WO2014143363A1 - Revêtement de barrière thermique hybride et son procédé de fabrication - Google Patents

Revêtement de barrière thermique hybride et son procédé de fabrication Download PDF

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Publication number
WO2014143363A1
WO2014143363A1 PCT/US2013/078186 US2013078186W WO2014143363A1 WO 2014143363 A1 WO2014143363 A1 WO 2014143363A1 US 2013078186 W US2013078186 W US 2013078186W WO 2014143363 A1 WO2014143363 A1 WO 2014143363A1
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WO
WIPO (PCT)
Prior art keywords
layer
barrier coating
thermal barrier
forming
thermal
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.)
Ceased
Application number
PCT/US2013/078186
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English (en)
Inventor
Brian T HAZEL
David A. Litton
Michael J. Maloney
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.)
RTX 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
Priority to US14/775,031 priority Critical patent/US20160017475A1/en
Priority to EP13878078.8A priority patent/EP2971240B1/fr
Publication of WO2014143363A1 publication Critical patent/WO2014143363A1/fr
Anticipated expiration legal-status Critical
Priority to US15/996,929 priority patent/US20180282853A1/en
Ceased legal-status Critical Current

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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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
    • C23C28/042—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—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 disclosure relates to a thermal barrier coating for use on a turbine engine component and to a process of making the thermal barrier coating.
  • a thermal barrier coating (TBC) is created to meet one or more performance requirements including, but not liited to, spallation life, calcia-magnesia-alumina- silicate (CMAS) resistance, foreign object damage (FOD) resistance, erosion, and low conductivity.
  • CMAS calcia-magnesia-alumina- silicate
  • FOD foreign object damage
  • a turbine barrier coating is applied to a turbine engine component, such as a turbine blade/vane, to help the component withstand the relatively high temperatures of its operational environment.
  • TBCs are often formed using a singular coating process such as an electron beam physical vapor deposition
  • a TBC may be formed from two separate EB-PVD layers formed from two different materials, such as 7 wt% yttria stabilized zirconia and gadolinia stabilized zirconia in order to improve the thermal conductivity properties of the coating.
  • the strain-tolerant columnar structure of an EB-PVD coating helps to increase the TBC spallation life.
  • a more porous TBC however may minimize the TBC thermal conductivity and possibly the thermal radiation through the coating.
  • TBC there is a porous outer layer over a more dense inner layer made by an EB-PVD process.
  • the two layers have diff rent porosity levels.
  • Such a structure can be formed by changing the coating temperature. More power equals more density but also more temperature. It is also known to form a dense vertically cracked microstructure for the TBC where the deposition is conducted at a two inch stand-off for the dense layer and a six inch stand-off for the porous layer.
  • thermal barrier coating which is applied to a turbine engine component having a substrate, which thermal barrier coating broadly comprises a first layer which has a strain tolerant columnar microstructure at an interface with the substrate for spallation resistance and a second layer which is porous conduction and radiation thermally resistant at an outer surface of the thermal barrier coating.
  • the first and second layers are formed from the same material.
  • the first and second layers are formed from different compositions.
  • the second layer has a porosity in the range of from 10 to 40%.
  • each of the first and second layers is formed from 7 wt% yttria stabilized zirconia.
  • the first layer is formed from 7wt% yttria stabilized zirconia and the second layer is formed from gadolinia stabilized zirconia .
  • the first layer has a first thermal conductivity and the second layer has a second thermal conductivity which is at least 10% lower than the first thermal conductivity.
  • a process for applying a thermal barrier coating to a turbine engine component which broadly comprises the steps of: forming a first layer which has a strain tolerant columnar microstructure at an interface of the first layer and a substrate using a suspension plasma spray technique; and forming a second layer which is porous and radiation thermally resistant at an outer surface of the thermal barrier coating using one of the suspension plasma spray technique and an air spray plasma technique.
  • the process further comprises forming a continuously graded microstructure from the interface to the outer surface.
  • the first layer forming step comprises suspending a powder feedstock in a liquid suspension and injecting the powder feedstock and the suspension into a plasma jet under conditions where the first layer is formed with the strain-tolerant columnar microstructure.
  • the second layer forming step comprises changing spray parameters so as to form the porous and radiation thermally resistant second layer.
  • the first and second layer forming steps comprises forming the first and second layers from the same material.
  • the first layer is formed from a first material having a first composition and the second layer is formed from a second material having a second composition which is different from the first composition.
  • the second layer is formed using the air spray plasma technique .
  • the second layer forming step comprises forming the second layer so as to have a porosity of from 10 to 40%.
  • the second layer forming step comprises forming the second layer so as to have a thermal conductivity which is at least 10% lower than a thermal conductivity of the first layer .
  • the first and second layer forming steps comprise using a powdered feedstock having a particle size in the range of from lOnm to 10 microns.
  • the first and second layer forming steps comprises using a powdered feedstock having a particle size in the range of from lOnm to 2.0 microns .
