EP0266299A2 - Revêtement de barrière thermique - Google Patents

Revêtement de barrière thermique Download PDF

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Publication number
EP0266299A2
EP0266299A2 EP87630212A EP87630212A EP0266299A2 EP 0266299 A2 EP0266299 A2 EP 0266299A2 EP 87630212 A EP87630212 A EP 87630212A EP 87630212 A EP87630212 A EP 87630212A EP 0266299 A2 EP0266299 A2 EP 0266299A2
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EP
European Patent Office
Prior art keywords
coating
bond coat
thermal barrier
ceramic
zirconia
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.)
Granted
Application number
EP87630212A
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German (de)
English (en)
Other versions
EP0266299A3 (en
EP0266299B1 (fr
Inventor
Raymond William Vine
Keith Douglas Sheffler
Charles Edward Bevan
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP0266299A2 publication Critical patent/EP0266299A2/fr
Publication of EP0266299A3 publication Critical patent/EP0266299A3/en
Application granted granted Critical
Publication of EP0266299B1 publication Critical patent/EP0266299B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • 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
    • 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
    • C23C4/04—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

Definitions

  • the present invention relates to plasma sprayed ceramic thermal barrier coatings used to protect substrates from elevated temperatures.
  • Gas turbine engines derive their thrust or other power output by the combustion of fuels. Since engine power and economy both improve with increased temperature, there has been a persistent trend in the gas turbine engine field toward increased engine operating temperatures. For many years this trend was accommodated by the development of improved materials. Whereas early gas turbine engines were based mainly on alloys derived from common steels, the modern gas turbine engine relies on nickel and cobalt base superalloys in many critical applications. It appears for the moment that property limits for metallic materials are being approached or perhaps have been reached, but the demand for increased temperature capability continues. While work is underway to develop ceramic turbine materials, this work is at a very preliminary stage and many difficulties must be overcome before ceramics play a structural role in gas turbine engines.
  • the currently favored ceramic constituent is zirconia, but because zirconia undergoes a phase transformation at about 1800°F, it is necessary to make additions to the zirconia to provide a stable or at least controlled microstructure at increasing temperature.
  • Patents which appear particularly pertinent to this subject area include U.S. Patent 4,055,705 which suggests a thermal barrier coating system using a NiCrAlY bond coat and a zirconia based ceramic coating which may contain, for example, 12% yttria for stabilization.
  • U.S. Patent 4,248,940 which shares a common assignee with the present application, describes a similar thermal barrier coating, but with emphasis on the type of thermal barrier coating in which the composition of the coating is graded from 100% metal at the bond coat to 100% ceramic at the outer surface.
  • This patent describes the use of MCrAlY bond coats, including NiCoCrAlY, and mentions the use of yttria stabilized zirconia.
  • Patent 4,328,285 describes a ceramic thermal barrier coating using a CoCrAlY or NiCrAlY bond coat with ceria stabilized zirconia.
  • U.S. Patent 4,335,190 describes a thermal barrier coating in which a NiCrAlY or CoCrAlY bond coat has a sputtered coating of yttria stabilized zirconia on which is plasma sprayed a further coating of yttria stabilized zirconia.
  • U.S. Patent 4,402,992 describes a method for applying a ceramic thermal barrier coating to hollow turbine hardware containing cooling holes without blockage of the holes.
  • the specifics of the coating mentioned are a NiCrAlY or a CoCrAly bond coat with yttria stabilized zirconia.
  • U.S. Patent 4,457,948 describes a method for producing a favorable crack pattern in a ceramic thermal barrier coating to enhance its durability.
  • the coating mentioned has a NiCrAlY bond coat and a fully yttria stabilized zirconia coating.
  • U.S. Patent 4,481,151 describes another ceramic thermal barrier coating in which the bond coat comprises NiCrAlY or CoCrAlY, but wherein the yttrium constituent may be replaced by ytterbium.
  • the ceramic constituent is partially yttria or ytterbium stabilized zirconia.
  • U.S. Patent 4,535,033 is a continuation-in-part application of the previously mentioned U.S. Patent 4,481,151 and deals with a ceramic thermal barrier coating in which zirconia is stabilized by ytterbia.
