SG172522A1 - Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware - Google Patents
Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware Download PDFInfo
- Publication number
- SG172522A1 SG172522A1 SG2010067361A SG2010067361A SG172522A1 SG 172522 A1 SG172522 A1 SG 172522A1 SG 2010067361 A SG2010067361 A SG 2010067361A SG 2010067361 A SG2010067361 A SG 2010067361A SG 172522 A1 SG172522 A1 SG 172522A1
- Authority
- SG
- Singapore
- Prior art keywords
- process according
- powder
- thermal barrier
- step comprises
- substrate
- Prior art date
Links
- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 26
- 239000007921 spray Substances 0.000 claims abstract description 30
- 239000000843 powder Substances 0.000 claims abstract description 29
- CMIHHWBVHJVIGI-UHFFFAOYSA-N gadolinium(iii) oxide Chemical compound [O-2].[O-2].[O-2].[Gd+3].[Gd+3] CMIHHWBVHJVIGI-UHFFFAOYSA-N 0.000 claims abstract description 26
- 238000000034 method Methods 0.000 claims abstract description 24
- 239000000758 substrate Substances 0.000 claims abstract description 18
- 230000008569 process Effects 0.000 claims abstract description 17
- 229910002076 stabilized zirconia Inorganic materials 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims description 40
- 239000011248 coating agent Substances 0.000 claims description 27
- 239000007789 gas Substances 0.000 claims description 25
- 239000000919 ceramic Substances 0.000 claims description 16
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 12
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 12
- 239000011229 interlayer Substances 0.000 claims description 9
- 239000010410 layer Substances 0.000 claims description 8
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 6
- 239000001257 hydrogen Substances 0.000 claims description 4
- 229910052739 hydrogen Inorganic materials 0.000 claims description 4
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 claims description 4
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 claims description 4
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 2
- 238000000151 deposition Methods 0.000 claims 7
- 125000004435 hydrogen atom Chemical class [H]* 0.000 claims 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims 1
- 229910052719 titanium Inorganic materials 0.000 claims 1
- 239000010936 titanium Substances 0.000 claims 1
- 230000004888 barrier function Effects 0.000 abstract description 2
- 239000002245 particle Substances 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 3
- 239000012159 carrier gas Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000007792 addition Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 150000002431 hydrogen Chemical class 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 239000003381 stabilizer Substances 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
- 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
-
- 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
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
PLASMA APPLICATION OF THERMAL BARRIER COATINGS WITH REDUCEDTHERMAL CONDUCTIVITY ON COMBUSTOR HARDWAREA process for forming a thermal barrier coatingcomprises the steps of providing a substrate, providing agadolinia stabilized zirconia powder, and forming a thermalbarrier coating having at least one of a porosity in arange of from 5 to 20% and a dense segmented structure onsaid substrate by supplying the gadolinia stabilized powderto a spray gun and using an air plasma spray technique.FIGURE 1
Description
PA 0003042-US (07-421)
PLASMA APPLICATION OF THERMAL BARRIER COATINGS WITH REDUCED
THERMAL CONDUCTIVITY ON COMBUSTOR HARDWARE
STATEMENT OF GOVERNMENT INTEREST
[0001] The Government of the United States of America may have rights in the present invention as a result of
Contract No. N00019-02-C-3003 awarded by the Department of the Air Force.
[0002] The present disclosure is directed to thermal barrier coatings with reduced thermal conductivity on combustor hardware, which coatings are applied using a plasma.
[0003] Ceramic thermal barrier coatings (TBCs) have been used for many years to extend the life of combustors and high turbine stationary and rotating parts in gas turbine engines. TBCs typically consist of a metallic bond coat and a ceramic top coat applied to a nickel or cobalt based alloy substrate which forms the part being coated. The coatings are typically applied to thicknesses between 5 and 40 mils and can provide up to 300 degrees F temperature reduction to the substrate metal. This temperature reduction translates into improved part durability, higher turbine operating temperatures, and improved turbine efficiency. Typically, the ceramic layer is a 7 wt% yttria stabilized zirconia applied by air plasma spray (APS). New low thermal conductivity coatings have been developed which can provide improved part performance.
PA 0003042-US (07-421)
[0004] One coating which has been used in the past for TBCs is gadolinia stabilized zirconia based thermal barrier coatings.
