EP0605196A1 - Verfahren zum Aufbringen einer Wärmedämmschicht - Google Patents
Verfahren zum Aufbringen einer Wärmedämmschicht Download PDFInfo
- Publication number
- EP0605196A1 EP0605196A1 EP93310442A EP93310442A EP0605196A1 EP 0605196 A1 EP0605196 A1 EP 0605196A1 EP 93310442 A EP93310442 A EP 93310442A EP 93310442 A EP93310442 A EP 93310442A EP 0605196 A1 EP0605196 A1 EP 0605196A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- zirconia layer
- substrate
- bondcoat
- zirconia
- layer
- 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.)
- Withdrawn
Links
- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 19
- 238000000576 coating method Methods 0.000 title description 15
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims abstract description 72
- 238000000034 method Methods 0.000 claims abstract description 33
- 230000008569 process Effects 0.000 claims abstract description 32
- 239000000758 substrate Substances 0.000 claims abstract description 29
- 238000000151 deposition Methods 0.000 claims abstract description 16
- 229910052751 metal Inorganic materials 0.000 claims abstract description 5
- 239000002184 metal Substances 0.000 claims abstract description 5
- 239000007921 spray Substances 0.000 claims description 5
- 229910052759 nickel Inorganic materials 0.000 claims description 2
- 229910000601 superalloy Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 claims 1
- 239000000956 alloy Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 34
- 239000011248 coating agent Substances 0.000 description 10
- 230000008021 deposition Effects 0.000 description 8
- 238000005382 thermal cycling Methods 0.000 description 8
- 239000000919 ceramic Substances 0.000 description 6
- 229910002076 stabilized zirconia Inorganic materials 0.000 description 5
- 230000007704 transition Effects 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000000843 powder Substances 0.000 description 4
- 238000009718 spray deposition Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- CPLXHLVBOLITMK-UHFFFAOYSA-N Magnesium oxide Chemical compound [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000012159 carrier gas Substances 0.000 description 1
- CETPSERCERDGAM-UHFFFAOYSA-N ceric oxide Chemical compound O=[Ce]=O CETPSERCERDGAM-UHFFFAOYSA-N 0.000 description 1
- 229910000422 cerium(IV) oxide Inorganic materials 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000395 magnesium oxide Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 229940098458 powder spray Drugs 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- -1 where M is Co Substances 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- 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
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
-
- 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
-
- 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
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
- C23C4/11—Oxides
-
- 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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame spraying
-
- 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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
Definitions
- This invention relates to a process for providing a thermal barrier coating on industrial gas turbine components such as combustion liners and transition pieces.
- Thermal barriercoating (TBC) systems are widely used in high temperature applications to provide oxidation and thermal resistance protection to metallic substrates under high thermal gradient conditions.
- Conventional TBC's are applied by various powder spray deposition processes, and consist of an intermediate metallic bondcoat attached to the substrate and a topcoat of stabilized zirconia.
- the zirconia may be phase-stabilized with between 6 and 22 weight percent yttria, or alternatively, magnesia, ceria or similar oxides. These coatings typically exhibit an un- cracked but porous microstructure. This type of processing is done with minimal substrate preheat, and is limited to a maximum coating thickness of 25 to 30 mil.
- thermal cycling resistance is significantly reduced due to coating spallation via cracking and separation between the bondcoat and initial zirconia deposit at that interface.
- Control of the initial zirconia layers deposited via this process is critical to the thermal cycling resistance of this TBC. In part, control is achieved through process parameter optimization and per-pass powder injection rates which are generally lowerthan conventional processing. Hence, this coating has a higher thermal conductivity per unit thickness than the porous conventional coating described above, by as much as 30 to 50%. Therefore, this coating may have an effective thermal resistance only one-third that of its absolute thickness advantage.
- the objective of this invention is to provide a superior TBC coating through plasma spray deposition of an initial zirconia deposit with a columnar microstructure achieved with controlled substrate preheat.
- This first or inner layer promotes good adherence, and is followed by a smooth, in-process transition to conditions which favor deposition of a controlled porosity, highly thermal resistive zirconia outer layer.
- a more specific objective of this invention is to provide a cost-effective coating process for large surface area components such as industrial landbased gas turbine combustion liners and transition pieces, which typically require TBC coatings over 1500-2000 square inches of surface area.
- this two-layer zirconia TBC microstructure is that it maximizes thermal cycling resistance and thermal resistivity at an overall lower coating thickness. This will result in reduced manufacturing cycle time and cost. Further reductions in cycle time may be achieved through increases in powder deposition rates, particularly for the outer zirconia layer, since a porous structure may be easier to achieve and control in this manner.
