EP1398394A1 - Procédé de projection à froid pour fabriquer une couche de MCrAlX - Google Patents

Procédé de projection à froid pour fabriquer une couche de MCrAlX Download PDF

Info

Publication number
EP1398394A1
EP1398394A1 EP20030018287 EP03018287A EP1398394A1 EP 1398394 A1 EP1398394 A1 EP 1398394A1 EP 20030018287 EP20030018287 EP 20030018287 EP 03018287 A EP03018287 A EP 03018287A EP 1398394 A1 EP1398394 A1 EP 1398394A1
Authority
EP
European Patent Office
Prior art keywords
coating
substrate
particles
mcraix
gas stream
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Withdrawn
Application number
EP20030018287
Other languages
German (de)
English (en)
Inventor
Bruce M. Warnes
Russel J. Ruprecht, Jr.
Jack E. Cockerill
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.)
Howmet Corp
Original Assignee
Howmet Research 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 Howmet Research Corp filed Critical Howmet Research Corp
Publication of EP1398394A1 publication Critical patent/EP1398394A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B7/00—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas
    • B05B7/14—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas designed for spraying particulate materials
    • B05B7/1481—Spray pistols or apparatus for discharging particulate material
    • B05B7/1486—Spray pistols or apparatus for discharging particulate material for spraying particulate material in dry state
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface

