EP1664383A1 - Wear-resistant layer, component comprising such a wear-resistant layer, and production method - Google Patents
Wear-resistant layer, component comprising such a wear-resistant layer, and production methodInfo
- Publication number
- EP1664383A1 EP1664383A1 EP04762715A EP04762715A EP1664383A1 EP 1664383 A1 EP1664383 A1 EP 1664383A1 EP 04762715 A EP04762715 A EP 04762715A EP 04762715 A EP04762715 A EP 04762715A EP 1664383 A1 EP1664383 A1 EP 1664383A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- component
- wear protection
- protection layer
- protected
- 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.)
- Ceased
Links
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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
-
- 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/323—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one amorphous metallic material layer
-
- 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
-
- 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/347—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with layers adapted for cutting tools or wear applications
-
- 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
- C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C8/02—Pretreatment of the material to be coated
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/228—Nitrides
- F05D2300/2281—Nitrides of aluminium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/228—Nitrides
- F05D2300/2284—Nitrides of titanium
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12576—Boride, carbide or nitride component
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component
Definitions
- Wear protection layer component with such a wear protection layer and manufacturing process
- the invention relates to a wear protection layer, in particular an erosion protection layer for gas turbine components, according to the preamble of patent claim 1. Furthermore, the invention relates to a component with such a wear protection layer according to the preamble of patent claim 1 1 and a method for producing a wear protection layer according to the preamble of patent claim 13.
- Fluid mechanically loaded components such as gas turbine components
- Erosion is a wear process that is caused by solid substances moving in the gas flow.
- wear protection layers are required which protect the components against wear, in particular against erosion, corrosion and oxidation.
- the wear protection layer disclosed there essentially consists of amorphous or amorphous-nanocrystalline metals, in particular of an alloy based on nickel-tungsten.
- the present invention is based on the problem of creating a novel wear protection layer, in particular for gas turbine components, and a component with such a wear protection layer and a corresponding production method.
- the wear protection layer according to the invention has an at least two-layer structure, a first layer being applied to the surface of the component to be protected and having a material composition adapted to the material composition of the component, and a second layer forming an outer cover layer.
- the first layer is preferably designed as a porous, relatively soft layer with damping properties, whereas the second layer is designed as a relatively hard layer.
- the outer, second layer provides the actual erosion protection.
- the underlying, damping first layer can absorb energy when particles are impacted, thus preventing cracking in the component to be protected.
- the component according to the invention is defined in independent claim 1 1 and the method according to the invention is defined in independent claim 13.
- FIG. 1 shows a highly schematic representation of a blade of a gas turbine which has a wear protection layer according to the invention
- FIGS. 1 and 2 show a blade of a gas turbine in perspective view, which carries a wear protection layer according to the invention.
- Fig. 2 shows a schematic cross section through the blade and the wear protection view.
- 1 shows a blade 10 of a gas turbine with an airfoil 11 and a blade root 12.
- the entire blade 10, namely a surface to be protected is coated with a wear protection layer 13.
- the complete blade 10 is coated with the wear protection layer 13 in the exemplary embodiment shown, it is also possible for the blade 10 to have the wear protection layer 13 only in sections, that is to say only in the area of the airfoil 11 or in the area of the blade root 12.
- Other gas turbine components such as integrally bladed rotors, can also be coated with the wear protection layer 13.
- FIG. 2 shows a cross section through the blade 10 in the region of the airfoil 11, the wear protection layer 13 being applied to a surface 14 of the airfoil 11.
- the wear protection layer 13 which forms an erosion protection layer in the exemplary embodiment shown, is constructed at least in two layers or two layers.
- the wear protection layer 13 comprises two layers.
- a first layer 15 is applied directly to the surface 1 of the airfoil 11.
- a second layer 16 forms an outer cover layer of the wear protection layer 13 and is applied directly to the first layer 15.
- the first layer 15 is produced from a material or a material that is adapted to the material composition of the component to be coated, in the exemplary embodiment shown to the material composition of the blade 10 or of the airfoil 11 . If the component to be coated, namely the airfoil 11, consists of a titanium alloy, then the first layer 15 of the wear protection layer 13 is also formed from a titanium alloy. In the exemplary embodiment shown, the airfoil is formed from a titanium-aluminum material or a titanium-aluminum material and the first layer 15 of the wear protection layer 13 likewise consists of a titanium-aluminum material.
- the first layer 15 of the wear protection layer 13 is porous and relatively soft compared to the component to be coated, namely the airfoil 11 to be coated.
- pores 17 are within the The first layer 15 of the wear protection layer 13 is shown in a highly schematic manner.
- the porous and relatively soft first layer 15 has damping properties.
- the second layer 16 applied to the first layer 15 is relatively hard in comparison to the first layer 15 and in comparison to the component to be coated, namely the airfoil 11 to be coated.
- the second layer 16 of the wear protection layer 13 is preferably made of a titanium nitride material, an aluminum nitride material or a titanium aluminum -Nitride material manufactured.