- the coating process of this invention thus produces a thermally resistant surface layer comprised of two layers (transitioned through grading of porosity) of stabilized zirconia ceramic attached to an oxidation and corrosion resistant metallic bondcoat, which is itself metallurgically bonded to a metallic substrate.
- an air plasma spray process used to deposit the inner stabilized-zirconia layer is controlled to produce a dense, columnar microstructure which has lower thermal resistivity, but which is extremely well adhered to the metallic bondcoat and which also provides maximum thermal cycling resistance to the composite, multi-layered coating system.
- the outer stabilized zirconia layer is applied by the air plasma spray deposition process to produce a controlled microstructure containing minimal cracks and approximately 10 to 20% porosity, which enhances thermal resistivity of the layer.
- a process for applying a thermal barrier coating to a metallic substrate which comprises the steps of:
- the invention relates to a gas turbine component having a thermal barrier coating thereon, applied by the above described process.
- FIGURE 1 is a cross section of a metal substrate provided with a thermal barrier coating in accordance with a first exemplary embodiment of the invention.
- a schematic illustration of an exemplary embodiment of the invention is shown to include a metallic substrate material 10 with a bondcoat 12 metallurgically bonded thereto.
- the substrate 10 may be, for example, a large superalloy surface area component of an industrial gas turbine engine. More specifically, the substrate may be a combustion liner or a transition piece (connecting the combustion chamber to the turbine) or other large component which typically requires a thermal barrier coating over 1500-2000 square inches of surface area.
- the metallic bondcoat 12 may be applied by a variety of thermal spray processes including air or vacuum plasma, or High Velocity Oxy-Fuel (HVOF) deposition to a suitable thickness, and may comprise MCrAIY chemical compositions, where M is Co, Ni, Fe or combinations of these elements.
- one such bondcoat may comprise 10-30% weight Chromium, 3-13 wt.% aluminum, and 0.05 to 1.0wt.% yttrium or other rare earth elements, and the balance M.
- An inner stabilized zirconia deposit layer 14 is applied to the bondcoat 12 by an air plasma spray process.
- the process is controlled (by substrate preheat) to produce a dense (i.e., substantially zero porosity), columnar microstructure which has lower thermal resistivity, but which is extremely well adhered to the metallic bondcoat 12.
- graded layers transitioning from all metal to all non-metallic
- the substrate temperature is initially elevated to a temperature in excess of 600°F. and up to about 1200°F. or higher to provide the dense, columnar microstructure.
- the thickness of this inner layer 14 is preferably between about 2 and about 20 mil, but may be greater. This inner layer 14 provides maximum thermal cycling resistance to the composite, multi-layered coating system.
- the process is continued under conditions which favor the deposition of a controlled porosity, highly thermal resistive zirconia outer layer 16, having a thickness of between about 10 and about 45 mi
- the outer zirconia layer 16 is also applied by the air plasma spray deposition process to produce a controlled microstructure containing minimal cracks and approximately a 10 to 20% porosity, which enhances the thermal resistivity of the layer. This is achieved by permitting the substrate 10 to cool to a lower temperature, between ambient and up to about 600°F. As a result of the continuity of the process, a transition zone between the inner and outer layers is created which has a porosity of between 0 and about 10%.