Definitions

  • the present invention relates to a method for cold spraying MCrAIX alloy particles to form an overlay coating on a substrate.
  • MCrAIY overlay coatings where M is selected from one or more of Ni, Co and Fe, are applied to hardware, such as turbine components including turbine airfoils (e.g. blades and vanes) and shroud bodies of gas turbine engines, as a hot corrosion resistant and oxidation resistant coating.
  • Shroud bodies collectively form an annular sealing surface against which the turbine blade tips seal as they rotate as is well known.
  • MCrAIY overlay coatings have been applied by various techniques. For example, initially MCrAIY overlay coatings were applied using electron beam physical vapor deposition (EB-PVD). Thermal spraying techniques were developed to overcome certain disadvantages associated with the EB-PVD deposition process. Such thermal spraying techniques have included low pressure plasma spraying (LPPS), high velocity oxygen fuel spraying (HVOF), and air plasma spray which are widely used today.
  • LPPS low pressure plasma spraying
  • HVOF high velocity oxygen fuel spraying
  • air plasma spray which are widely used today.
  • MCrAIY alloy powder particles are heated in a high temperature plasma jet to above their melting point and propelled towards a substrate inside a vacuum chamber which maintains the spray environment at some low pressure below 1 atmosphere, and typically below 50 torr. Powder particle heat and velocity are achieved using a plasma torch designed or modified for operation under reduced ambient pressure.
  • the high velocity oxygen fuel coating method is a supersonic flame spray process that transfers thermal and kinetic energy to powder particles of the MCrAlY alloy powder particles using a combustion torch, rather than a plasma.
  • the particles are heated by the torch to above their melting point before they impact the substrate.
  • the method typically is performed in a spray environment at local atmospheric pressure, and the torch may be manipulated manually or using automated systems.
  • the component being coated is typically fixtured and attached to a table or drive system.
  • Thermal spraying processes such as the LSSP, HVOF and air plasma spray processes for applying MCrAIY overlay coatings suffer from certain disadvantages.
  • the thermal sprayed coating applied on hollow airfoil substrates typically covers surface-film cooling holes on the exterior surface of the airfoil substrate. If airfoils with advanced cooling schemes are coated by thermal spraying, the cooling holes must be opened after coating such as by, for example, pumping hot acid through the hollow airfoil substrate so that the acid exits through the covered cooling holes in a manner to corrode away the coating overlying the cooling holes.
  • the MCrAIY coating can be drilled through to expose the underlying cooling holes. The acid pumping and drilling operations are expensive and time consuming.
  • Such thermal spraying processes are disadvantageous in that the as-sprayed MCrAIY overlay coating exhibits a rough surface (e.g. greater than 300 micro-inch) such that it is necessary to perform expensive and time consuming shot peening and polishing operations on the as-sprayed coating to achieve an airfoil surface finish required by engine manufacturers (e.g. less than 75 micro-inch surface finish).
  • thermal spraying processes can be inefficient from the standpoint that deposit efficiency (percentage of the initial powder sprayed and deposited on the substrate) is low.
  • deposit efficiency percentage of the initial powder sprayed and deposited on the substrate
  • the deposition efficiency of HVOF process typically is only 30% to 35%. Since thermal spray powders can cost form $40.00 to $60.00 per pound, the low deposition efficiency represents a significant waste of expensive raw material.
  • the surface of the airfoil substrate must be rough (e.g. greater than 200 micro-inch surface roughness) to create a good mechanical bond between the coating and the substrate.
  • the necessary surface roughness of the substrate is achieved by an aggressive grit blasting operation (e.g. 55-65 psi with 16 grit alumina particles).
  • the grit particles can become embedded in the substrate surface and require a subsequent grit particle removal operation as described, for example, in US Patent 6 194 026.
  • thermal spray processes require significant heating of the substrate prior to coating deposition.
  • the process can require heating the substrate to 1400 to 1800 degrees F over a four minute time period followed by reverse arc cleaning over a four minute time period before coating deposition.
  • the precoating steps of heating and reverse arc cleaning can consume over 50% of the total time to coat the substrate.
  • the present invention provides a method of gas-dynamic spraying of particles comprising MCrAIX alloy, wherein M is selected from one or more of Ni, Co, and Fe and wherein X is an element other than M, Cr, and Al and preferably is selected from one or more of Y, a rare earth element, and a reactive element, including the steps of providing a supersonic gas jet stream having solid-phase MCrAIX alloy particles entrained therein and having a gas stream temperature to maintain the particles below their melting temperature and impinging the solid-phase particles in the supersonic gas stream against a nickel or cobalt base superalloy substrate to deposit an MCrAIX overlay coating thereon.
  • the particles comprising MCrAlX alloy preferably have a mean particle size (diameter) of about 20 microns and below, and more preferably of 10 microns and below, to provide substantially increased deposition efficiency and substantially reduced as-sprayed coating surface roughness.