- the second layer 16, which forms the cover layer of the wear protection layer 13, is relatively thin compared to the first layer 15.
- the outer, second layer 16 preferably has a thickness of less than 0.1 mm.
- the inner first layer 15 has a thickness of up to 1 mm.
- the relatively hard, outer second layer 16 provides the actual erosion protection of the wear protection layer 13.
- the second layer 16 protects the airfoil 11 against erosion by fine particles.
- the underlying first layer 15, which is porous and relatively soft, has damping properties so that the same energy can be absorbed when larger particles impact the wear protection layer 13.
- the fine, round and microscopic pores 17 within the first layer 15 of the wear protection layer 13 prevent a crack from the relatively hard, outer layer 16 into the component to be protected, namely the airfoil 1 1 to be protected, when larger particles impact ,
- the wear protection layer 13 according to the invention represents effective protection against erosion wear.
- the first layer 15 of the wear protection layer 13 consists of a similar or the same material as the component to be protected, thermally induced internal stresses or diffusion problems on the part to be protected become Avoided component.
- the wear protection layer 13 can thus be safely and permanently applied to the component to be protected.
- the wear protection layer 13 is applied in layers to the component to be protected.
- the first layer 15 and subsequently and the second layer 16 of the wear protection layer 13 are applied to the component to be protected, which has a component material composition.
- the first layer 15 of the wear protection layer 13 has a material composition adapted to the component material composition and is designed as a porous layer.
- the first layer 15 of the wear protection layer 13 is applied to the surface of the component to be protected by means of a directed, atomic or nanoscale particle beam or matter vapor jet.
- a PVD process Physical Vapor Deposition
- additives are incorporated into the matter vapor jet, which evaporate during the subsequent hardening of the first layer 15 and thereby leave the pores 17.
- the additives are preferably designed as fulerenes. Instead of the fulerenes, however, other additives can also be used which evaporate when the first layer 15 hardens or burns in and leave the pores 17.
- the first layer 15 can also be applied to the surface of the component to be protected using a slip process.
- a slip material the composition of which is adapted to the material composition of the component to be protected, is applied to the component to be protected by brushing, dipping or spraying.
- additives are embedded in this slip material, which evaporate when the first layer hardens and leave behind the pores.
- the second layer 16 is then applied to the first layer 15.
- the second layer 16 is applied directly to the first layer 15. This is preferably done by vapor deposition, nitriding, aluminizing or oxidizing.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10343761A DE10343761A1 (en) | 2003-09-22 | 2003-09-22 | Wear protection layer, component with such a wear protection layer and manufacturing process |
PCT/DE2004/001882 WO2005031038A1 (en) | 2003-09-22 | 2004-08-26 | Wear-resistant layer, component comprising such a wear-resistant layer, and production method |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1664383A1 true EP1664383A1 (en) | 2006-06-07 |
Family
ID=34306005
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04762715A Ceased EP1664383A1 (en) | 2003-09-22 | 2004-08-26 | Wear-resistant layer, component comprising such a wear-resistant layer, and production method |
Country Status (4)
Country | Link |
---|---|
US (1) | US20070190352A1 (en) |
EP (1) | EP1664383A1 (en) |
DE (1) | DE10343761A1 (en) |
WO (1) | WO2005031038A1 (en) |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102135018B (en) * | 2006-06-08 | 2012-12-05 | 西门子公司 | Coated turbine part and method for coating turbine part |
RU2414603C2 (en) * | 2006-06-08 | 2011-03-20 | Сименс Акциенгезелльшафт | Component of turbine (versions), turbine and procedure for turbine component coating |
DE102006050789A1 (en) * | 2006-10-27 | 2008-04-30 | Mtu Aero Engines Gmbh | Vaporized coating for a gas turbine of an aircraft engine comprises pore formers formed as an adhesion promoting layer and/or a heat insulating layer |
DE102007005755A1 (en) * | 2007-02-06 | 2008-08-07 | Mtu Aero Engines Gmbh | Device for the protection of components with combustible titanium alloy from titanium fire and process for their production |
DE102008019891A1 (en) | 2008-04-21 | 2009-10-22 | Mtu Aero Engines Gmbh | Erosion protection coating |
DE102008045381A1 (en) * | 2008-09-02 | 2010-03-04 | Schaeffler Kg | Wear and corrosion-inhibiting layer composite |