  • a ceramic thermal barrier coating having surprisingly enhanced durability relative to similar ceramic thermal barrier coatings known in the art.
  • a NiCoCrAlY bond coat is plasma sprayed, in air, on the surface of the substrate to be protected, after the substrate surface has been properly prepared.
  • the ceramic consists of yttria partially stabilized zirconia, containing about 7% yttria to provide the proper degree of stabilization, plasma sprayed in air on the previously applied NiCoCrAlY bond coat.
  • the resultant coating has surprisingly enhanced durability relative to similar thermal barrier coatings which employ other types of MCrAlY bond coats and ceramic top coats.
  • the use of 7% yttria stabilized zirconia permits the coating to be used at elevated temperatures compared to other thermal barrier coatings which have employed other zirconia stabilizers or other amounts of yttria.
  • the use of air plasma spraying as opposed to low pressure chamber plasma spraying eliminates substrate preheating and post spray heat treatment.
  • the invention is particularly pertinent to coating of sheet metal parts which are prone to distortion in heat treatment.
  • Figure 1 depicts the relative life of several different ceramic thermal barrier coatings in a very severe test performed at 2025°F.
  • the test comprised a six-minute thermal cycle in which the coated substrate (a sheet metal sample) was heated from about 200°F to about 2025°F in two minutes, held for two minutes at 2025°F and was then forced air cooled in two minutes back down to about 200°F.
  • This is a severe test employing conditions which are more demanding than those which would normally be encountered in a gas turbine engine.
  • the figure illustrates the time to failure in hours, the number of cycles is obtained by multiplying the number of hours by 10.
  • the left-most bar (A) on the chart is a coating which has been used commercially in gas turbine engines at temperatures up to about 1800°F.
  • This coating consists of zirconia (fully) stabilized with about 21% magnesia applied on a CoCrAlY (23%Cr, 13%Al, .65%Y bal Co) bond coat.
  • the left-most coating is a graded coating so that the CoCrAlY composition diminishes through the thickness of the coating from 100% at the bond coat to 0% at the outer coat at the outer surface.
  • the remaining coatings on the chart are non-graded two-layer coatings.
  • the graded coating (A) which displays the shortest life, failed in the graded portion of the coating as a consequence of oxidation of the finely divided metallic constituent which causes swelling of the coating and subsequent spallation.
  • This coating fails in an abnormally short time because of the nature of the coating failure and the severe test conditions, the coating has a normal maximum use temperature of about 1800°F.
  • the next bar (B) on the chart comprises the same ceramic constitutent, zirconia stabilized with 21% magnesia, but this is a two-layer coating in which a 100% ceramic layer is applied to a bond coat.
  • the bond coat is a simple alloy of nickel-22 weight percent aluminum.
  • the third bar (C) on the chart uses the same 21% magnesia stabilized zirconium on a NiCoCrAlY bond coat (nominal compsition 23%Co, 17%Cr, 12.5%Al, 0.45%Y bal Ni). This coating had both the bond coat and the ceramic layer deposited by plasma spraying in air. Interestingly enough, the third coating on the chart displays abou a 2x improvement in life over the previously mentioned 21% MgO stabilized zirconia coating on Ni-22%Al coating illustrating that the bond coat does affect coating performance.
  • All of the coatings based on 21% magnesia stabilized zirconia appear to fail as a result of destabilization of the ceramic over time by volatilization of the less stable magnesia material at elevated temperatures and/or the effects of microscopic thermal mechanical stresses/racheting with the ultimate formation of the monoclinic crystalline phase of zirconia at temperatures in excess of about 1900°F.
  • the monoclinic crystal phase is the non-thermal cyclable zirconia that is unstable in gas turbine applications.
  • the last two coatings described in the figure used zirconia partially stabilized with about 7% yttria, this type of stabilized zirconia does not undergo thermal degradation until temperatures in excess of about 2200°F are encountered.
  • the fourth bar (D) on the chart uses the 7% yttria partially stabilized zirconia on a NiCoCrAlY (23%Co, 17%Cr, 12.5%Al, 0.45%Y bal Ni) bond coat, but differs from the other coatings in that the metallic constituents were applied by low-pressure plasma spraying, spraying in a chamber in which the gas pressure was reduced to about 5 millimeters of mercury before spraying.