  • the as-sprayed MCrAIX overlay coating is deposited on an unheated superalloy substrate residing in ambient air.
  • the as-sprayed MCrAIX overlay coating deposited on the superalloy substrate subsequently is heat treated to form a diffusion bond between the coating and the substrate.
  • An embodiment of the present invention relates to gas-dynamic spraying of particles comprising an MCrAIX alloy on a nickel or cobalt base superalloy substrate to deposit an MCrAIX alloy overlay coating thereon.
  • the MCrAIX alloys are hot corrosion resistant and oxidation resistant protective alloys applied as an overlay coating or layer onto turbine components such as airfoils, which include turbine blades and vanes, and shroud blocks as well other turbine components, and non-turbine engine components.
  • overlay coating is meant that the as-sprayed coating is not bonded to the substrate by a metallurgical diffusion bond or zone between the coating and substrate, but is adherent to the substrate by virtue of a mechanical bond to the substrate.
  • the M alloying element is selected from the group consisting of Ni, Co, and Fe and combinations thereof.
  • the X alloying element comprises an element other than M, Cr, and AI.
  • X preferably is selected from the group consisting of Y, a rare earth element such as Ce and/or La, and a reactive element such as Si, Hf, Zr, an alkali element such as K, and/or alkaline earth element such as Ca and/or Mg and other reactive elements (where reactive element refers to an element that forms stable sulfides, borides, phosphides, or other compounds with species such as S, B, P, etc. detrimental to oxidation resistance of the coating), and combinations of two or more of Y a rare earth element, and reactive element.
  • the MCrAIX coating typically consists essentially of, in weight %, about 14% to about 35% Cr, about 4% to about 30% Al, about 0.1% to about 3% X where X is selected from one or more of the above-described elements, and balance essentially M where M is iron and/or nickel and/or cobalt.
  • the present invention involves providing a supersonic gas stream having solid-phase MCrAIX particles entrained therein and having a gas stream temperature low enough to maintain the MCrAIX particles below their melting temperature and impinging the solid-phase particles in the supersonic gas jet stream against a nickel or cobalt base superalloy substrate to deposit the overlay MCrAIX coating thereon.
  • Apparatus for practicing the invention is shown in Figure 1 as including a source 10 of compressed carrier gas, which preferably comprises helium, although the invention can be practiced using other carrier gases such as air, nitrogen, and mixtures thereof.
  • the compressed carrier gas is typically at a pressure in the range of 100 to 600 psig.
  • a high pressure cylinder of helium at 400 psi can be used to practice the method of the invention.
  • the compressed carrier gas is supplied to a gas preheater 12 and to a powder particle feeder 14 via respective conduits 13 and 15.
  • Respective valves 16 and 18 are provided in conduits 13 and 15 for the purpose of gas shut-off.
  • the gas pre-heater 12 functions to preheat the carrier gas (e.g. He) to a temperature above ambient but well below the melting temperature of the MCrAIX particles being sprayed so that the MCrAIX particles are not melted and remain in the solid phase in the supersonic stream.
  • the gas pre-heater can comprise a conventional electrical resistance gas heater or any other type of heater capable of heating the compressed gas such as a gas pre-heater like that described in US Patent 5 302 414, whose teachings are incorporated herein by reference.
  • the powder particle feeder 14 functions to meter via conduit 20 the MCrAIX particles at a selected powder flow rate to a mixing chamber 22 while the compressed, pre-heated gas enters the chamber 22 via conduit 24 from the gas pre-heater 12.
  • the powder particle feeder 14 can comprise a drum-type feeder like that described in US Patent 5 302 414, whose teachings are incorporated herein by reference.
  • the invention can be practiced using other powder particle feeders such as including, but not limited to those that are based on a rotating feeder wheel or feeder screw or a fluidized feeder bed.
  • the mixture of compressed carrier gas and MCrAIX powder particles is flowed through a supersonic (convergent-divergent) nozzle 30 having a gas distribution baffle 30a, convergent (sonic) section 30b, and divergent (supersonic) section 30c.
  • a supersonic (convergent-divergent) nozzle 30 having a gas distribution baffle 30a, convergent (sonic) section 30b, and divergent (supersonic) section 30c.
  • the supersonic gas jet stream impinges on the unheated substrate S to deposit the MCrAIX overlay coating thereon.
  • the nozzle 30 and the substrate S are disposed in ambient air with the substrate at ambient air temperature; i.e. no pre-heating of substrate S is required.
  • Substrate specimens comprising a nickel base superalloy known as Rene'41 were sprayed pursuant to the invention to deposit a CoNiCrAlY overlay coating thereon.
  • the substrate Rene'41 nickel base superalloy has a nominal composition of, in weight %, 19% Cr-11% Co-10% Mo-5% Fe-0.09% C-1.5% Al- 3% Ti-balance Ni.
  • the substrate specimens comprised a plate shape having dimensions 2 inches wide by 4 inches long by 1/8 inch thick and were pre-treated prior to spraying by grit blasting using 220 grit aluminum oxide particles at 40 to 60 psi air pressure.
  • CoNiCrAlY powder of different particles sizes were used and are available as CO-210-6 and CO-210-23 from Praxair Surface Technologies.
