WO2011001117A1 - Revêtement de protection thermique pour une pièce de turbomachine et son procédé de réalisation - Google Patents
Revêtement de protection thermique pour une pièce de turbomachine et son procédé de réalisation Download PDFInfo
- Publication number
- WO2011001117A1 WO2011001117A1 PCT/FR2010/051382 FR2010051382W WO2011001117A1 WO 2011001117 A1 WO2011001117 A1 WO 2011001117A1 FR 2010051382 W FR2010051382 W FR 2010051382W WO 2011001117 A1 WO2011001117 A1 WO 2011001117A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- coating
- metal alloy
- thermal
- ceramic
- thermal protection
- Prior art date
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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- 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
- C23C28/34—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
- C23C28/341—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 at least one carbide 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
- C23C28/345—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 at least one oxide layer
- C23C28/3455—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 at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide 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
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
-
- 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
- Y10T428/12479—Porous [e.g., foamed, spongy, cracked, etc.]
-
- 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
- Y10T428/21—Circular sheet or circular blank
- Y10T428/213—Frictional
-
- 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
- Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
- Y10T428/259—Silicic material
Definitions
- the invention relates to a thermal protection coating, in particular for a part of a turbomachine such as a turboprop or an airplane turbojet, and a method for producing this coating.
- a certain number of parts must be protected or isolated from a heat input either from a flow of hot gases generated in the turbomachine, or from neighboring parts worn themselves at high speeds. temperature. It is therefore necessary to equip these parts with thermal protection means that are compatible with the requirements specific to aircraft engines: durability, direct environmental resistance, low weight, simplicity, proven efficiency, etc.
- thermal protection means are not added parts and instead are integrated parts to protect that already have a specific function in the aircraft engine. It is therefore not possible to use thermal protection sheets, which are effective but which constitute additional parts increasing the mass and decreasing the available space in the engine.
- the invention therefore relates to a thermal protection coating of turbomachine parts, in particular in an aircraft engine, which does not have the aforementioned drawbacks.
- thermal protective coating which is simple, easy and economical, which can have a relatively large thickness and has a relatively low density.
- thermal protection coating in particular for turbomachine parts or brake discs, characterized in that it comprises at least 80% by volume of hollow ceramic microbeads distributed in a metal alloy to nickel or cobalt base.
- This coating has a thermal conductivity less than or equal to 1W / m ° C. and its thickness can reach about 5 mm, this thickness being adjustable and to control the heat transfer.
- Its density is less than 2000 kg / m 3 and it can be used over temperature ranges of between -50 ° C. and + 1100 ° C., depending on the metal alloy associated with the ceramic microbeads.
- micro-ceramic balls which are derived from incinerator combustion products and have a very low cost price.
- the resistance to heat transfer of the coating according to the invention is mainly related to the presence of hollow ceramic microbeads whose volume proportion may be greater than 90%.
- the diameter of the micro-beads is typically between 30 and 30.
- the metal alloy of the coating according to the invention may comprise aluminum, chromium and ytthum.
- the invention also proposes a process for producing a thermal protection coating of the type described above, this process being characterized in that it consists in forming the thermal spray coating on the surface of a piece, a mixture of ceramic hollow micro-beads and a powder of a metal alloy based on nickel or chromium, by means of a plasma torch generating a plasma dart oriented towards the part and in which one injects simultaneously and laterally, upstream, the metal alloy powder and, downstream, the ceramic microbeads.
- a metal alloy bonding layer having a thickness typically of between 50 and 200 ⁇ m, the alloy of the bonding layer being preferably identical to that of the thermal protection coating.
- This bonding layer increases the roughness of the surface of the part and allows a better traction adhesion of the thermal protection coating.
- the method may then consist in forming, on the thermal protective coating, a protective layer against erosion or against frictional wear and / or a reflective layer of protection against thermal radiation.
- the invention also proposes a turbomachine part, such as a crankcase or a rear pod, or a brake disk in a braking system, characterized in that it comprises a thermal protection coating as described above or realized by execution of the method which has just been described.
- FIG. 2 is a graph showing thermal expansion curves of a coating according to the invention and of the part on which this coating is deposited;
- FIG. 3 is a schematic sectional view, on a large scale, of a part surface having a thermal protection coating according to the invention.
