1/de not_active Withdrawn
-
2006
- 2006-09-16 EP EP06805298A patent/EP1929060A1/fr not_active Ceased
- 2006-09-16 WO PCT/DE2006/001636 patent/WO2007033650A1/fr active Application Filing
- 2006-09-16 US US12/067,274 patent/US20090169372A1/en not_active Abandoned
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2117269A (en) * | 1982-03-11 | 1983-10-12 | Rolls Royce | Thermal barrier coating |
| EP0702130B1 (fr) * | 1994-09-16 | 2003-04-23 | MTU Aero Engines GmbH | Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs |
| DE19840966A1 (de) * | 1998-09-08 | 2000-03-09 | Impreglon International L L C | Oberflächenbeschichtung für ein Substrat und Verfahren zur Ausbildung einer Oberflächenbeschichtung |
| EP1070769A1 (fr) * | 1999-07-22 | 2001-01-24 | ALSTOM POWER (Schweiz) AG | Procédé de revêtement d'un composant localement sollicité d'une façon différente |
| WO2001009405A1 (fr) * | 1999-07-30 | 2001-02-08 | Chromalloy Holland B.V. | Reduction de la force de resistance pour les composants des moteurs a turbine a gaz |
| WO2003083160A2 (fr) * | 2002-03-27 | 2003-10-09 | Applied Materials, Inc. | Evaluation d'un composant de chambre a revetement texture |
| US20040086689A1 (en) * | 2002-10-31 | 2004-05-06 | Tosoh Corporation | Island projection-modified part, method for producing the same, and apparatus comprising the same |
| US20040115351A1 (en) * | 2002-12-17 | 2004-06-17 | Yuk-Chiu Lau | High temperature abradable coatings |
| US20040258842A1 (en) * | 2003-06-19 | 2004-12-23 | Noriaki Hamaya | Coated member and method of manufacture |
Also Published As
| Publication number | Publication date |
|---|---|
| US20090169372A1 (en) | 2009-07-02 |
| DE102005044991A1 (de) | 2007-03-22 |
| EP1929060A1 (fr) | 2008-06-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1929060A1 (fr) | Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection | |
| EP2316988B1 (fr) | Aube de turbine résistant à l'usure et à l'oxydation | |
| EP2317078B1 (fr) | Aube de turbine abrasive monocristalline | |
| EP2780552B1 (fr) | Blindage d'ailettes d'étanchéité d'aubes en tial par dépôt de particules de matériau dur par brasage par induction | |
| DE102009049707A1 (de) | Verfahren zur Herstellung einer Lauf- oder Statorschaufel und eine derartige Schaufel | |
| WO2010121597A2 (fr) | Procédé de production d'un blindage d'un bout d'aube et aubes ainsi produites et turbines à gaz | |
| DE102007005755A1 (de) | Vorrichtung zum Schutz von Bauteilen mit brennbarer Titanlegierung vor Titanfeuer und Verfahren zu deren Herstellung | |
| WO2010094273A2 (fr) | Fabrication d'aubes et disque combinés de turbine avec une couche de protection contre l'oxydation ou la corrosion | |
| WO2011015187A1 (fr) | Revêtement de bout d'aube abrasable | |
| WO2011009430A1 (fr) | Procédé de revêtement d'une aube de turbine | |
| EP2245274A1 (fr) | Procede et dispositif de revetement partiel d'elements | |
| DE102011087158A1 (de) | Verfahren zur Panzerung der Z-Notch von TiAl-Schaufeln | |
| WO2015121000A1 (fr) | Aube de compresseur pourvue d'un revêtement dur résistant à l'érosion | |
| EP0868253A2 (fr) | Procede d'elimination de fissures dans un element constitutif metallique, notamment une aube de turbine, et aube de turbine | |
| EP1382707A1 (fr) | Systeme stratifie | |
| EP2802742A1 (fr) | Procédé de fabrication et de restauration de revêtements de barrière thermique en céramique dans des turbines à gaz et turbine à gaz correspondante | |
| EP2275220A1 (fr) | Procédé de blindage de composants à partir d'une matière première à base de TiAl et composants correspondants | |
| EP2808488B1 (fr) | Aube en TiAl dotée d'une modification de surface | |
| EP2537959B1 (fr) | Revêtement multicouches anti-usure et procédé de fabrication | |
| EP3423752B1 (fr) | Élément exposé à un écoulement et procédé de revêtement d'un élément exposé à un écoulement | |
| EP2684982A1 (fr) | Couche de protection pour un composant d'une turbomachine | |
| EP2761057B1 (fr) | Système de couche doté d'une surface de substrat structurée et son procédé de fabrication | |
| EP3493931A1 (fr) | Procédé de fabrication d'une structure de conduit et constituants | |
| EP3269842A1 (fr) | Procede destine a la fabrication d'un composant et composant | |
| EP2913425A1 (fr) | Couche d'isolation thermique avec alliage iridium-rhodium |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
| DPE1 | Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101) | ||
| WWE | Wipo information: entry into national phase |
Ref document number: 2006805298 Country of ref document: EP |
|
| WWP | Wipo information: published in national office |
Ref document number: 2006805298 Country of ref document: EP |
|
| WWE | Wipo information: entry into national phase |
Ref document number: 12067274 Country of ref document: US |