EP2228461A1 (en) | 2009-02-26 | 2010-09-15 | Siemens Aktiengesellschaft | Component coating |
DE102009018685A1 (en) | 2009-04-23 | 2010-10-28 | Mtu Aero Engines Gmbh | Method for producing an armor of a blade tip as well as correspondingly produced blades and gas turbines |
US20100304107A1 (en) * | 2009-05-27 | 2010-12-02 | United Technologies Corporation | Layered coating for erosion protection |
US8721294B2 (en) | 2010-05-20 | 2014-05-13 | United Technologies Corporation | Airfoil with galvanically isolated metal coating |
US9291062B2 (en) | 2012-09-07 | 2016-03-22 | General Electric Company | Methods of forming blades and method for rendering a blade resistant to erosion |
WO2015053832A2 (en) * | 2013-07-09 | 2015-04-16 | United Technologies Corporation | High-modulus coating for local stiffening of airfoil trailing edges |
EP3019710A4 (en) | 2013-07-09 | 2017-05-10 | United Technologies Corporation | Plated polymer fan |
EP3019711B1 (en) | 2013-07-09 | 2023-11-01 | RTX Corporation | Plated polymer nosecone |
WO2015006438A1 (en) | 2013-07-09 | 2015-01-15 | United Technologies Corporation | Plated polymer compressor |
US9789664B2 (en) | 2013-07-09 | 2017-10-17 | United Technologies Corporation | Plated tubular lattice structure |
WO2015069335A2 (en) * | 2013-09-09 | 2015-05-14 | United Technologies Corporation | Fan blades and manufacture methods |
US9834835B2 (en) * | 2015-02-18 | 2017-12-05 | United Technologies Corporation | Fire containment coating system for titanium |
US10450876B2 (en) * | 2015-04-15 | 2019-10-22 | United Technologies Corporation | Abrasive tip blade manufacture methods |
CN114150254B (en) * | 2021-11-10 | 2022-09-06 | 中国科学院上海硅酸盐研究所 | Thermal barrier coating for TiAl alloy and preparation method thereof |
Family Cites Families (18)
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US3758233A (en) * | 1972-01-17 | 1973-09-11 | Gen Motors Corp | Vibration damping coatings |
US3951612A (en) * | 1974-11-12 | 1976-04-20 | Aerospace Materials Inc. | Erosion resistant coatings |
US4917960A (en) * | 1983-12-29 | 1990-04-17 | Sermatech International, Inc. | Porous coated product |
US4839245A (en) * | 1985-09-30 | 1989-06-13 | Union Carbide Corporation | Zirconium nitride coated article and method for making same |
GB8710296D0 (en) * | 1987-04-30 | 1987-06-03 | British Petroleum Co Plc | Wear resistant multi-layered composite |
DE3742944C1 (en) * | 1987-12-18 | 1988-10-27 | Mtu Muenchen Gmbh | Oxidation protection layer |
US4904528A (en) * | 1987-12-24 | 1990-02-27 | United Technologies Corporation | Coated gas turbine engine compressor components |
US4904542A (en) * | 1988-10-11 | 1990-02-27 | Midwest Research Technologies, Inc. | Multi-layer wear resistant coatings |
JPH03221441A (en) * | 1990-01-26 | 1991-09-30 | Ishikawajima Harima Heavy Ind Co Ltd | Anticorrosive and oxidation-resistant material and manufacture thereof |
US5672436A (en) * | 1990-05-31 | 1997-09-30 | Grumman Aerospace Corporation | Oxidation protection method for titanium |
US5413871A (en) * | 1993-02-25 | 1995-05-09 | General Electric Company | Thermal barrier coating system for titanium aluminides |
US5952085A (en) * | 1994-03-23 | 1999-09-14 | Rolls-Royce Plc | Multiple layer erosion resistant coating and a method for its production |
US5975912A (en) * | 1994-06-03 | 1999-11-02 | Materials Research Corporation | Low temperature plasma-enhanced formation of integrated circuits |
US5783315A (en) * | 1997-03-10 | 1998-07-21 | General Electric Company | Ti-Cr-Al protective coatings for alloys |
FR2767841B1 (en) * | 1997-08-29 | 1999-10-01 | Commissariat Energie Atomique | PROCESS FOR THE PREPARATION BY CHEMICAL VAPOR DEPOSITION (CVD) OF A MULTI-LAYER COATING BASED ON Ti-Al-N |
GB9911006D0 (en) * | 1999-05-13 | 1999-07-14 | Rolls Royce Plc | A titanium article having a protective coating and a method of applying a protective coating to a titanium article |
US6544665B2 (en) * | 2001-01-18 | 2003-04-08 | General Electric Company | Thermally-stabilized thermal barrier coating |
US7186092B2 (en) * | 2004-07-26 | 2007-03-06 | General Electric Company | Airfoil having improved impact and erosion resistance and method for preparing same |
-
2003
- 2003-09-22 DE DE10343761A patent/DE10343761A1/en not_active Ceased
-
2004
- 2004-08-26 WO PCT/DE2004/001882 patent/WO2005031038A1/en active Application Filing
- 2004-08-26 US US10/572,770 patent/US20070190352A1/en not_active Abandoned
- 2004-08-26 EP EP04762715A patent/EP1664383A1/en not_active Ceased
Non-Patent Citations (1)
Title |
---|
See references of WO2005031038A1 * |
Also Published As
Publication number | Publication date |
---|---|
US20070190352A1 (en) | 2007-08-16 |
DE10343761A1 (en) | 2005-04-14 |
WO2005031038A1 (en) | 2005-04-07 |
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