- FIG. 1 schematically shows means for the formation of a thermal protection coating 10 on the surface of a part 12, in particular of a turbomachine part, these means comprising a plasma torch 14 comprising supply of plasmagene gases such as argon and hydrogen and electrical supply means, and means 16 for lateral injection of a metal powder flow and means 18 for lateral injection of a flow of ceramic hollow micro-beads, the metal powder and the ceramic microspheres being injected into a plasma dart at a distance D from the surface of the part to be coated which is of the order of 150 mm for a torch 14 of a given type.
- a plasma torch 14 comprising supply of plasmagene gases such as argon and hydrogen and electrical supply means
- means 16 for lateral injection of a metal powder flow and means 18 for lateral injection of a flow of ceramic hollow micro-beads, the metal powder and the ceramic microspheres being injected into a plasma dart at a distance D from the surface of the part to be coated which is of the order of 150 mm for
- the injection positions of the metal powder and the ceramic balls are adjustable, the injection of the ceramic balls being downstream of the injection of the metal powder to take into account the difference in density of these two constituents.
- the metal powder injected at 16 into the plasma stinger is a powder of a metal alloy such as NiAl, NiCrAl or MCrAlY, M being nickel or cobalt or nickel-cobalt, depending on the temperatures at which the piece 12 is exposed. to protect.
- a metal alloy such as NiAl, NiCrAl or MCrAlY, M being nickel or cobalt or nickel-cobalt, depending on the temperatures at which the piece 12 is exposed. to protect.
- alloys of the NiCrAI type for temperature ranges between -50 ° C. and + 900 ° C. and alloys of the MCrAIY type for temperature ranges of up to + 1100 ° C.
- M being a metal.
- Ni or Co or nickel-cobalt the hollow micro-ceramic balls injected at 18 have any composition and a mean diameter of between approximately 30 and 250 ⁇ m, these microbeads being for example of the silico-aluminous type and being recycling products such as those resulting from combustion. incinerator.
- the mixture projected onto the surface of the part 12 comprises at least 80% by volume of ceramic micro-beads and, preferably, at least 90% by volume of these microbeads.
- a mixture of a NiCrAl alloy and hollow ceramic microspheres is sprayed onto the surface of the part 12 using a torch 14, the metal alloy flow rate being 24 g / min. and the flow rate of ceramic micro-beads being 48 g / min.
- the plasma torch is fed with a plasma Ar-H2 gas flow rate of between 5 and 50 liters per minute, and with an electric current of an intensity of 500A.
- the piece 12 is formed with a coating 10 having a density of 1700 kg / m 3 which contains about 95% by volume of hollow ceramic microspheres.
- the thermal conductivity of this coating is in the range of 0.7 to 1, 4 W / m. ° C between 20 and 800 0 C.
- the thickness of the coating 10 is typically between 2 and 5 mm, depending temperatures at which the piece 12 is subjected.
- the protective coating 10 has a coefficient of thermal expansion lower than that of the part 12 as can be seen from the thermal expansion curves of FIG.
- This figure shows the curve d1 of thermal expansion of the part 12 as a function of the temperature T, and the curve d2 of thermal expansion of the coating 10.
- the material of this coating is subjected to a temperature that is quite substantially greater than the temperature at which the part 12 is exposed.
- the thermal protective coating has a coefficient of expansion less than that of the part 12, the thermal expansions of the part 12 and the coating 10 at the temperatures they are applied to them are substantially equal and their difference ⁇ d is relatively small.
- the thermal protection coating 10 will not be the seat of an accumulation of tensile stresses that could cause microcracks, in the insulating coating and / or at the interface between the piece 12 and the coating 10, these microfissurations forming thermal bridges and degrading the thermal insulation.
- the thermal protective coating 10 has an adhesion on the part 12 of between 5 and 20 MPa, depending on its content of hollow micro-beads, and a hardness of between 10 and 80 HR15Y.
- This attachment layer 22 may be formed by thermal spraying a metal material which is preferably identical to the metal alloy of the coating 10.
- the attachment layer 22 may have a thickness typically between 50 and 200 microns.
