EP2733236A1 - Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur - Google Patents

Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur Download PDF

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Publication number
EP2733236A1
EP2733236A1 EP12192924.4A EP12192924A EP2733236A1 EP 2733236 A1 EP2733236 A1 EP 2733236A1 EP 12192924 A EP12192924 A EP 12192924A EP 2733236 A1 EP2733236 A1 EP 2733236A1
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EP
European Patent Office
Prior art keywords
thermal barrier
barrier coating
layer
layer system
ceramic 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.)
Withdrawn
Application number
EP12192924.4A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Werner Stamm
Karsten Klein
Eckart Schumann
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP12192924.4A priority Critical patent/EP2733236A1/fr
Publication of EP2733236A1 publication Critical patent/EP2733236A1/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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 invention relates to a layer system in which a two-layer ceramic thermal barrier coating is present, in which recesses are introduced in the outermost ceramic layer, whereby the abrasive behavior is improved.
  • Ceramic layer systems on substrates with intermediate metallic adhesion promoter layer are state of the art.
  • the object is achieved by a layer system according to claim 1.
  • FIG. 1 an inventive layer system 1 is shown.
  • the layer system 1 has a substrate 4.
  • the substrate material is in particular a nickel- or cobalt-based superalloy, in particular an alloy according to FIG. 4 ,
  • a metallic adhesion promoter layer 7 comprising nickel aluminides, platinum aluminides or preferably an MCrAlX alloy.
  • An aluminum oxide layer (TGO) is preferably grown on this metallic adhesion promoter layer 7 or on the substrate 4 before the application of a ceramic layer, or it is deliberately produced, whereas in use it is generated in any case (TGO not shown).
  • an at least two-layer ceramic thermal barrier coating 13 is applied in a known manner.
  • porous means that the absolute difference in porosity is at least 2 vol%, in particular at least 4 vol%. (Example: porosity of inner layer 13: 8 vol%, then porosity of outer layer 19: ⁇ 12 vol%). The porosity of the outermost layer 19 is at most 40%.
  • the same material is preferably used for the thermal barrier coatings 16, 19.
  • the holes 20 and / or recesses 21 are not cracks.
  • the holes 20 preferably have a constant cross-section (viewed in the direction 25 of the layer thickness).
  • the recesses 21 are preferably formed uniformly, thus have a constant cross section in the cross section parallel to the direction 25.
  • the holes 20 and / or recesses 21 preferably extend parallel in a vertical direction 25 to the substrate 4.
  • the production of the holes 20 or recesses 21 can be done in several ways, in particular by subsequent laser processing or directly during the coating.
  • the holes 20 and / or recesses 21 are preferably uniformly distributed over the surface 22 or a surface area, especially where a contact surface is given for use.
  • the line-shaped recesses 21 and / or holes 20 are preferably used to reduce the contact area between a blade tip of a turbine blade 120, and the housing of a gas turbine 100 or generally between two mutually moving components.
  • the holes 20 and / or the line-shaped depressions 21 may also extend into the inner denser ceramic thermal barrier coating 16.
  • the holes 20 and / or recesses 21 preferably do not extend as far as the metallic adhesion promoter layer 7 or to the substrate 4 or not to the TGO.
  • HVOF or plasma spray processes are used for the production of both ceramic layers 16, 19.
  • FIG. 3 shows a perspective view of a blade 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjacent thereto and an airfoil 406 and a blade tip 415.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole Workpiece consists of a single crystal.
  • a columnar grain structure columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified
  • a monocrystalline structure ie the whole Workpiece consists of a single crystal.
  • directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • the density is preferably 95% of the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8Al-0.6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10A1-0,4Y-1 are also preferably used , 5RE.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , that is, it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • suitable coating methods e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 5 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the vane 130 has a guide vane foot (not shown here) facing the inner casing 138 of the turbine 108 and a vane head opposite the vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12192924.4A 2012-11-16 2012-11-16 Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur Withdrawn EP2733236A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12192924.4A EP2733236A1 (fr) 2012-11-16 2012-11-16 Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12192924.4A EP2733236A1 (fr) 2012-11-16 2012-11-16 Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur

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EP2733236A1 true EP2733236A1 (fr) 2014-05-21

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016105327A1 (fr) * 2014-12-22 2016-06-30 Siemens Aktiengesellschaft Procédé permettant de contrôler le délaminage de revêtement entraîné lors de la formation des trous de refroidissement au travers des revêtements de barrière thermique
WO2017076731A1 (fr) * 2015-11-02 2017-05-11 Siemens Aktiengesellschaft Système de barrière thermique doté de trous destinés à de l'air de refroidissement et une couche formant barrière thermique différente dans la zone des trous destinés à de l'air de refroidissement
DE102015222808A1 (de) * 2015-11-19 2017-05-24 Siemens Aktiengesellschaft Segmentiertes zweilagiges Schichtsystem

Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0412397B1 (fr) 1989-08-10 1998-03-25 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium possédant une résistance plus grande à la corrosion et l'oxydation
EP0892090A1 (fr) 1997-02-24 1999-01-20 Sulzer Innotec Ag Procédé de fabrication de structure smonocristallines
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6024792A (en) 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
WO2000044949A1 (fr) 1999-01-28 2000-08-03 Siemens Aktiengesellschaft Superalliage a base de nickel presentant une bonne usinabilite
EP1247941A1 (fr) * 2001-04-03 2002-10-09 Siemens Aktiengesellschaft Aube de turbine à gaz
EP1283278A2 (fr) * 2001-08-02 2003-02-12 Siemens Westinghouse Power Corporation Revêtement de barrière thermique segmenté et procédé pour sa fabrication
EP1306454A1 (fr) 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
EP1319729A1 (fr) 2001-12-13 2003-06-18 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel
US20030211354A1 (en) * 1996-12-10 2003-11-13 Siemens Westinghouse Power Corporation Sinter resistant abradable thermal barrier coating
EP1204776B1 (fr) 1999-07-29 2004-06-02 Siemens Aktiengesellschaft Piece resistant a des temperatures elevees et son procede de production
EP1564537A1 (fr) * 2004-02-17 2005-08-17 Siemens Aktiengesellschaft Surveillance non destructive de modifications microstructurelles d' un élément de construction ( système de couches, aubes de turbine, garnissage de chambre de combustion )
WO2007112783A1 (fr) * 2006-04-06 2007-10-11 Siemens Aktiengesellschaft Revetement stratifie formant une barriere thermique a porosite elevee et composant
EP2009131A1 (fr) * 2006-03-31 2008-12-31 Mitsubishi Heavy Industries, Ltd. Element de revetement bouclier thermique, son procede de production, materiau de revetement bouclier thermique, turbine a gaz et corps fritte
EP2275645A2 (fr) * 2009-07-17 2011-01-19 Rolls-Royce Corporation Composant de turbine à gaz comprenant des caractéristiques de réduction de la fatigue
WO2011103927A1 (fr) * 2010-02-26 2011-09-01 Siemens Aktiengesellschaft Couche d'accrochage métallique à deux couches

Patent Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0412397B1 (fr) 1989-08-10 1998-03-25 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium possédant une résistance plus grande à la corrosion et l'oxydation
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
US20030211354A1 (en) * 1996-12-10 2003-11-13 Siemens Westinghouse Power Corporation Sinter resistant abradable thermal barrier coating
EP0892090A1 (fr) 1997-02-24 1999-01-20 Sulzer Innotec Ag Procédé de fabrication de structure smonocristallines
US6024792A (en) 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
WO2000044949A1 (fr) 1999-01-28 2000-08-03 Siemens Aktiengesellschaft Superalliage a base de nickel presentant une bonne usinabilite
EP1204776B1 (fr) 1999-07-29 2004-06-02 Siemens Aktiengesellschaft Piece resistant a des temperatures elevees et son procede de production
EP1247941A1 (fr) * 2001-04-03 2002-10-09 Siemens Aktiengesellschaft Aube de turbine à gaz
EP1283278A2 (fr) * 2001-08-02 2003-02-12 Siemens Westinghouse Power Corporation Revêtement de barrière thermique segmenté et procédé pour sa fabrication
EP1306454A1 (fr) 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
EP1319729A1 (fr) 2001-12-13 2003-06-18 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel
EP1564537A1 (fr) * 2004-02-17 2005-08-17 Siemens Aktiengesellschaft Surveillance non destructive de modifications microstructurelles d' un élément de construction ( système de couches, aubes de turbine, garnissage de chambre de combustion )
EP2009131A1 (fr) * 2006-03-31 2008-12-31 Mitsubishi Heavy Industries, Ltd. Element de revetement bouclier thermique, son procede de production, materiau de revetement bouclier thermique, turbine a gaz et corps fritte
WO2007112783A1 (fr) * 2006-04-06 2007-10-11 Siemens Aktiengesellschaft Revetement stratifie formant une barriere thermique a porosite elevee et composant
EP2275645A2 (fr) * 2009-07-17 2011-01-19 Rolls-Royce Corporation Composant de turbine à gaz comprenant des caractéristiques de réduction de la fatigue
WO2011103927A1 (fr) * 2010-02-26 2011-09-01 Siemens Aktiengesellschaft Couche d'accrochage métallique à deux couches

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016105327A1 (fr) * 2014-12-22 2016-06-30 Siemens Aktiengesellschaft Procédé permettant de contrôler le délaminage de revêtement entraîné lors de la formation des trous de refroidissement au travers des revêtements de barrière thermique
WO2017076731A1 (fr) * 2015-11-02 2017-05-11 Siemens Aktiengesellschaft Système de barrière thermique doté de trous destinés à de l'air de refroidissement et une couche formant barrière thermique différente dans la zone des trous destinés à de l'air de refroidissement
DE102015222808A1 (de) * 2015-11-19 2017-05-24 Siemens Aktiengesellschaft Segmentiertes zweilagiges Schichtsystem

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