[0005] It is desirable to form a thermal barrier coating which has a relatively low thermal conductivity.
[0006] As described herein, there is provided a process for forming a thermal barrier coating comprises the steps of providing a substrate, providing a gadolinia stabilized zirconia powder, and forming a thermal barrier coating having at least one of a porosity in a range of from 5 to 20% and a dense segmented structure on said substrate by supplying the gadolinia stabilized powder to a spray gun and using an air plasma spray technique.
[0007] Other details of the thermal barrier coatings applied using an air plasma spray technique, as well as advantages attendant thereto, are set forth in the following detailed description and the accompanying drawings.
[0008] Figs. 1 and 2 are photomicrographs showing a low conductivity cracked coating formed using a F4 Plasma Spray
Gun, which coating includes a ceramic layer consisting of wt% Gd;03 and 70 wt% ZrO, with a air plasma sprayed
MCrAlY bond coat);
PA 0003042-US (07-421)
Fig. 3 is a photomicrograph showing a coating system which includes a metallic bond coat, a ceramic bond coat, and a ceramic top coat formed by a low conductivity coating in which the metallic bond coat is an air plasma-sprayed
MCrAlY bond coat, the ceramic bond coat is a 7 YSZ interlayer, and the ceramic top coat is a 30 wt% Gd,03 — 70 wt% ZrO, top layer.
[0009] As described herein, a plasma spray technique is utilized to apply a gadolinia stabilized zirconia based thermal barrier coatings on combustor hardware such as panels, chambers, heat shields, transition ducts, augmenters, etc. The plasma spray technique may be an air plasma spray technique in which a desirable coating microstructure is produced.
[0010] In air plasma spray, the coating material is propelled toward the surface of the substrate to be coated.
The coating material is in the form of a spray. The powder or powders forming the coating material are fed along with carrier gases into a high temperature plasma gas stream.
In the plasma gas stream, the powder particles are melted and accelerated toward the surface of the substrate to be coated. The powder particles are fed to a spray gun at a desired feed rate. A carrier gas flow such as an argon gas flow is used to maintain the powder under pressure and facilitate powder feed. The carrier gas flow rate is described in standard cubic feet per hour. Standard conditions may be defined as about room temperature and about one atmosphere of pressure.
PA 0003042-US (07-421)
[0011] The gases that make up the plasma gas stream comprise a primary gas (such as an argon gas or nitrogen gas) and a secondary gas (such as a hydrogen gas). Helium gas may be used as the secondary gas if desired.
[0012] The process includes the step of translating a spray gun so that the nozzle is positioned at a desired distance from the surface to be coated. The substrate to be coated may be passed through the spray of powder particles emanating from the spray gun.
[0013] The spray gun to be used to form the coatings disclosed herein may include both internal feed and external feed spray guns. Suitable spray guns include the
Plasmadyne SG-100, Sulzer Metco 3MB, 7 MB, or 9 MB, and the
Plasma Technic F-4. The desired coating may also be applied with the high deposition rate Sulzer Metco Triplex gun and/or the Progressive HE100 gun.
[0014] Zirconia based powder with the additions of rare earth stabilizers, such as gadolinia, have been found to yield coatings having lower thermal conductivities than many current thermal barrier cocatings. A useful zirconia based powder is one which consists of optionally 3.0 to 14 wts of at least one of yttria and titania, 15 to 70 wt% gadolinia, and the balance zirconia. The yttria and/or titania, and the gadolinia, improve the thermal barrier coating’s ceramic mechanical properties, while still achieving a reduced thermal conductivity ceramic coating.
Coatings formed using these powders are shown in Figs. 1 and 2.
PA 0003042-US (07-421)
[0015] If desired, one could apply to a substrate, a coating which has a metallic bond coat, such as a MCrAlY type coating where M is Ni or Co, a ceramic interlayer, such as a 7 YSZ coating, deposited on the metallic bond coat and a ceramic top coat comprising from 15 to 70 wt gadolinia and the balance zirconia. Such a coating system is illustrated in Fig. 3.
[0016] The air plasma spray parameters may be adjusted to produce a coating with a desired level of porosity or a coating with a dense segmented structure. For porous coatings, the coating may have a thermal conductivity which ranges from 3.0 to 10 BTU in/hr ft? F. For segmented coatings, the coating may have a thermal conductivity which ranges from 5.0 to 12.5 BTU in/hr ft? F.