  • This type of low pressure plasma spraying has been shown in the past to provide substantially enhanced thermal barrier coatings containing less oxides and porosity in the metallic bond coating and having better integrity and adherence.
  • One feature of chamber spraying is that the substrate must be preheated to 1600°F-1800°F before spraying.
  • FIG. 2 is a schematic illustration of a gas turbine combustor.
  • plasma spraying metallic bond coating such as NiCoCrAlY, under reduced atmospheric pressures leads to the formation of a weak metallic substrate-metallic bond coating interface which requries a post high temperature heat treatment to form a metallurgical bond between the substrate and bond coat.
  • the heat treatment means that sheet metal constituents which are prone to warpage cannot receive this type of coating.
  • the final bar (E) on the chart illustrates the invention coating performance. It can be seen that the invention coating performance is fully equivalent to that of the best prior coating despite the fact that the invention coating is applied in air and does not receive any subsequent heat treatment.
  • the present invention derives some of its beneficial attributes from the use of the NiCoCrAlY bond coat. This appears to be the case despite the fact that failure occurs in the ceramic coating rather than at the interface between the bond coat and the ceramic coating.
  • the exact mechanism by which the use of a NiCoCrAlY bond coat benefits coating performance is not fully understood, but is undoubtedly related to the enhanced ductility of NiCoCrAlY coatings (as described in U.S. Patent 3,928,026) relative to the NiCrAlY and CoCrAlY bond coats which the art has generally favored up until now.
  • the ceramic constituent of the present invention namely, zirconia stabilized with 6% to 8% yttria
  • zirconia stabilized with 6% to 8% yttria is more durable than some of the zirconia coatings which the prior art has used which have been stabilized to different degrees by different additions.
  • This can be seen on the graph by the comparison between the magnesia stabilized zirconia and yttria stabilized zirconia, both of which were applied on a NiCoCrAlY bond coat.
  • Other testing indicates that, tested at 2000°F, 7% yttria stabilized zirconia is about twice as durable as 12% yttria stabilized zirconia and about 5x as durable as 20% yttria (fully) stabilized zirconia.
  • the present invention can be applied to superalloy substrates as follows. There is generally no limit on the substrate composition provided, of course, it has the requisite mechanical properties at the intended use temperature.
  • the substrate surface must be clean and properly prepared and this is most easily accomplished by grit blasting the surface to remove all oxide and other contaminants and to leave behind a slightly roughened surface of increased surface area to enhance bonding of the metallic bond coat to the substrate.
  • the bond coat is applied to the substrate by plasma spraying.
  • the plasma spray parameters are the same as those described below for the ceramic constituent.
  • the bond coat material is NiCoCrAlY having a composition falling within the following range 15-40%Co, 10-40%Cr, 6-15%Al, 0.7%Si, 0-2.0%Hf, 0.01-1.0%Y, bal essentially Ni and has a particle size which is preferably within the range -170+325 US std. sieve.
  • the bond coat preferably has a thickness of from 0.003-0.015 inches. There is no benefit to be obtained by any increase in bond coat thickness. Any bond coat thickness less than about 0.003 inch is risky because plasma sprayed coatings of thicknesses much less than about 0.003 inch tend to leave exposed substrate areas and the ceramic coating will not properly bond to the exposed substrate. This leads to early catasrophic coating failure by spallation.
  • the plasma spraying of the bond coat to the prepared substrate surface is preferably performed in a timely fashion and preferably no more than about two hours elapses to minimize the possibility of substrate surface contamination, for example, by oxidation.
  • the bond coat coated substrates are then adapted to receive a coating of zirconia stabilized with 5%-8% yttria.
  • the particle size to be sprayed is 60 micron (avg)
  • the power flow rate is 50 gm/min
  • the plasma spraying conditions are 35 volts and 800 amps using a mix of argon helium as a carrier gas in a Plasmadyne gun held about 3 inches from the surface and translated about 74 ft/min relative to the surface.
  • the application of the ceramic coating to the bond coated substrate is preferably performed within about two hours so as to minimize contamination and other problems.
EP87630212A 1986-10-30 1987-10-26 Revêtement de barrière thermique Expired - Lifetime EP0266299B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US925654 1978-07-17
US92565486A 1986-10-30 1986-10-30