- thermal protection coating 10 is sensitive to erosion, because the presence of the hollow ceramic micro-beads 24 can be formed on the coating 10 an erosion protection layer, this layer 26 being made by projection thermal of a metallic material and having a thickness typically between 50 and 150 microns, or deposit on the coating 10, by painting or by deposit electrolytic, (this coating being electroconductive), a layer of another material having anti-erosion properties.
- the upper layer 26 may be an antifriction layer or a protective layer against frictional wear, such as for example a layer of a carbide such as WC / Co or WC / CoCr, or a layer of a standard metallic material such as NiAI or NiCrAI coated with a film of a mineral varnish resistant to high temperatures.
- a protective layer against frictional wear such as for example a layer of a carbide such as WC / Co or WC / CoCr, or a layer of a standard metallic material such as NiAI or NiCrAI coated with a film of a mineral varnish resistant to high temperatures.
- the upper layer 26 may have reflective properties with respect to the incident radiative spectrum.
- the thermal protection coating 10 it is possible to deposit on the thermal protection coating 10 a layer of small thickness (for example 50 to 200 ⁇ m) of a ceramic coating such as ZrO 2 / Y 2 O 3, which can be used up to temperatures of approximately 1250 ° C.
- a ceramic coating such as ZrO 2 / Y 2 O 3, which can be used up to temperatures of approximately 1250 ° C.
- Such a layer makes it possible to reflect more than 40% of the radiant energy received.
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012103463/02A RU2012103463A (ru) | 2009-07-02 | 2010-07-01 | Теплозащитное покрытие для детали газотурбинного двигателя и способ его реализации |
US13/380,952 US20120107110A1 (en) | 2009-07-02 | 2010-07-01 | thermal protection coating for a turbine-engine part, and a method of making it |
JP2012518122A JP2012531523A (ja) | 2009-07-02 | 2010-07-01 | タービンエンジン部品用の断熱被膜およびその製造方法 |
EP10742020A EP2449146A1 (fr) | 2009-07-02 | 2010-07-01 | Revêtement de protection thermique pour une pièce de turbomachine et son procédé de réalisation |
CN2010800300792A CN102471860A (zh) | 2009-07-02 | 2010-07-01 | 用于涡轮引擎部件的热保护涂层及其制作方法 |
CA2766493A CA2766493A1 (fr) | 2009-07-02 | 2010-07-01 | Revetement de protection thermique pour une piece de turbomachine et son procede de realisation |
BRPI1014009A BRPI1014009A2 (pt) | 2009-07-02 | 2010-07-01 | revestimento de proteção térmica, processo de produção de um revestimento de proteção térmica, peça de turbomáquina, e, disco de freio. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0903251A FR2947568B1 (fr) | 2009-07-02 | 2009-07-02 | Revetement de protection thermique pour une piece de turbomachine et son procede de realisation |
FR09/03251 | 2009-07-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011001117A1 true WO2011001117A1 (fr) | 2011-01-06 |
Family
ID=41463064
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2010/051382 WO2011001117A1 (fr) | 2009-07-02 | 2010-07-01 | Revêtement de protection thermique pour une pièce de turbomachine et son procédé de réalisation |
Country Status (9)
Country | Link |
---|---|
US (1) | US20120107110A1 (fr) |
EP (1) | EP2449146A1 (fr) |
JP (1) | JP2012531523A (fr) |
CN (1) | CN102471860A (fr) |
BR (1) | BRPI1014009A2 (fr) |
CA (1) | CA2766493A1 (fr) |
FR (1) | FR2947568B1 (fr) |
RU (1) | RU2012103463A (fr) |
WO (1) | WO2011001117A1 (fr) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2604377B1 (fr) * | 2011-12-15 | 2015-07-15 | Siemens Aktiengesellschaft | Procédé de traitement laser d'une pièce doté d'une couche en céramique |
CN102744930B (zh) * | 2012-06-26 | 2015-08-19 | 中国科学院宁波材料技术与工程研究所 | 空调压缩机零部件表面的强韧润滑复合薄膜及其制备方法 |