[0017] A useful coating has a porosity in the range of 5.0 to 20%. The desired porosity for the ccating may be obtained by altering the gun power settings, the standoff distance, the powder particle size, and the powder feed rate.
[0018] Segmented coatings provide the coating with strain tolerance during operation which leads to increased spallation life. For combustor panel applications, a coating system having a segmented microstructure topcoat layer with a ceramic interlayer provides a useful coating system.
[0019] If desired, one can obtain a coating with a dense segmented structure by increasing the power settings and shorten the standoff distance. One can do this by using
PA 0003042-US (07-421) the settings set forth in columns 6 — 8 of U.S. patent no. 5,879,753, which patent is incorporated by reference herein.
[0020] For example, a useful coating may be applied using the Plasmadyne SG-100 spray gun using an amperage range of 350 to 825 amps, a voltage of 35 to 50 volts applied to a cathode and anode within the plasma-gun body, an argon primary gas flow of 75 — 105 SCFH, a hydrogen secondary gas flow of 1.0 to 10 SCFH or a helium gas flow of 45 —- 75
SCFH, a powder gas flow exiting the gun of 4.0 to 20 SCFH, a powder feed rate to the gun of 10 to 40 grams/min., and a gun distance from the surface being coated of from 3.0 to 5.0 inches. Alternatively, the coatings may be applied with the Plasma Technic F-4 spray gun using an amperage range of from 500 to 700 amps, a voltage of 55 to 65 volts, an argon primary gas flow of 65 to 90 SCFH, a hydrogen secondary gas flow of 8 — 22 SCFH, a powder gas flow from the spray gun of 6 to 12 SCFH, a powder feed rate to the spray gun of 35 — 55 grams/min. and a gun distance from the surface being coated of from 4.0 to 7.0 inches.
[0021] One of the benefits of the process of the present invention is the application of a thermal barrier coating having lower thermal conductivity than many current coatings resulting in longer ccoating life, performance improvements, and cost savings.
[0022] Burner rig testing of a low conductivity coating formed in accordance with the present disclosure with a ceramic interlayer was found to be 1.6 to 1.9 times better in spallation resistance than without the interlayer. In
PA 0003042-US (07-421) addition, low conductivity coatings with an interlayer are 1.3 to 1.5 times better in spallation than current coatings.
[0023] In accordance with the foregoing disclosure, there has been provided a plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware. While the plasma application of thermal barrier coatings has been described in the context of specific embodiments thereof, other unforeseeable alternatives, modifications, and variations may become apparent to those skilled in the art having read the foregoing description.
Accordingly, it is intended to embrace those alternatives, modifications, and variations as fall within the broad scope of the appended claims.
Claims (13)
1. A process for forming a thermal barrier coating comprising the steps of: providing a substrate; providing a gadolinia stabilized zirconia powder; and forming a thermal barrier coating having at least one of a porosity in a range of from 5 to 20% and a dense segmented structure on said substrate by supplying the gadolinia stabilized powder to a spray gun and using an air plasma spray technique.
2. The process according to claim 1, wherein said substrate providing step comprises providing a combustor component.
3. The process according to claim 1, wherein said substrate providing step comprises providing one of a combustor panel, a combustor chamber, a combustor heat shield, a combustor transition duct, and a combustor augmentor.
4. The process according to claim 1, wherein said powder providing step comprises providing a powder consisting of optionally from 3.0 to 14 wt% of at least one of yttria and titania, from 15 to 70 wt% gadolinia, and the balance zirconia.
PA 0003042-US (07-421)
5. The process according to claim 1, wherein said powder providing step comprises providing a powder consisting of from 3.0 to 14 wt% of at least one of yttria and titanium, from 15 to 70 wt% gadolinia, and the balance zirconia.
6. The process according to claim 1, wherein said thermal barrier coating forming step comprises using an amperage range of 350 to 825 amps, a voltage of 35 to 50 volts, an argon primary gas flow of 75 to 105 SCFH, at least one of a hydrogen secondary gas flow of 1.0 to 10 SCFH and a helium secondary gas flow of 45 to 75 SCFH, a powder gas flow exiting a spray gun of 4.0 to 20 SCFH, a powder feed rate to the spray gun of 10 to 40 grams/min., and a gun distance from a surface of the substrate being coated of from 3.0 to
5.0 inches.