  • FIG. 1 illustrates a turbine engine component having a thermal barrier coating in accordance with the present disclosure deposited thereon
  • FIG. 2 illustrates a system for forming the coating on the turbine engine component.
  • the turbine engine component may be any component which requires a thermal barrier coating such as a blade/vane.
  • the turbine engine component 10 may have a substrate 12 formed from any suitable material known in the art including, but not limited to, a nickel based alloy, a cobalt based alloy, a titanium based alloy, a ceramic material, and an organo- matrix composite material.
  • a thermal barrier coating 14 may be deposited on the substrate 12.
  • the thermal barrier coating 14 may have a first layer 16 which interfaces with the surface 18 of the substrate 12 and an outer second layer 20.
  • the first layer 16 may be formed so as to have a strain-tolerant columnar microstructure at the interface with the surface 18 of the substrate.
  • the second layer 20 may be formed to have a porous thermal conduction and radiant heat transfer resistant microstructure at an outer surface 22 of the thermal barrier coating.
  • the first layer 16 and the second layer 20 may formed from a material having the same composition.
  • each of the layers 16 and 20 may be formed from a 7 wt% yttria stabilized zirconia (7YSZ) .
  • the first layer 16 may be formed from a first material having a first composition and the second layer 20 may be formed from a second material having a second composition which is different from the first composition.
  • the first layer 16 may be formed from 7YSZ, while the second layer 20 is formed from gadolinia stabilized zirconia.
  • Each of the layers 16 and 20 may be formed using suspension plasma spray (SPS) technique such as that shown in FIG. 2.
  • SPS suspension plasma spray
  • a powdered feedstock is suspended in a liquid suspension 30.
  • the powdered feedstock may be 7YSZ which may be suspended in ethanol, water, or other alcohols such as methanol.
  • the powdered feedstock may have a particle size in the range of from 10 nm to 10 microns mean size diameter. In another non-limiting embodiment, the particles size may be in the range of from 10 nm to 2.0 microns.
  • the powdered feedstock in the suspension is injected into a plasma jet 32 created by a plasma torch 34 and thus deposited onto the substrate 12. The spray conditions are such that the first layer 16 is formed to have the desired strain tolerant columnar microstructure .
  • the deposition technique may have a short stand off (similar to that used in dense vertically cracked coatings) and high power/enthalpy plasma conditions.
  • the spray conditions may be changed so as to form the second layer 20 with the porous thermal conduction and radiant heat transfer resistant microstructure.
  • the angle of the spray nozzle could be changed from normal relative to the surface on which the layer 20 is being deposited; (2) the stand off may be increased; and/or (3) the plasma power/enthalpy may be reduced.
  • More porosity in the second layer 20 than in the first layer 16 creates a reduction in thermal conductivity.
  • the second layer 20 may have a reduction of at least 10% in thermal conductivity. This may come purely from a porosity increase or a change in the structure from columnar to more splat like. An increase in porosity increases the erosion rate.
  • a useful limit may be 10 to 40% porosity in the second layer 20.
  • the columnar structure SPS gives a thermal cyclic spallation resistance similar to EB-PVD (much higher than APS and higher than dense vertically cracked) .
  • Erosion is a function of porosity content and can be greater or less than EB-PVD (generally higher than APS and more like dense vertically cracked) .
  • Thermal conductivity as discussed above, follows the porosity content .
  • the spray conditions may be discreetly or incrementally changed throughout the spray run.
  • the spray conditions may be changed so that a continuously graded microstructure is formed where there is the strain-tolerant columnar microstructure at the interface with the substrate 12 for thermal barrier coating spallation resistance and a porous thermal conduction and radiation thermally resistant layer at the outer surface 22.
  • the first layer 16 may be formed using the above discussed SPS technique and the second layer 20 may be formed using a porous air plasma spray (APS) technique.
  • APS porous air plasma spray
  • thermal barrier coating can be formed using a single piece of equipment and in a single coating run .
  • Another advantage is that one can easily change the composition of the second layer 20 so that it is different than the composition of the first layer 16. This can easily be done by changing the composition of the feedstock being injected into the plasma jet.
  • a hybrid thermal barrier coating and a process for making same. While the coating and process have been described in the context of specific embodiments thereof, other unforeseen 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.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Ceramic Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

La présente invention concerne un revêtement de barrière thermique hybride appliqué à un composant de moteur à turbine comportant un substrat. Le revêtement de barrière thermique comporte une première couche possédant une microstructure en forme de colonne tolérante à la contrainte au niveau d'une interface avec le substrat pour une résistance à la spallation et une seconde couche qui est poreuse, résistante à la conduction et au rayonnement au niveau d'une surface externe du revêtement de barrière thermique.
PCT/US2013/078186 2013-03-14 2013-12-30 Revêtement de barrière thermique hybride et son procédé de fabrication Ceased WO2014143363A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US14/775,031 US20160017475A1 (en) 2013-03-14 2013-12-30 Hybrid Thermal Barrier Coating and Process of Making Same
EP13878078.8A EP2971240B1 (fr) 2013-03-14 2013-12-30 Revêtement de barrière thermique hybride et son procédé de fabrication
US15/996,929 US20180282853A1 (en) 2013-03-14 2018-06-04 Hybrid Thermal Barrier Coating and Process of Making Same