US10458255B2 (en) * | 2013-02-10 | 2019-10-29 | United Technologies Corporation | Removable film for airfoil surfaces |
US20180179623A1 (en) * | 2016-12-22 | 2018-06-28 | GM Global Technology Operations LLC | Thermal spray deposition of hollow microspheres |
CN111520423B (zh) * | 2020-05-11 | 2021-03-16 | 中国矿业大学 | 一种矿井高速提升机用非均质制动盘 |
CN114455757B (zh) * | 2022-01-06 | 2024-01-19 | 纳美盾新材料有限公司 | 一种净水处理系统及其工艺 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2507729A1 (fr) * | 1981-06-12 | 1982-12-17 | Snecma | Joint susceptible d'etre use par abrasion et son procede de realisation |
WO1997018341A1 (fr) * | 1995-11-13 | 1997-05-22 | The University Of Connecticut | Produits nanostructures pour pulverisation a chaud |
US6071628A (en) * | 1999-03-31 | 2000-06-06 | Lockheed Martin Energy Systems, Inc. | Thermal barrier coating for alloy systems |
US20040137259A1 (en) * | 2003-01-09 | 2004-07-15 | Pabla Surinder Singh | High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2507331A1 (fr) * | 1981-06-05 | 1982-12-10 | Cables De Lyon Geoffroy Delore | Dispositif de jonction des extremites de deux cables sous-marins a fibres optiques |
US4386112A (en) * | 1981-11-02 | 1983-05-31 | United Technologies Corporation | Co-spray abrasive coating |
JPH0248769B2 (ja) * | 1989-03-29 | 1990-10-26 | Toyo Kaabon Kk | Bureekipatsudo |
CA2055897C (fr) * | 1990-11-21 | 1997-08-26 | Larry Sokol | Enceinte utilisee pour l'application d'un enduit vaporise a chaud et methode d'utilisation connexe |
EP0816526B1 (fr) * | 1996-06-27 | 2001-10-17 | United Technologies Corporation | Système de revêtement barrière thermique isolant |
US6977060B1 (en) * | 2000-03-28 | 2005-12-20 | Siemens Westinghouse Power Corporation | Method for making a high temperature erosion resistant coating and material containing compacted hollow geometric shapes |
JP3825231B2 (ja) * | 2000-07-24 | 2006-09-27 | 三菱重工業株式会社 | 溶射用中空セラミックス粉末の製造方法 |
US6670046B1 (en) * | 2000-08-31 | 2003-12-30 | Siemens Westinghouse Power Corporation | Thermal barrier coating system for turbine components |
JP2003308074A (ja) * | 2002-04-16 | 2003-10-31 | Oda Kensetsu Kk | 多孔質吸音・遮音性成形体及びその製造方法 |
CA2504831C (fr) * | 2005-04-21 | 2010-10-19 | Standard Aero Limited | Revetements composites en ceramique resistant a l'usure et methode de production connexe |
-
2009
- 2009-07-02 FR FR0903251A patent/FR2947568B1/fr active Active
-
2010
- 2010-07-01 US US13/380,952 patent/US20120107110A1/en not_active Abandoned
- 2010-07-01 RU RU2012103463/02A patent/RU2012103463A/ru not_active Application Discontinuation
- 2010-07-01 WO PCT/FR2010/051382 patent/WO2011001117A1/fr active Application Filing
- 2010-07-01 JP JP2012518122A patent/JP2012531523A/ja active Pending
- 2010-07-01 CN CN2010800300792A patent/CN102471860A/zh active Pending
- 2010-07-01 CA CA2766493A patent/CA2766493A1/fr not_active Abandoned
- 2010-07-01 BR BRPI1014009A patent/BRPI1014009A2/pt not_active IP Right Cessation
- 2010-07-01 EP EP10742020A patent/EP2449146A1/fr not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2507729A1 (fr) * | 1981-06-12 | 1982-12-17 | Snecma | Joint susceptible d'etre use par abrasion et son procede de realisation |
WO1997018341A1 (fr) * | 1995-11-13 | 1997-05-22 | The University Of Connecticut | Produits nanostructures pour pulverisation a chaud |
US6071628A (en) * | 1999-03-31 | 2000-06-06 | Lockheed Martin Energy Systems, Inc. | Thermal barrier coating for alloy systems |
US20040137259A1 (en) * | 2003-01-09 | 2004-07-15 | Pabla Surinder Singh | High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same |
Also Published As
Publication number | Publication date |
---|---|
BRPI1014009A2 (pt) | 2016-04-12 |
CA2766493A1 (fr) | 2011-01-06 |
EP2449146A1 (fr) | 2012-05-09 |