Publications (3)

Publication Number Publication Date
EP0266299A2 true EP0266299A2 (fr) 1988-05-04
EP0266299A3 EP0266299A3 (en) 1989-05-31
EP0266299B1 EP0266299B1 (fr) 1992-05-13

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Application Number Title Priority Date Filing Date
EP87630212A Expired - Lifetime EP0266299B1 (fr) 1986-10-30 1987-10-26 Revêtement de barrière thermique

Country Status (8)

Country Link
EP (1) EP0266299B1 (fr)
JP (1) JP2826824B2 (fr)
AU (1) AU594521B2 (fr)
CA (1) CA1330638C (fr)
DE (2) DE3779045D1 (fr)
IL (1) IL84067A (fr)
MX (1) MX169998B (fr)
SG (1) SG76592G (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990002825A1 (fr) * 1988-09-06 1990-03-22 Battelle Memorial Institute Revetements en alliage metallique et procedes d'application
GB2226050A (en) * 1988-12-16 1990-06-20 United Technologies Corp Thin abradable ceramic air seal
WO1992005298A1 (fr) * 1990-09-20 1992-04-02 United Technologies Corporation Enduit en ceramique a structure colonnaire destine a servir de barriere thermique et avec adherence amelioree
GB2252567A (en) * 1991-02-11 1992-08-12 Inst Elektroswarki Patona Metal/ceramic protective coating for superalloy articles
EP0526670A1 (fr) * 1991-06-21 1993-02-10 Praxair S.T. Technology, Inc. Revêtements doubles pour substrats variés
FR2716237A1 (fr) * 1994-02-16 1995-08-18 United Technologies Corp Structure de revêtement pour confiner des matériaux fondus dans des moteurs à turbine à gaz.
WO1996012049A1 (fr) * 1994-10-14 1996-04-25 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
EP0816526A2 (fr) * 1996-06-27 1998-01-07 United Technologies Corporation Système de revêtement de barrière thermique isolant
EP0825271A1 (fr) * 1996-08-16 1998-02-25 ROLLS-ROYCE plc Article métallique ayant une couche d'arrêt thermique et méthode pour son application
WO2006025865A3 (fr) * 2004-03-02 2006-06-15 Honeywell Int Inc Revetements mcra1y modifies sur des bouts de pale de turbine a durabilite amelioree
EP1889940A3 (fr) * 2006-08-18 2008-06-25 United Technologies Corporation Revêtement de barrière thermique doté d'une couche supérieure à pulvérisation plasma
US10287899B2 (en) 2013-10-21 2019-05-14 United Technologies Corporation Ceramic attachment configuration and method for manufacturing same
CN113106374A (zh) * 2021-03-19 2021-07-13 航天材料及工艺研究所 一种耐高温高热流冲刷的复合涂层及其制备方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5320879A (en) * 1992-07-20 1994-06-14 Hughes Missile Systems Co. Method of forming coatings by plasma spraying magnetic-cerment dielectric composite particles
JP3939362B2 (ja) * 1997-10-30 2007-07-04 アルストム 高温保護コーティング
JP2009063072A (ja) * 2007-09-06 2009-03-26 Railway Technical Res Inst ブレーキディスクとその表面改質方法及びブレーキディスクの表面改質装置
JP2018162506A (ja) * 2017-03-27 2018-10-18 川崎重工業株式会社 高温部材及びその製造方法

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DE2740398A1 (de) * 1976-09-09 1978-03-16 Union Carbide Corp Zweifachueberzug fuer den schutz gegen thermische beanspruchungen und korrosion
WO1981001983A1 (fr) * 1980-01-07 1981-07-23 United Technologies Corp Revetements de barrieres thermiques en ceramique a grains en colonnes sur des substrats polis
GB2159838A (en) * 1984-06-08 1985-12-11 United Technologies Corp Surface strengthening of overlay coatings
EP0181087A1 (fr) * 1984-10-03 1986-05-14 Westinghouse Electric Corporation Aubes de turbine pour turbines à combustion

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CA1068178A (fr) * 1975-09-11 1979-12-18 United Technologies Corporation Couche thermofuge pour superalliage a base de nickel
DE2842848A1 (de) * 1977-10-17 1979-04-19 United Technologies Corp Ueberzogener gegenstand, insbesondere superlegierungsgasturbinenschaufel
US4269903A (en) * 1979-09-06 1981-05-26 General Motors Corporation Abradable ceramic seal and method of making same
GB2063305B (en) * 1979-10-15 1984-02-01 United Technologies Corp Carbon bearing mcraiy coatings coated articles and method for these coatings
SE8401757L (sv) * 1984-03-30 1985-10-01 Yngve Lindblom Metalloxidkeramiska ytskikt pa hog temperaturmaterial

Patent Citations (4)

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Publication number Priority date Publication date Assignee Title
DE2740398A1 (de) * 1976-09-09 1978-03-16 Union Carbide Corp Zweifachueberzug fuer den schutz gegen thermische beanspruchungen und korrosion
WO1981001983A1 (fr) * 1980-01-07 1981-07-23 United Technologies Corp Revetements de barrieres thermiques en ceramique a grains en colonnes sur des substrats polis
GB2159838A (en) * 1984-06-08 1985-12-11 United Technologies Corp Surface strengthening of overlay coatings
EP0181087A1 (fr) * 1984-10-03 1986-05-14 Westinghouse Electric Corporation Aubes de turbine pour turbines à combustion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
MATERIALS LETTERS, vol. 3, nos. 9/10, July 1985, pages 396-400, Elsevier Science Publishers B.V., Amsterdam, NL; R. SIVAKUMAR: "Phase stability and thermal shock resistance of plasma sprayed MgO.ZrO2 coatings" *