7. The process according to claim 1, wherein said thermal barrier coating forming step comprises using an amperage range of from 500 to 700 amps, a voltage of 55 to 65 volts, an argon primary gas flow of 65 to 90 SCFH, a hydrogen secondary gas flow of 8 to 22 SCFH, a powder gas flow from a spray gun of 6 to 12 SCFH, a powder feed rate to the spray gun of 35 to 55 grams/min. and a gun distance from a surface of a substrate being coated of from 4.0 to 7.0 inches.
8. The process according to claim 1, further comprising depositing a ceramic interlayer on said substrate prior to said thermal barrier coating step.
PA 0003042-US (07-421)
9. The process according to claim 8, wherein said ceramic interlayer depositing step comprises depositing a layer of
7.0 wt% yttria stabilized zirconia.
10. The process according to claim 8, further comprising depositing a bondcoat layer on said substrate prior to said ceramic interlayer depositing step.
11. The process according to claim 10, wherein said bondcoat layer depositing step comprises depositing a metallic bondcoat layer.
12. The process according to claim 1, wherein said thermal barrier coating forming step comprises forming a segmented coating having a thermal conductivity in the range of from
5.0 to 12.5 BTU in/hr ft” F.
13. The process according to claim 1, wherein said thermal barrier coating forming step comprises forming a porous coating having a thermal conductivity in the range of from
3.0 to 10 BTU in/hr ft” F.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/638,051 US20110143043A1 (en) | 2009-12-15 | 2009-12-15 | Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SG172522A1 true SG172522A1 (en) | 2011-07-28 |
Family
ID=43218439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SG2010067361A SG172522A1 (en) | 2009-12-15 | 2010-09-16 | Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20110143043A1 (en) |
| EP (1) | EP2336381B1 (en) |
| SG (1) | SG172522A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9249514B2 (en) * | 2012-08-31 | 2016-02-02 | General Electric Company | Article formed by plasma spray |
| US20140255613A1 (en) * | 2013-03-05 | 2014-09-11 | Pratt & Whitney Canada Corp. | Low energy plasma coating |
| EP2971240B1 (en) * | 2013-03-14 | 2018-11-21 | United Technologies Corporation | Hybrid thermal barrier coating and process of making the same |
| US10287899B2 (en) | 2013-10-21 | 2019-05-14 | United Technologies Corporation | Ceramic attachment configuration and method for manufacturing same |
| US10322976B2 (en) | 2013-12-06 | 2019-06-18 | United Technologies Corporation | Calcium-magnesium alumino-silicate (CMAS) resistant thermal barrier coatings, systems, and methods of production thereof |
| WO2015127052A1 (en) | 2014-02-21 | 2015-08-27 | Oerlikon Metco (Us) Inc. | Thermal barrier coatings and processes |
| US9927126B2 (en) | 2015-06-10 | 2018-03-27 | General Electric Company | Prefilming air blast (PAB) pilot for low emissions combustors |
| US10184665B2 (en) | 2015-06-10 | 2019-01-22 | General Electric Company | Prefilming air blast (PAB) pilot having annular splitter surrounding a pilot fuel injector |
| CN115536386B (en) * | 2022-11-04 | 2024-04-02 | 华东理工大学 | High fracture toughness, CMAS corrosion resistance and ultra-high temperature sintering thermal barrier coating material, preparation and application thereof, and thermal barrier coating |
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| US4577902A (en) * | 1983-02-08 | 1986-03-25 | Leggett & Platt, Incorporated | Rocker recliner and away-from-the-wall recliner chairs |
| US4707025A (en) * | 1986-06-26 | 1987-11-17 | Parma Corporation | Rocker recliner |
| AU3323193A (en) * | 1991-12-24 | 1993-07-28 | Detroit Diesel Corporation | Thermal barrier coating and method of depositing the same on combustion chamber component surfaces |
| US6102656A (en) * | 1995-09-26 | 2000-08-15 | United Technologies Corporation | Segmented abradable ceramic coating |