- This two-layer zirconia TBC microstructure is that it maximizes thermal cycling resistance and thermal resistivity at a lower total coating thickness. This will result in reduced manufacturing cycle time and cost. Further reductions in cycle time may be achieved through increases in powder deposition rates, particularly for the outer zirconia layer, since a porous structure may be easier to achieve and control in this manner.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US99692092A | 1992-12-29 | 1992-12-29 | |
US996920 | 1992-12-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0605196A1 true EP0605196A1 (de) | 1994-07-06 |
Family
ID=25543430
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP93310442A Withdrawn EP0605196A1 (de) | 1992-12-29 | 1993-12-22 | Verfahren zum Aufbringen einer Wärmedämmschicht |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0605196A1 (de) |
JP (1) | JPH06235074A (de) |
KR (1) | KR940014878A (de) |
CA (1) | CA2110007A1 (de) |
NO (1) | NO934862L (de) |
Cited By (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0705911A1 (de) * | 1994-10-04 | 1996-04-10 | General Electric Company | Hochtemperatur-Schutzschicht |
GB2296503A (en) * | 1994-12-28 | 1996-07-03 | Gen Electric | Thrmal barrier coating having grooves for enhanced strain tolerance |
WO1996035826A1 (en) * | 1995-05-08 | 1996-11-14 | Alliedsignal Inc. | Porous thermal barrier coating |
EP0765951A2 (de) * | 1995-09-26 | 1997-04-02 | United Technologies Corporation | Verschleissfeste keramische Beschichtung |
GB2317400A (en) * | 1996-09-19 | 1998-03-25 | Toshiba Kk | Thermal barrier coating providing reaction sintering suppression |
EP0916635A2 (de) * | 1997-11-18 | 1999-05-19 | United Technologies Corporation | Keramische Ueberzuege mit mehrschichtiger Porositaet |
WO1999035306A2 (en) * | 1997-12-09 | 1999-07-15 | N.V. Interturbine | Thermal barrier coating ceramic structure |
WO2000009778A1 (en) * | 1998-08-11 | 2000-02-24 | Siemens Westinghouse Power Corporation | Multilayer thermal barrier coating systems |
US6287644B1 (en) | 1999-07-02 | 2001-09-11 | General Electric Company | Continuously-graded bond coat and method of manufacture |
EP1295964A3 (de) * | 2001-09-24 | 2004-01-14 | Siemens Westinghouse Power Corporation | Wärmesperrschicht mit Doppelmikrostruktur |
WO2004029330A1 (en) * | 2002-09-25 | 2004-04-08 | Volvo Aero Corporation | A thermal barrier coating and a method of applying such a coating |
EP1731630A2 (de) * | 2005-06-10 | 2006-12-13 | The General Electric Company | Wärmedammbeschichtung und Verfahren zur dessen Herstellung |
EP1780308A2 (de) * | 2005-10-27 | 2007-05-02 | The General Electric Company | Verfahren und Vorrichtung zum Herstellen eines Bauteils |
US7258934B2 (en) | 2002-09-25 | 2007-08-21 | Volvo Aero Corporation | Thermal barrier coating and a method of applying such a coating |
WO2007112783A1 (de) * | 2006-04-06 | 2007-10-11 | Siemens Aktiengesellschaft | Layered thermal barrier coating with a high porosity, and a component |
EP1852524A2 (de) * | 2006-05-01 | 2007-11-07 | The General Electric Company | Verfahren zum Herstellen Wärmedämmschichten mit verbesserten Wärmedämmungeigenschaften |
EP1889940A2 (de) | 2006-08-18 | 2008-02-20 | United Technologies Corporation | Wärmedämmende Beschichtung mit Plasmasprühaußenschicht |
WO2009097834A1 (de) | 2008-02-06 | 2009-08-13 | Forschungszentrum Jülich GmbH | Wärmedämmschichtsystem sowie verfahren zu seiner herstellung |
EP2196559A1 (de) | 2008-12-15 | 2010-06-16 | ALSTOM Technology Ltd | Wärmesperrenbeschichtungssystem, damit beschichtete Komponenten und Verfahren zum Auftragen eines Wärmesperrenbeschichtungssystems auf Komponenten |
EP2108715A3 (de) * | 2008-04-08 | 2010-12-08 | General Electric Company | Wärmesperrenbeschichtungssystem und Beschichtungsverfahren für eine Gasturbinenmotorummantelung |
EP2281924A1 (de) * | 2009-08-04 | 2011-02-09 | United Technologies Corporation | Strukturelle unterschiedliche Wärmedämmbeschichtungen |
RU2445199C2 (ru) * | 2010-03-25 | 2012-03-20 | Общество с ограниченной ответственностью "Производственное предприятие Турбинаспецсервис" | Способ упрочнения блока сопловых лопаток турбомашин из никелевых и кобальтовых сплавов |