  • the powder produced a coating analyzed after spraying and heat treatment as having a nominal composition of, in weight %, 31.4% Ni-20.5% Cr-9% AI-0.9% Y-balance Co.
  • Two powder different particle sizes were sprayed in different spray trials; namely, particles having a mean particle diameter of 6.4 microns (CO-210-6) and 14.8 microns (CO-210-23).
  • Mean particle diameter means that half of the particles had a diameter greater than the given size and the other half had a diameter less than the given size.
  • the length, I, of nozzle section 30c was 100 mm.
  • Helium at 400 psi and pre-heated to 400 degrees C by pre-heater 12, Figure 1, was used as the compressed carrier gas.
  • the nozzle section 30a was spaced a standoff distance of 25 mm from the substrate specimen, which was at ambient air temperature.
  • the drum-type feeder described above similar to that in construction and operation to that described in US Patent 5 302 414 was used to provide a feed rate of powder of 3 to 5 kg/hr.
  • the CoNiCrAlY overlay coatings were deposited to a thickness of 0.004 to 0.008 inch on the unheated substrate specimens.
  • the invention is not limited to the above nozzle rectangular configuration and spray parameters since a circular cross-section or other cross-sectional shape of nozzle 30 as well as other nozzle dimensions and other spray parameters can be used in practice of the invention.
  • the deposition efficiency of the spray processes using the two different powder particle sizes set forth above were determined by spraying a known weight of the powder at each plate specimen of known initial plate specimen weight, determining the final weight of the plate specimen after spraying, and calculating the weight increase of each plate specimen due to the powder applied thereon, and determining a percentage by dividing the weight increase of each specimen by the initial weight of powder sprayed for that specimen and multiplying by 100.
  • the deposition efficiencies are shown in Figure 2. As can be seen in Figure 2, the deposition efficiency for CoNiCrAlY powder increased as the powder particle size deceased. A maximum deposition efficiency of 55% was achieved for the mean particle diameter of 6.4 microns. This represents a substantial improvement (e.g.
  • the surface finish of the as-sprayed CoNiCrAIY coatings was measured with a profilometer both parallel and perpendicular to the spray direction. Multiple measurements (6 in each direction) were averaged, and the average surface finish was plotted as function of powder particle size as shown in Figure 3.
  • Figure 3 reveals that the surface finish improved as the mean particle diameter decreased.
  • a surface finish of 243 micro-inches was achieved for the CoNiCrAIY coating using the mean particle diameter of 6.4 microns.
  • the surface finish of the coatings was better than or equal to that obtained using the LPPS, HVOF and air plasma spray processes, which produce coating surface finishes greater than 300 micro-inches. Since gas turbine engine manufacturers require a surface finish of less than 100 micro-inches, the improved surface finish achieved by the invention will require less post-coat processing than a similar MCrAIX coating sprayed by LPPS, HVOF and air plasma spray processes.
  • typical post-coating processing for a typical MCrAIX overlay coating applied by LPPS involves firstly a diffusion heat treatment (e.g. 2-5 hours at 1080 degrees C) to form a diffusion bond between the coating and the substrate and to form equilibrium phases in the coating alloy. Secondly, the overlay coating is shot peened for 400 seconds to achieve about a 125 micro-inches surface finish. Thirdly, the heat-treated and peened coating must be vibratory polished for 3 hours to reduce the surface finish to less than 75 micro-inches using conventional media bowl polishing procedures.
  • a diffusion heat treatment e.g. 2-5 hours at 1080 degrees C
  • the overlay coating is shot peened for 400 seconds to achieve about a 125 micro-inches surface finish.
  • the heat-treated and peened coating must be vibratory polished for 3 hours to reduce the surface finish to less than 75 micro-inches using conventional media bowl polishing procedures.
  • the coated substrate also was diffusion heat treated (e.g. 2-5 hours at 1080 degrees C) to form a diffusion bond between the coating and the substrate and to form equilibrium phases in the coating alloy.
  • diffusion heat treated e.g. 2-5 hours at 1080 degrees C
  • only 210 seconds of shot peening was needed to reduce the surface finish of the coating to 79 micro-inches, representing a 47% reduction in peening time as compared to a typical MCrAIY coating applied by LPPS.
  • a final surface finish of 69 micro-inches was obtained on the CoNiCrAIY coating with just 30 minutes media bowl polishing time as compared to 3 hours for an MCrAIY coating applied by LPPS, representing an 84% reduction in polishing time as compared to a typical MCrAIY coating applied by LPPS.
  • the above-described spraying trials demonstrate that substrate surface preparation using less aggressive grit blasting can be used and still obtain acceptable green bond strength (prior to diffusion heat treatment) of the MCrAIX overlay coatings.
  • the invention can be practiced without any substrate pre-heating prior to spray deposition so as to eliminate the need for a grit-removal operation, pre-heat operation, and reverse arc cleaning as required by the LPPS process.
EP20030018287 2002-08-13 2003-08-12 Procédé de projection à froid pour fabriquer une couche de MCrAlX Withdrawn EP1398394A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US21794802A 2002-08-13 2002-08-13
US217948 2002-08-13