| US6177200B1 (en) * | 1996-12-12 | 2001-01-23 | United Technologies Corporation | Thermal barrier coating systems and materials |
| US5879753A (en) * | 1997-12-19 | 1999-03-09 | United Technologies Corporation | Thermal spray coating process for rotor blade tips using a rotatable holding fixture |
| US6165600A (en) * | 1998-10-06 | 2000-12-26 | General Electric Company | Gas turbine engine component having a thermal-insulating multilayer ceramic coating |
| CA2306941A1 (en) * | 2000-04-27 | 2001-10-27 | Standard Aero Ltd. | Multilayer thermal barrier coatings |
| US7001859B2 (en) * | 2001-01-22 | 2006-02-21 | Ohio Aerospace Institute | Low conductivity and sintering-resistant thermal barrier coatings |
| US6586115B2 (en) * | 2001-04-12 | 2003-07-01 | General Electric Company | Yttria-stabilized zirconia with reduced thermal conductivity |
| DE20106560U1 (en) * | 2001-04-14 | 2002-08-29 | Dewert Antriebs Systemtech | Seat-recliner armchair adjustable by motor |
| US6703137B2 (en) * | 2001-08-02 | 2004-03-09 | Siemens Westinghouse Power Corporation | Segmented thermal barrier coating and method of manufacturing the same |
| GB0121732D0 (en) * | 2001-09-10 | 2001-10-31 | Pellerin Rene | Tilt adjustment assembly for reclining chair |
| US6634706B2 (en) * | 2001-09-27 | 2003-10-21 | Lane Furniture Industries, Inc. | Rocking recliner chair |
| US20030138658A1 (en) * | 2002-01-22 | 2003-07-24 | Taylor Thomas Alan | Multilayer thermal barrier coating |
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| US7258934B2 (en) * | 2002-09-25 | 2007-08-21 | Volvo Aero Corporation | Thermal barrier coating and a method of applying such a coating |
| US6945599B2 (en) * | 2003-09-30 | 2005-09-20 | Lane Furniture Industries, Inc. | Rocker recliner mechanism |
| GB0325358D0 (en) * | 2003-10-30 | 2003-12-03 | Peter Cook Internat Plc | Powered furniture |
| US6869703B1 (en) * | 2003-12-30 | 2005-03-22 | General Electric Company | Thermal barrier coatings with improved impact and erosion resistance |
| US6916561B1 (en) * | 2003-12-30 | 2005-07-12 | General Electric Company | Thermal barrier coatings with lower porosity for improved impact and erosion resistance |
| US7326470B2 (en) * | 2004-04-28 | 2008-02-05 | United Technologies Corporation | Thin 7YSZ, interfacial layer as cyclic durability (spallation) life enhancement for low conductivity TBCs |
| US7927722B2 (en) * | 2004-07-30 | 2011-04-19 | United Technologies Corporation | Dispersion strengthened rare earth stabilized zirconia |
| JP2006104577A (en) * | 2004-10-04 | 2006-04-20 | United Technol Corp <Utc> | Segmented gadolinia zirconia coating film, method for forming the same, segmented ceramic coating system and coated film component |
| US7021711B1 (en) * | 2004-11-04 | 2006-04-04 | Ultra-Mek, Inc. | Rocking-reclining seating unit with motion lock |
| CA2529781C (en) * | 2004-12-14 | 2010-10-12 | Mitsubishi Heavy Industries, Ltd. | Thermal barrier coating material, thermal barrier member, and member coated with thermal barrier and method for manufacturing the same |
| US7504157B2 (en) * | 2005-11-02 | 2009-03-17 | H.C. Starck Gmbh | Strontium titanium oxides and abradable coatings made therefrom |
| US7455913B2 (en) * | 2006-01-10 | 2008-11-25 | United Technologies Corporation | Thermal barrier coating compositions, processes for applying same and articles coated with same |
| US7875370B2 (en) * | 2006-08-18 | 2011-01-25 | United Technologies Corporation | Thermal barrier coating with a plasma spray top layer |
| US20080044663A1 (en) * | 2006-08-18 | 2008-02-21 | United Technologies Corporation | Dual layer ceramic coating |
-
2009
- 2009-12-15 US US12/638,051 patent/US20110143043A1/en not_active Abandoned
-
2010
- 2010-09-16 SG SG2010067361A patent/SG172522A1/en unknown
- 2010-09-30 EP EP10251689.5A patent/EP2336381B1/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| EP2336381B1 (en) | 2014-06-04 |
| US20110143043A1 (en) | 2011-06-16 |
| EP2336381A1 (en) | 2011-06-22 |
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