WO2017076731A1 - 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 - Google Patents

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 Download PDF

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Publication number
WO2017076731A1
WO2017076731A1 PCT/EP2016/075895 EP2016075895W WO2017076731A1 WO 2017076731 A1 WO2017076731 A1 WO 2017076731A1 EP 2016075895 W EP2016075895 W EP 2016075895W WO 2017076731 A1 WO2017076731 A1 WO 2017076731A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling air
ceramic
ceramic material
layer system
air holes
Prior art date
Application number
PCT/EP2016/075895
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Christian Menke
Werner Stamm
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2017076731A1 publication Critical patent/WO2017076731A1/fr

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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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • 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

Definitions

  • Thermal insulation layer system with cooling air holes and different thermal insulation layer in the area of cooling air holes
  • the invention relates to a thermal barrier coating system comprising a substrate and at least one ceramic coating, wherein the thermal barrier coating system has through holes and has a different ceramic coating in the region of the through holes.
  • Turbine components of gas turbines have cooling air holes, in particular rows of cooling air holes, where cooling air flows from ⁇ , since there the components are exposed to specific thermal loads so that it is there to stronger thermal gradient.
  • the object is achieved by a ceramic layer system according to claim 1.
  • FIG. 1 shows a cross section of a wall of a component 1.
  • the component 1 is in particular a turbine blade 4 on a substrate a ceramic coating 7 is hands before ⁇ .
  • the substrate 4 has at least one through hole 13. Around the through hole 13 there is a recess 11, where no first ceramic material of the ceramic coating 7 is present.
  • a second ceramic material 10 is present in the recess 11.
  • Such a turbine blade 1 has a wall which has a substrate 4 and on the outside a ceramic coating 7 made of a first ceramic material.
  • the substrate 4 is in particular a nickel- or cobalt-based superalloy ⁇ .
  • a metallic bond layer is present (not shown in detail) on the substrate 4, insbesonder based NiCoCrAlY, an oxide layer, grown, or oxidized by the metallic bond coating layer, and since ⁇ up at least a ceramic coating 7 made of a ers th ceramic material.
  • the first ceramic material is preferably teilstabili ⁇ overbased zirconium oxide.
  • the layer system 1 also has through holes 13, which serve for film cooling in turbine components. It is in the area of the through hole 13, no material of the ceramic coating 7 is provided from the first ceramic material, but a second material as the ceramic thermal barrier coating 10 on the surface of the sub ⁇ strats in the region. 11
  • the second ceramic material is different from the first ceramic material at least by a higher poro ⁇ intensity at least 2% (absolute) and / or through the micro ⁇ structure with longitudinal cracks or a DVC structure (perpendicular right cracks in a dense layer) and / or by the composition.
  • the second material is in particular a ceramic coating with vertical cracks (DVC), which also has an increased density and / or a pyrochlore.
  • DVC vertical cracks
  • a gap 19 is preferably present.
  • FIG. 2 shows a plan view of FIG. 1.
  • the second material 15 is preferably continuous along the orientation 15.
  • Such an arrangement is produced in that first the first ceramic material for the ceramic Schichtsys ⁇ system 7 is applied and layer by suitable measures during loading or subsequent removal of a recess is formed in which no ceramic material along the cooling air ⁇ row 14 or the Through hole 13 is present.
  • the extent of the recess 11 transverse to the longitudinal direction of the cooling air row 14, 30, 33, 36 is 2-3 times the diameter of the through hole 13th
  • the second ceramic material is deposited in the area around the through holes 13.
  • the porosity of the ceramic coating for the layer 7 is at least 8%.
  • the porosity for such a dense layer of the second ceramic material having elongated cracks or DVC structure is at most 6%, especially at most 5%.
  • the second ceramic material for the ceramic coating and the through hole 13 may be applied around the cooling air row 14, and then the first material for the coating 7 is applied.
  • FIG. 3 shows a plan view of an airfoil 39 of a turbine blade.
  • the one side of the airfoil 39 has, in particular, three rows of cooling air 30, 33, 36. These can run straight 33, once bent 30a, 30b or bent twice 36a, 36b, 36c.
  • sections 30a, 30b; 33; 36a, 36b, 36c each arranged a plurality of cooling air holes in a straight line.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un système de barrière thermique pourvu de trous destinés à de l'air de refroidissement et une couche formant barrière thermique différente dans la zone des trous débouchants. L'utilisation de deux matériaux différents dans la zone des trous débouchants (13) et en dehors des trous débouchants (13) permet d'éviter tout écaillage du matériau céramique.
PCT/EP2016/075895 2015-11-02 2016-10-27 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 WO2017076731A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015221422.2A DE102015221422A1 (de) 2015-11-02 2015-11-02 Wärmedämmschichtsystem mit Kühlluftlöchern und verschiedener Wärmedämmschicht im Bereich der Kühlluftbohrungen
DE102015221422.2 2015-11-02

Publications (1)

Publication Number Publication Date
WO2017076731A1 true WO2017076731A1 (fr) 2017-05-11

Family

ID=57218879

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2016/075895 WO2017076731A1 (fr) 2015-11-02 2016-10-27 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

Country Status (2)

Country Link
DE (1) DE102015221422A1 (fr)
WO (1) WO2017076731A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021123151A1 (de) 2021-09-07 2023-03-09 Aurubis Ag Verfahren und Anlage zur Rückgewinnung von Metallen aus schwarzer Masse

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1669545A1 (fr) * 2004-12-08 2006-06-14 Siemens Aktiengesellschaft Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
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
EP2733236A1 (fr) * 2012-11-16 2014-05-21 Siemens Aktiengesellschaft Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6375425B1 (en) * 2000-11-06 2002-04-23 General Electric Company Transpiration cooling in thermal barrier coating
JP5550699B2 (ja) * 2012-10-15 2014-07-16 三菱重工業株式会社 ガスタービン用部材

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1669545A1 (fr) * 2004-12-08 2006-06-14 Siemens Aktiengesellschaft Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
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
EP2733236A1 (fr) * 2012-11-16 2014-05-21 Siemens Aktiengesellschaft Système de couche céramique double couche avec couche extérieure poreuse et évidements à l'intérieur

Also Published As

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DE102015221422A1 (de) 2017-05-04

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