Publications (1)

Publication Number Publication Date
EP1398394A1 true EP1398394A1 (fr) 2004-03-17

Family

ID=31714464

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20030018287 Withdrawn EP1398394A1 (fr) 2002-08-13 2003-08-12 Procédé de projection à froid pour fabriquer une couche de MCrAlX

Country Status (3)

Country Link
EP (1) EP1398394A1 (fr)
JP (1) JP2004076157A (fr)
CA (1) CA2433613A1 (fr)

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005093128A1 (fr) * 2004-03-22 2005-10-06 Honeywell International, Inc. Reparation par l'application d'un aerosol gasodynamique a froid sur des composants d'un moteur a turbine a gaz
EP1630253A1 (fr) * 2004-08-23 2006-03-01 Delphi Technologies, Inc. Procédé pour la fabrication en ligne continue de revêtements rapides par pulvérisation cinétique
WO2006034778A1 (fr) * 2004-09-24 2006-04-06 Linde Aktiengesellschaft Procede de pulverisation par gaz froid et pistolet pulverisateur a gaz froid caracterises par un temps de sejour prolonge de la poudre dans le jet de gaz
EP1672175A1 (fr) * 2004-12-14 2006-06-21 Honeywell International Inc. Procédé d'application sur des éléments de turbines de revêtements du type MCrAlY résistant aux dommages de l'environment.
WO2006075994A2 (fr) * 2004-04-06 2006-07-20 Honeywell International Inc. Pulverisation gazodynamique a froid d'un alliage resistant a l'usure sur des pales de turbine
EP1705266A2 (fr) * 2005-03-23 2006-09-27 United Technologies Corporation Dépôt d'une couche de liaison sur des organes de machine par pulverisation à froid
EP1834699A1 (fr) * 2005-01-07 2007-09-19 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) Dispositif de buse de pulverisation thermique et equipement de pulverisation thermique
WO2007110134A1 (fr) * 2006-03-24 2007-10-04 Linde Aktiengesellschaft Pistolet de projection à gaz froid
EP1921181A1 (fr) * 2006-10-27 2008-05-14 United Technologies Corporation Bandes métalliques poreuses à pulvérisation froide
WO2008140588A1 (fr) * 2006-11-30 2008-11-20 Honeywell International Inc. Procédé de fabrication d'un système de revêtement isolant thermique et résistant à l'environnement sur un composant
EP1995344A1 (fr) * 2007-05-25 2008-11-26 InnCoa GmbH Revêtement doté d'une gestion ultérieure par diffusion
WO2008154465A1 (fr) * 2007-06-11 2008-12-18 Honeywell International Inc. Procédé de formation de couches d'accrochage destinées à des revêtements de barrière thermique sur des composants de moteur de turbine
EP1579921A3 (fr) * 2004-03-24 2009-02-18 Delphi Technologies, Inc. Buse de pulvérisation cinétique
DE102007048484A1 (de) * 2007-10-09 2009-04-16 Man Turbo Ag Heißgasgeführte Komponente einer Strömungsmaschine
WO2009103268A1 (fr) * 2008-02-20 2009-08-27 Mtu Aero Engines Gmbh Procédé d'application d'un revêtement sur des pièces
US20100092662A1 (en) * 2006-11-14 2010-04-15 Siemens Aktiengesellschaft Rough Bonding Agent Layers by Means of HS-PVD or Cold Spray
US8113413B2 (en) 2006-12-13 2012-02-14 H.C. Starck, Inc. Protective metal-clad structures
US8197894B2 (en) 2007-05-04 2012-06-12 H.C. Starck Gmbh Methods of forming sputtering targets
US8226741B2 (en) 2006-10-03 2012-07-24 H.C. Starck, Inc. Process for preparing metal powders having low oxygen content, powders so-produced and uses thereof
US8246903B2 (en) 2008-09-09 2012-08-21 H.C. Starck Inc. Dynamic dehydriding of refractory metal powders
US20130183453A1 (en) * 2012-01-17 2013-07-18 Peter Heinrich Method and device for thermal spraying
US8499825B2 (en) 2007-07-19 2013-08-06 Toyota Jidosha Kabushiki Kaisha Method for manufacturing heat transfer member, power module, vehicle inverter, and vehicle
US8703233B2 (en) 2011-09-29 2014-04-22 H.C. Starck Inc. Methods of manufacturing large-area sputtering targets by cold spray
US8708659B2 (en) 2010-09-24 2014-04-29 United Technologies Corporation Turbine engine component having protective coating
EP2725120A1 (fr) * 2012-10-24 2014-04-30 Hitachi Ltd. Composants à haute température avec des revêtements de barrière thermique pour turbine à gaz
DE102012023210A1 (de) 2012-11-28 2014-05-28 Wieland-Werke Ag Kupferband zur Herstellung von Leiterplatten
WO2014082695A1 (fr) 2012-11-28 2014-06-05 Wieland-Werke Ag Pièces électro-conductrices à adhérence améliorée et procédé de fabrication desdites pièces
US8783584B2 (en) 2007-06-25 2014-07-22 Plasma Giken Co., Ltd. Nozzle for cold spray system and cold spray device using the nozzle for cold spray system
US8802191B2 (en) 2005-05-05 2014-08-12 H. C. Starck Gmbh Method for coating a substrate surface and coated product
US20140254740A1 (en) * 2012-12-28 2014-09-11 Global Nuclear Fuel - Americas, Llc Fuel rods with wear-inhibiting coatings and methods of making the same
WO2014178937A1 (fr) * 2013-05-03 2014-11-06 United Technologies Corporation Réchauffeur de gaz portatif haute température et haute pression
ITCO20130018A1 (it) * 2013-05-17 2014-11-18 Nuovo Pignone Srl Metodo per il trattamento di un componente per prevenire l'erosione di tale componente
CN114471987A (zh) * 2022-03-02 2022-05-13 季华实验室 一种冷喷涂喷枪