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361781656P 2013-03-14 2013-03-14
US61/781,656 2013-03-14

Related Child Applications (2)

Application Number Title Priority Date Filing Date
US14/775,031 A-371-Of-International US20160017475A1 (en) 2013-03-14 2013-12-30 Hybrid Thermal Barrier Coating and Process of Making Same
US15/996,929 Division US20180282853A1 (en) 2013-03-14 2018-06-04 Hybrid Thermal Barrier Coating and Process of Making Same

Publications (1)

Publication Number Publication Date
WO2014143363A1 true WO2014143363A1 (fr) 2014-09-18

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US (2) US20160017475A1 (fr)
EP (1) EP2971240B1 (fr)
WO (1) WO2014143363A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043411A1 (fr) * 2015-11-09 2017-05-12 Commissariat Energie Atomique Revetement ceramique multicouche de protection thermique a haute temperature, notamment pour application aeronautique, et son procede de fabrication
US10436042B2 (en) 2015-12-01 2019-10-08 United Technologies Corporation Thermal barrier coatings and methods

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6908973B2 (ja) * 2016-06-08 2021-07-28 三菱重工業株式会社 遮熱コーティング、タービン部材、ガスタービン、ならびに遮熱コーティングの製造方法
US20250115768A1 (en) * 2023-10-06 2025-04-10 Rtx Corporation Multi-phase radiative and thermal barrier coating system

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JP2001348655A (ja) * 2000-06-09 2001-12-18 Mitsubishi Heavy Ind Ltd 遮熱コーティング材、それを適用したガスタービン部材およびガスタービン
JP2009108856A (ja) * 2007-10-29 2009-05-21 General Electric Co <Ge> 遮熱コーティングの処理方法及び関連物品
JP2010255121A (ja) * 2010-07-20 2010-11-11 Mitsubishi Heavy Ind Ltd 皮膜材料
US20110151219A1 (en) * 2009-12-21 2011-06-23 Bangalore Nagaraj Coating Systems for Protection of Substrates Exposed to Hot and Harsh Environments and Coated Articles
EP2341166A1 (fr) 2009-12-29 2011-07-06 Siemens Aktiengesellschaft Barrière thermique ceramique nano- et microstructurée

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DE102008007870A1 (de) * 2008-02-06 2009-08-13 Forschungszentrum Jülich GmbH Wärmedämmschichtsystem sowie Verfahren zu seiner Herstellung
US20110143043A1 (en) * 2009-12-15 2011-06-16 United Technologies Corporation Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware
EP2450465A1 (fr) * 2010-11-09 2012-05-09 Siemens Aktiengesellschaft Système de couche poreux doté d'une couche intérieure poreuse
US9017792B2 (en) * 2011-04-30 2015-04-28 Chromalloy Gas Turbine Llc Tri-barrier ceramic coating
US20130260132A1 (en) * 2012-04-02 2013-10-03 United Technologies Corporation Hybrid thermal barrier coating

Patent Citations (6)

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Publication number Priority date Publication date Assignee Title
JP2001348655A (ja) * 2000-06-09 2001-12-18 Mitsubishi Heavy Ind Ltd 遮熱コーティング材、それを適用したガスタービン部材およびガスタービン
JP2009108856A (ja) * 2007-10-29 2009-05-21 General Electric Co <Ge> 遮熱コーティングの処理方法及び関連物品
US20110151219A1 (en) * 2009-12-21 2011-06-23 Bangalore Nagaraj Coating Systems for Protection of Substrates Exposed to Hot and Harsh Environments and Coated Articles
EP2341166A1 (fr) 2009-12-29 2011-07-06 Siemens Aktiengesellschaft Barrière thermique ceramique nano- et microstructurée
KR20120088874A (ko) * 2009-12-29 2012-08-08 지멘스 악티엔게젤샤프트 나노 및 마이크로 구조의 세라믹 열 차단 코팅
JP2010255121A (ja) * 2010-07-20 2010-11-11 Mitsubishi Heavy Ind Ltd 皮膜材料

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043411A1 (fr) * 2015-11-09 2017-05-12 Commissariat Energie Atomique Revetement ceramique multicouche de protection thermique a haute temperature, notamment pour application aeronautique, et son procede de fabrication
WO2017080948A1 (fr) * 2015-11-09 2017-05-18 Commissariat A L'energie Atomique Et Aux Energies Alternatives Revêtement céramique multicouche de protection thermique à haute température, notamment pour application aéronautique, et son procédé de fabrication
US10436042B2 (en) 2015-12-01 2019-10-08 United Technologies Corporation Thermal barrier coatings and methods

Also Published As

Publication number Publication date
US20180282853A1 (en) 2018-10-04
EP2971240A4 (fr) 2016-12-21
EP2971240A1 (fr) 2016-01-20
US20160017475A1 (en) 2016-01-21
EP2971240B1 (fr) 2018-11-21

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