WO2013107712A1 (de) * | 2012-01-16 | 2013-07-25 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Verfahren zur herstellung einer keramischen schicht auf einer aus einer ni-basislegierung gebildeten oberfläche |
CN101698364B (zh) * | 2009-11-03 | 2013-08-28 | 西安交通大学 | 一种热障涂层及其制备工艺 |
JP2014224325A (ja) * | 2014-08-26 | 2014-12-04 | 三菱重工業株式会社 | 機械部品のコーティング方法及び機械部品 |
US9023486B2 (en) | 2011-10-13 | 2015-05-05 | General Electric Company | Thermal barrier coating systems and processes therefor |
US9034479B2 (en) | 2011-10-13 | 2015-05-19 | General Electric Company | Thermal barrier coating systems and processes therefor |
DE102014222686A1 (de) * | 2014-11-06 | 2016-05-12 | Siemens Aktiengesellschaft | Doppellagige Wärmedämmschicht durch unterschiedliche Beschichtungsverfahren |
US10280765B2 (en) | 2013-11-11 | 2019-05-07 | United Technologies Corporation | Article with coated substrate |
RU2697758C1 (ru) * | 2019-01-14 | 2019-08-19 | федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" | Способ нанесения жаростойких покрытий y-мо-о из плазмы вакуумно-дугового разряда |
RU2702515C1 (ru) * | 2018-06-06 | 2019-10-08 | Общество с ограниченной ответственностью "Научно-производственное предприятие "Уралавиаспецтехнология" | Способ упрочняющей обработки детали из сплава на никелевой основе (варианты) |
CN113088859A (zh) * | 2021-03-30 | 2021-07-09 | 潍柴动力股份有限公司 | 复合涂层、活塞、发动机和车辆 |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE527179C2 (sv) * | 2003-12-05 | 2006-01-17 | Sandvik Intellectual Property | Tunnfilmssolcell eller tunnfilmsbatteri, innefattande en zirkoniumoxidbelagd bandprodukt av ferritiskt kromstål |
JP4645030B2 (ja) * | 2003-12-18 | 2011-03-09 | 株式会社日立製作所 | 遮熱被膜を有する耐熱部材 |
US7354663B2 (en) | 2004-04-02 | 2008-04-08 | Mitsubishi Heavy Industries, Ltd. | Thermal barrier coating, manufacturing method thereof, turbine part and gas turbine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4503130A (en) * | 1981-12-14 | 1985-03-05 | United Technologies Corporation | Prestressed ceramic coatings |
EP0183638A1 (de) * | 1984-11-28 | 1986-06-04 | United Technologies Corporation | Verfahren zum Aufbringen einer kontinuierlich abgestuften Metallkeramikschicht auf metallischen Substraten |
EP0185603A1 (de) * | 1984-11-28 | 1986-06-25 | United Technologies Corporation | Verbesserung der Lebensdauer von metallvulkanischen Turbinenabdichtungen |
US4613259A (en) * | 1984-11-28 | 1986-09-23 | United Technologies Corporation | Apparatus for controlling powder flow rate in a carrier gas |
EP0366924A2 (de) * | 1988-11-03 | 1990-05-09 | AlliedSignal Inc. | Keramischer Temperaturbarriere-Überzug mit einer Zwischenschicht aus Aluminiumoxid |
WO1992005298A1 (en) * | 1990-09-20 | 1992-04-02 | United Technologies Corporation | Columnar ceramic thermal barrier coating with improved adherence |
WO1993018199A1 (en) * | 1992-03-05 | 1993-09-16 | Rolls-Royce Plc | A coated article |
-
1993
- 1993-11-25 CA CA002110007A patent/CA2110007A1/en not_active Abandoned
- 1993-12-22 EP EP93310442A patent/EP0605196A1/de not_active Withdrawn
- 1993-12-24 JP JP5325561A patent/JPH06235074A/ja not_active Withdrawn
- 1993-12-28 KR KR1019930030354A patent/KR940014878A/ko not_active Application Discontinuation
- 1993-12-28 NO NO934862A patent/NO934862L/no unknown
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4503130A (en) * | 1981-12-14 | 1985-03-05 | United Technologies Corporation | Prestressed ceramic coatings |
EP0183638A1 (de) * | 1984-11-28 | 1986-06-04 | United Technologies Corporation | Verfahren zum Aufbringen einer kontinuierlich abgestuften Metallkeramikschicht auf metallischen Substraten |
EP0185603A1 (de) * | 1984-11-28 | 1986-06-25 | United Technologies Corporation | Verbesserung der Lebensdauer von metallvulkanischen Turbinenabdichtungen |
US4613259A (en) * | 1984-11-28 | 1986-09-23 | United Technologies Corporation | Apparatus for controlling powder flow rate in a carrier gas |
EP0366924A2 (de) * | 1988-11-03 | 1990-05-09 | AlliedSignal Inc. | Keramischer Temperaturbarriere-Überzug mit einer Zwischenschicht aus Aluminiumoxid |
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Also Published As
Publication number | Publication date |
---|---|
JPH06235074A (ja) | 1994-08-23 |
NO934862L (no) | 1994-06-30 |
CA2110007A1 (en) | 1994-06-30 |
NO934862D0 (no) | 1993-12-28 |
KR940014878A (ko) | 1994-07-19 |
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