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3784404B1 (ja) 2004-11-24 2006-06-14 株式会社神戸製鋼所 溶射ノズル装置およびそれを用いた溶射装置
JP4736022B2 (ja) * 2005-01-28 2011-07-27 Ｔｏｔｏ株式会社 複合構造物形成システム及び形成方法
CN100413997C (zh) * 2005-04-29 2008-08-27 中国科学院金属研究所 一种高耐蚀性的镍基完全非晶合金涂层的制备方法
AU2007317650B2 (en) * 2006-11-07 2012-06-14 H.C. Starck Surface Technology and Ceramic Powders GmbH Method for coating a substrate and coated product
JP4586823B2 (ja) 2007-06-21 2010-11-24 トヨタ自動車株式会社 成膜方法、伝熱部材、パワーモジュール、車両用インバータ、及び車両
JP2010229426A (ja) * 2007-08-07 2010-10-14 Showa Denko Kk 熱交換器用部材の製造方法および熱交換器用部材
JP5130991B2 (ja) * 2008-03-27 2013-01-30 株式会社Ｉｈｉ コールドスプレー方法、コールドスプレー装置
JP2010144224A (ja) * 2008-12-19 2010-07-01 Honda Motor Co Ltd 金属皮膜の改質処理方法及びアルミ基合金積層体
JP5500676B2 (ja) * 2009-12-24 2014-05-21 株式会社日立製作所 耐熱合金皮膜の形成方法、それに用いる複合粉末
JP5573505B2 (ja) * 2010-09-01 2014-08-20 株式会社Ｉｈｉ コールドスプレー装置用エジェクタノズル及びコールドスプレー装置
US20130164558A1 (en) * 2011-12-27 2013-06-27 United Technologies Corporation Oxidation Resistant Coating with Substrate Compatibility
CN104024465A (zh) * 2011-12-29 2014-09-03 通用电气公司 压力掩蔽系统及其使用方法
JP6321407B2 (ja) * 2014-03-07 2018-05-09 日本発條株式会社 成膜装置
JP2019112723A (ja) * 2019-03-13 2019-07-11 ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． 構成部品の浸食を防止するために当該構成部品を処理するための方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993454A (en) * 1975-06-23 1976-11-23 United Technologies Corporation Alumina forming coatings containing hafnium for high temperature applications
US4687678A (en) * 1984-03-30 1987-08-18 Lindblom Yngve S Process for preparing high temperature materials
EP0484533A1 (fr) * 1990-05-19 1992-05-13 Anatoly Nikiforovich Papyrin Procede et dispositif de revetement
US6365222B1 (en) * 2000-10-27 2002-04-02 Siemens Westinghouse Power Corporation Abradable coating applied with cold spray technique
US20020066770A1 (en) * 2000-12-05 2002-06-06 Siemens Westinghouse Power Corporation Cold spray repair process

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993454A (en) * 1975-06-23 1976-11-23 United Technologies Corporation Alumina forming coatings containing hafnium for high temperature applications
US4687678A (en) * 1984-03-30 1987-08-18 Lindblom Yngve S Process for preparing high temperature materials
EP0484533A1 (fr) * 1990-05-19 1992-05-13 Anatoly Nikiforovich Papyrin Procede et dispositif de revetement
US6365222B1 (en) * 2000-10-27 2002-04-02 Siemens Westinghouse Power Corporation Abradable coating applied with cold spray technique
US20020066770A1 (en) * 2000-12-05 2002-06-06 Siemens Westinghouse Power Corporation Cold spray repair process

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PAPYRIN, A. (KTECH): "Cold spray technology.", ADVANCED MATERIALS & PROCESSES (2001) 159, (9), 49-51, NUMERICAL DATA, GRAPHS ISSN: 0882-7958, XP009024286 *