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990002825A1 (fr) * 1988-09-06 1990-03-22 Battelle Memorial Institute Revetements en alliage metallique et procedes d'application
GB2226050A (en) * 1988-12-16 1990-06-20 United Technologies Corp Thin abradable ceramic air seal
FR2640688A1 (fr) * 1988-12-16 1990-06-22 United Technologies Corp Dispositif d'etancheite pneumatique en ceramique, pouvant etre use par frottement, notamment pour turbomoteurs
GB2226050B (en) * 1988-12-16 1993-04-07 United Technologies Corp Thin abradable ceramic air seal
WO1992005298A1 (fr) * 1990-09-20 1992-04-02 United Technologies Corporation Enduit en ceramique a structure colonnaire destine a servir de barriere thermique et avec adherence amelioree
GB2252567A (en) * 1991-02-11 1992-08-12 Inst Elektroswarki Patona Metal/ceramic protective coating for superalloy articles
GB2252567B (en) * 1991-02-11 1994-09-14 Inst Elektroswarki Patona Metal/ceramic protective coating for superalloy articles
EP0526670A1 (fr) * 1991-06-21 1993-02-10 Praxair S.T. Technology, Inc. Revêtements doubles pour substrats variés
US5921751A (en) * 1994-02-16 1999-07-13 United Technologies Corporation Coating scheme to contain molten material during gas turbine engine fires
FR2716237A1 (fr) * 1994-02-16 1995-08-18 United Technologies Corp Structure de revêtement pour confiner des matériaux fondus dans des moteurs à turbine à gaz.
WO1995022635A1 (fr) * 1994-02-16 1995-08-24 Sohl, Charles, E. Systeme de revetements confinant les materiaux fondus en cas d'incendie
WO1996012049A1 (fr) * 1994-10-14 1996-04-25 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
US5993980A (en) * 1994-10-14 1999-11-30 Siemens Aktiengesellschaft Protective coating for protecting a component from corrosion, oxidation and excessive thermal stress, process for producing the coating and gas turbine component
EP0816526A3 (fr) * 1996-06-27 1998-01-28 United Technologies Corporation Système de revêtement de barrière thermique isolant
EP0816526A2 (fr) * 1996-06-27 1998-01-07 United Technologies Corporation Système de revêtement de barrière thermique isolant
EP0825271A1 (fr) * 1996-08-16 1998-02-25 ROLLS-ROYCE plc Article métallique ayant une couche d'arrêt thermique et méthode pour son application
US6025078A (en) * 1996-08-16 2000-02-15 Rolls-Royce Plc Metallic article having a thermal barrier coating and a method of application thereof
WO2006025865A3 (fr) * 2004-03-02 2006-06-15 Honeywell Int Inc Revetements mcra1y modifies sur des bouts de pale de turbine a durabilite amelioree
US7316850B2 (en) 2004-03-02 2008-01-08 Honeywell International Inc. Modified MCrAlY coatings on turbine blade tips with improved durability
EP1889940A3 (fr) * 2006-08-18 2008-06-25 United Technologies Corporation Revêtement de barrière thermique doté d'une couche supérieure à pulvérisation plasma
US7875370B2 (en) 2006-08-18 2011-01-25 United Technologies Corporation Thermal barrier coating with a plasma spray top layer
US10287899B2 (en) 2013-10-21 2019-05-14 United Technologies Corporation Ceramic attachment configuration and method for manufacturing same
CN113106374A (zh) * 2021-03-19 2021-07-13 航天材料及工艺研究所 一种耐高温高热流冲刷的复合涂层及其制备方法

Also Published As

Publication number Publication date
DE266299T1 (de) 1988-09-22
MX169998B (es) 1993-08-04
IL84067A0 (en) 1988-03-31
CA1330638C (fr) 1994-07-12
AU8050087A (en) 1988-05-05
SG76592G (en) 1992-10-02
JP2826824B2 (ja) 1998-11-18
IL84067A (en) 1992-03-29
EP0266299A3 (en) 1989-05-31
DE3779045D1 (de) 1992-06-17
AU594521B2 (en) 1990-03-08
EP0266299B1 (fr) 1992-05-13
JPS63118059A (ja) 1988-05-23

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