FR2947568A1 (fr) | 2011-01-07 |
US20120107110A1 (en) | 2012-05-03 |
JP2012531523A (ja) | 2012-12-10 |
CN102471860A (zh) | 2012-05-23 |
RU2012103463A (ru) | 2013-08-10 |
FR2947568B1 (fr) | 2011-07-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2011001117A1 (fr) | Revêtement de protection thermique pour une pièce de turbomachine et son procédé de réalisation | |
CA2844240C (fr) | Procede de realisation d'un renfort de protection du bord d'attaque d'une pale | |
CA2917068C (fr) | Procede de preparation a la depose d'un revetement metallique par projection thermique sur un substrat | |
CA2196744C (fr) | Revetement de barriere thermique a sous-couche amelioree et pieces revetues par une telle barriere thermique | |
US6887587B2 (en) | Reflective coatings to reduce radiation heat transfer | |
BE897012A (fr) | Bandage externe etanche a l'air revetu de matiere ceramique pour les moteurs a turbine a gaz | |
FR2883574A1 (fr) | "procede de depot par projection thermique d'un revetement anti-usure" | |
WO2003006710A1 (fr) | Procede de reparation locale de pieces revetues d'une barriere thermique | |
CA3066848A1 (fr) | Piece de turbomachine revetue et procede de fabrication associe | |
FR2990442A1 (fr) | Alliage de zirconium permettant d'ameliorer la resistance a l'oxydation a tres haute temperature et son procede de fabrication. | |
CA2735981A1 (fr) | Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur | |
EP3071722B1 (fr) | Procédé intégré de frittage pour microfissuration et tenue à l'érosion des barrières thermiques | |
WO2012146864A1 (fr) | Pièce comportant un revêtement sur un substrat métallique en superalliaae, le revêtement comprenant une sous-couche métallique | |
FR2757879A1 (fr) | Procede de pulverisation a l'aide de l'arc electrique pour l'application d'un revetement metallique augmentant le transfert de la chaleur et piece ainsi obtenue | |
CA2508821A1 (fr) | Procede de fabrication ou de reparation d'un revetement sur un substrat metallique | |
US10513942B2 (en) | Fusible bond for gas turbine engine coating system | |
FR3129678A1 (fr) | Piece pour une turbomachine comportant un revêtement de barriere thermique en geopolymere | |
EP3963183A1 (fr) | Procede de revetement d'une piece de turbomachine d'aeronef | |
JP2017179542A (ja) | 溶射用粉末およびこれを用いたアブレーダブル溶射皮膜の成膜方法 | |
FR3027959B1 (fr) | Protection anti-feu d'une piece en materiau composite d'une turbine a gaz | |
EP2371994A1 (fr) | Procédé pour réaliser un revêtement d'acier inoxydable sur une matrice en cuivre | |
FR3070400A1 (fr) | Couche protectrice resistante aux materiaux du type cmas | |
KR20070016943A (ko) | 세라믹 열 분사 코팅의 미세구조 제어 방법 | |
FR2739631A1 (fr) | Revetement de surface anticorrosion de type mcraly, procede de depot d'un tel revetement, aube monocristalline de turbine a gaz pourvue d'un tel revetement | |
FR2465793A1 (fr) | Procede pour le depot de couches d'alliage sur des substrats metalliques a une temperature elevee |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 201080030079.2 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 10742020 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2010742020 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2766493 Country of ref document: CA |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13380952 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012518122 Country of ref document: JP |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012103463 Country of ref document: RU |
|
REG | Reference to national code |
Ref country code: BR Ref legal event code: B01A Ref document number: PI1014009 Country of ref document: BR |
|
ENP | Entry into the national phase |
Ref document number: PI1014009 Country of ref document: BR Kind code of ref document: A2 Effective date: 20111229 |