Cited By (57)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005093128A1 (fr) * 2004-03-22 2005-10-06 Honeywell International, Inc. Reparation par l'application d'un aerosol gasodynamique a froid sur des composants d'un moteur a turbine a gaz
EP1579921A3 (fr) * 2004-03-24 2009-02-18 Delphi Technologies, Inc. Buse de pulvérisation cinétique
WO2006075994A3 (fr) * 2004-04-06 2006-09-28 Honeywell Int Inc Pulverisation gazodynamique a froid d'un alliage resistant a l'usure sur des pales de turbine
WO2006075994A2 (fr) * 2004-04-06 2006-07-20 Honeywell International Inc. Pulverisation gazodynamique a froid d'un alliage resistant a l'usure sur des pales de turbine
EP1630253A1 (fr) * 2004-08-23 2006-03-01 Delphi Technologies, Inc. Procédé pour la fabrication en ligne continue de revêtements rapides par pulvérisation cinétique
WO2006034778A1 (fr) * 2004-09-24 2006-04-06 Linde Aktiengesellschaft Procede de pulverisation par gaz froid et pistolet pulverisateur a gaz froid caracterises par un temps de sejour prolonge de la poudre dans le jet de gaz
EP1672175A1 (fr) * 2004-12-14 2006-06-21 Honeywell International Inc. Procédé d'application sur des éléments de turbines de revêtements du type MCrAlY résistant aux dommages de l'environment.
US7378132B2 (en) 2004-12-14 2008-05-27 Honeywell International, Inc. Method for applying environmental-resistant MCrAlY coatings on gas turbine components
EP1834699A1 (fr) * 2005-01-07 2007-09-19 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) Dispositif de buse de pulverisation thermique et equipement de pulverisation thermique
EP1834699A4 (fr) * 2005-01-07 2008-06-25 Kobe Steel Ltd Dispositif de buse de pulverisation thermique et equipement de pulverisation thermique
EP1705266A3 (fr) * 2005-03-23 2007-01-17 United Technologies Corporation Dépôt d'une couche de liaison sur des organes de machine par pulverisation à froid
EP1705266A2 (fr) * 2005-03-23 2006-09-27 United Technologies Corporation Dépôt d'une couche de liaison sur des organes de machine par pulverisation à froid
US8802191B2 (en) 2005-05-05 2014-08-12 H. C. Starck Gmbh Method for coating a substrate surface and coated product
WO2007110134A1 (fr) * 2006-03-24 2007-10-04 Linde Aktiengesellschaft Pistolet de projection à gaz froid
CN101410551B (zh) * 2006-03-24 2011-10-19 林德股份公司 冷气喷涂枪
US8715386B2 (en) 2006-10-03 2014-05-06 H.C. Starck Inc. Process for preparing metal powders having low oxygen content, powders so-produced and uses thereof
US8226741B2 (en) 2006-10-03 2012-07-24 H.C. Starck, Inc. Process for preparing metal powders having low oxygen content, powders so-produced and uses thereof
EP1921181A1 (fr) * 2006-10-27 2008-05-14 United Technologies Corporation Bandes métalliques poreuses à pulvérisation froide
US8192792B2 (en) 2006-10-27 2012-06-05 United Technologies Corporation Cold sprayed porous metal seals
US20100092662A1 (en) * 2006-11-14 2010-04-15 Siemens Aktiengesellschaft Rough Bonding Agent Layers by Means of HS-PVD or Cold Spray
WO2008140588A1 (fr) * 2006-11-30 2008-11-20 Honeywell International Inc. Procédé de fabrication d'un système de revêtement isolant thermique et résistant à l'environnement sur un composant
US8448840B2 (en) 2006-12-13 2013-05-28 H.C. Starck Inc. Methods of joining metallic protective layers
US8113413B2 (en) 2006-12-13 2012-02-14 H.C. Starck, Inc. Protective metal-clad structures
US8777090B2 (en) 2006-12-13 2014-07-15 H.C. Starck Inc. Methods of joining metallic protective layers
US9095932B2 (en) 2006-12-13 2015-08-04 H.C. Starck Inc. Methods of joining metallic protective layers
US8883250B2 (en) 2007-05-04 2014-11-11 H.C. Starck Inc. Methods of rejuvenating sputtering targets
US9783882B2 (en) 2007-05-04 2017-10-10 H.C. Starck Inc. Fine grained, non banded, refractory metal sputtering targets with a uniformly random crystallographic orientation, method for making such film, and thin film based devices and products made therefrom
US8491959B2 (en) 2007-05-04 2013-07-23 H.C. Starck Inc. Methods of rejuvenating sputtering targets
US8197894B2 (en) 2007-05-04 2012-06-12 H.C. Starck Gmbh Methods of forming sputtering targets
EP1995344A1 (fr) * 2007-05-25 2008-11-26 InnCoa GmbH Revêtement doté d'une gestion ultérieure par diffusion
WO2008154465A1 (fr) * 2007-06-11 2008-12-18 Honeywell International Inc. Procédé de formation de couches d'accrochage destinées à des revêtements de barrière thermique sur des composants de moteur de turbine
US8783584B2 (en) 2007-06-25 2014-07-22 Plasma Giken Co., Ltd. Nozzle for cold spray system and cold spray device using the nozzle for cold spray system
US8499825B2 (en) 2007-07-19 2013-08-06 Toyota Jidosha Kabushiki Kaisha Method for manufacturing heat transfer member, power module, vehicle inverter, and vehicle
US9926629B2 (en) 2007-10-09 2018-03-27 Man Diesel & Turbo Se Hot gas-guided component of a turbomachine
DE102007048484A1 (de) * 2007-10-09 2009-04-16 Man Turbo Ag Heißgasgeführte Komponente einer Strömungsmaschine
WO2009103268A1 (fr) * 2008-02-20 2009-08-27 Mtu Aero Engines Gmbh Procédé d'application d'un revêtement sur des pièces
US8470396B2 (en) 2008-09-09 2013-06-25 H.C. Starck Inc. Dynamic dehydriding of refractory metal powders
US8246903B2 (en) 2008-09-09 2012-08-21 H.C. Starck Inc. Dynamic dehydriding of refractory metal powders
US8961867B2 (en) 2008-09-09 2015-02-24 H.C. Starck Inc. Dynamic dehydriding of refractory metal powders
US8708659B2 (en) 2010-09-24 2014-04-29 United Technologies Corporation Turbine engine component having protective coating
US9412568B2 (en) 2011-09-29 2016-08-09 H.C. Starck, Inc. Large-area sputtering targets
US8734896B2 (en) 2011-09-29 2014-05-27 H.C. Starck Inc. Methods of manufacturing high-strength large-area sputtering targets
US9293306B2 (en) 2011-09-29 2016-03-22 H.C. Starck, Inc. Methods of manufacturing large-area sputtering targets using interlocking joints
US9120183B2 (en) 2011-09-29 2015-09-01 H.C. Starck Inc. Methods of manufacturing large-area sputtering targets
US9108273B2 (en) 2011-09-29 2015-08-18 H.C. Starck Inc. Methods of manufacturing large-area sputtering targets using interlocking joints
US8703233B2 (en) 2011-09-29 2014-04-22 H.C. Starck Inc. Methods of manufacturing large-area sputtering targets by cold spray
US20130183453A1 (en) * 2012-01-17 2013-07-18 Peter Heinrich Method and device for thermal spraying
EP2725120A1 (fr) * 2012-10-24 2014-04-30 Hitachi Ltd. Composants à haute température avec des revêtements de barrière thermique pour turbine à gaz
WO2014082695A1 (fr) 2012-11-28 2014-06-05 Wieland-Werke Ag Pièces électro-conductrices à adhérence améliorée et procédé de fabrication desdites pièces
DE102012023210A1 (de) 2012-11-28 2014-05-28 Wieland-Werke Ag Kupferband zur Herstellung von Leiterplatten
US20140254740A1 (en) * 2012-12-28 2014-09-11 Global Nuclear Fuel - Americas, Llc Fuel rods with wear-inhibiting coatings and methods of making the same
US9911511B2 (en) * 2012-12-28 2018-03-06 Global Nuclear Fuel—Americas, LLC Fuel rods with wear-inhibiting coatings and methods of making the same
WO2014178937A1 (fr) * 2013-05-03 2014-11-06 United Technologies Corporation Réchauffeur de gaz portatif haute température et haute pression
WO2014184363A1 (fr) * 2013-05-17 2014-11-20 Nuovo Pignone Srl Procédé de traitement d'un composant pour prévenir l'érosion d'un tel composant
ITCO20130018A1 (it) * 2013-05-17 2014-11-18 Nuovo Pignone Srl Metodo per il trattamento di un componente per prevenire l'erosione di tale componente
CN105339525A (zh) * 2013-05-17 2016-02-17 诺沃皮尼奥内股份有限公司 用于处理构件来防止这样的构件的腐蚀的方法
CN114471987A (zh) * 2022-03-02 2022-05-13 季华实验室 一种冷喷涂喷枪

Also Published As

Publication number Publication date
JP2004076157A (ja) 2004-03-11
CA2433613A1 (fr) 2004-02-13

Similar Documents

Publication Publication Date Title
EP1398394A1 (fr) Procédé de projection à froid pour fabriquer une couche de MCrAlX
US5866271A (en) Method for bonding thermal barrier coatings to superalloy substrates
EP1674595B1 (fr) Reparation structural par pulversation a froid d'aluminium
US5277936A (en) Oxide containing MCrAlY-type overlay coatings
EP1829984B1 (fr) Procédé de fabrication d'un revêtement de barrière thermique à forte densité
US20110048017A1 (en) Method of depositing protective coatings on turbine combustion components
US6403165B1 (en) Method for modifying stoichiometric NiAl coatings applied to turbine airfoils by thermal processes
EP1939316A1 (fr) Système de revêtement de barrière thermique et procédé pour le revêtement d'un composant
US20060216428A1 (en) Applying bond coat to engine components using cold spray
US7601431B2 (en) Process for coating articles and articles made therefrom
US5098797A (en) Steel articles having protective duplex coatings and method of production
US20090162670A1 (en) Method for applying ceramic coatings to smooth surfaces by air plasma spray techniques, and related articles
US20110052406A1 (en) Airfoil and process for depositing an erosion-resistant coating on the airfoil
US20060222776A1 (en) Environment-resistant platinum aluminide coatings, and methods of applying the same onto turbine components
EP0969117A2 (fr) Procédé pour la production d'un système de revêtement de barrière thermique
EP3404127A1 (fr) Revêtement de barrière environnementale à gradient fonctionnel
CN101711290A (zh) 为涡轮发动机部件上的热障涂层形成粘合层的方法
US6180260B1 (en) Method for modifying the surface of a thermal barrier coating, and related articles
US20080131612A1 (en) Method for making an environment-resistant and thermal barrier coating system on a component
US6485792B1 (en) Endurance of NiA1 coatings by controlling thermal spray processing variables
US20050053800A1 (en) Method for post deposition of beta phase nickel aluminide coatings
US20070116884A1 (en) Process for coating articles and articles made therefrom
GB2206358A (en) Corrosion-resistant aluminium-bearing iron base alloy coating
JP3468599B2 (ja) 高速ガス炎溶射法
Meyer et al. Production Coating Cost Comparison

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20040918