EP1645654A1 - Verfahren zum Herstellen einer flexiblen Wärmedämmschich - Google Patents

Verfahren zum Herstellen einer flexiblen Wärmedämmschich Download PDF

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Publication number
EP1645654A1
EP1645654A1 EP04291265A EP04291265A EP1645654A1 EP 1645654 A1 EP1645654 A1 EP 1645654A1 EP 04291265 A EP04291265 A EP 04291265A EP 04291265 A EP04291265 A EP 04291265A EP 1645654 A1 EP1645654 A1 EP 1645654A1
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EP
European Patent Office
Prior art keywords
torch
blade
ceramic layer
thermal barrier
jet
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Withdrawn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
EP04291265A
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English (en)
French (fr)
Inventor
Per Bengtsson
Laurent Dudon
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Priority to EP04291265A priority Critical patent/EP1645654A1/de
Publication of EP1645654A1 publication Critical patent/EP1645654A1/de
Withdrawn legal-status Critical Current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
    • C23C4/04—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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50211—Expansivity similar

Definitions

  • the invention relates to flexo-adaptive thermal barriers, that is to say the thermal barriers having a sufficient flexibility to adapt to the deformations of the substrate, whether mechanical origin or dilatometric under the effect of a thermal gradient.
  • the invention relates more particularly to an economical process for obtaining such barriers by thermal spraying.
  • the thermal barriers thus obtained by plasma spraying are therefore reserved for fixed parts that do not undergo thermal shocks such as combustion chambers.
  • the ceramic layer is of the order of 0.3 mm and its life is perfectly controlled in this case.
  • US Pat. No. 6,306,517 also discloses a method for applying a thin-film thermal barrier by plasma spraying, the bond between the layers being improved by the columnar germination of the grains, which can thus become common to several layers. With such a process unfortunately, the germination is also laterally which reduces the flexibility of the thermal barrier.
  • the sensitivity to chipping of a thermal barrier increases in the projecting parts of the part having a small radius of curvature, so more particularly with small parts such as turbine blades.
  • thermal barrier the least sensitive possible to chipping, it is necessary to seek to obtain a thermal barrier having a cohesion of high material and a hooking of the strongest.
  • a first problem to be solved is to improve the resistance to flaking of the thermal barriers.
  • a second problem to be solved is to reduce the cost of developing a thermal barrier.
  • a thermal barrier in order to be resistant to both the high thermal stresses on the surface of the substrate and the important mechanical stresses thereof, and thereby to respond to the first problem, must be flexible in the directions tangential to the surface it covers. For this purpose, it is necessary to introduce vertical cracks ranging from the surface of the thermal barrier to the substrate or the underlayer, ie through the entire ceramic layer.
  • the invention proposes a method for obtaining a flexo-adpative thermal barrier, the thermal barrier comprising a ceramic layer (44) having a thickness of at least 80 ⁇ m deposited on a substrate (40) covered with a underlayer (42), the ceramic layer (44) being deposited by thermal spraying using a torch (30) called "plasma arc", the operation of the torch being defined by the power of the torch , the flow rate of material, the distance of the torch to the workpiece (10) to be coated and the speed of movement of the torch relative to the workpiece.
  • a torch (30) called "plasma arc"
  • Such a method is remarkable in that it consists in depositing, directly on the underlayer and in a single pass, the ceramic layer while maintaining a projection distance of between 20 mm and 90 mm, the speed of displacement of the torch being between 2mm / s and 10mm / s, the material flow being between 40g / min and 100g / min and the arc intensity of the torch being between 500A and 800A, so as to obtain after cooling at least 2 substantially vertical cracks per millimeter and passing through the entire ceramic layer.
  • the power of the torch being set to a high value and the ceramic layer produced in one pass, the new drops of molten material arrive on the still very hot material, which causes an excellent connection by welding between the ceramic grains in the vertical direction.
  • This is favored by the choice of a displacement speed of the torch as small as possible, preferably between 2mm / s and 10mm / s.
  • the temperature at the location of the deposit is high which allows to obtain a dense microstructure with a number micro horizontal cracks, delaminations and reduced pores, and better cohesion of the material.
  • Single-pass projection is an important parameter that directly affects the chipping resistance of the thermal barrier.
  • the cracks are denser and homogeneous and the vertical bonds between the grains are simultaneously improved.
  • the inventors obtain a thermal barrier having a satisfactory resistance to chipping up to a thickness of the ceramic layer. of 250 ⁇ m, the optimum quality however being between 100 ⁇ m and 150 ⁇ m.
  • the power of the appropriate torch to achieve this result depends on many parameters such as the ceramic used heat dissipation in the room, the flow of powder, the width of the jet, the coefficient of loss of the torch, etc. It should also be noted that those skilled in the art will, however, limit the power of the torch so as not to cause excessive heating which risks causing the substrate to melt or an inadmissible alteration of its granular structure.
  • the dimensions of the cracks, as well as the number of cracks per mm, depend on the thickness of the deposit. The thicker the deposit, the wider the cracks and the smaller their number per mm.
  • the thickness of the ceramic layer obtained in a single pass is obviously a function of the flow rate of material, the distance of the torch to the workpiece and the speed of movement of the torch, ie the jet, relative to per piece, as well as the coefficient of loss of the torch.
  • the thickness of the ceramic layer increases with the flow of material, but this thickness decreases as the distance or speed increases.
  • the part to be coated with a thermal barrier is a turbine blade made of nickel superalloy base with directed solidification.
  • the thermal barrier comprises an undercoat of McrAlY covered by a ceramic layer of 125 ⁇ m ZrO 2 zircon with 8% Y 2 O 3 ytrine.
  • the blade 12 of the blade 10 is covered with an underlay of McrAIY deposited according to the usual methods.
  • the blade 10 is then held by its foot 14 on a rotating assembly 20 capable of rotating the blade on its axis 16, that is to say on itself in the direction of the length, the blade 12 being presented in front of a plasma torch 30 whose jet will be referenced 32.
  • the plasma torch 32 is here the F4 model marketed by the company whose corporate name is Sultzer Metco.
  • the torch is placed at 50mm from the blade 10, the blade 10 being then rotated on its axis 16.
  • the torch 30 is put into operation and the jet 32 first touches the top 18a of the blade 10 and progressively moves towards the foot 14 to reach the other end 18b of the blade 12 and thus to form on the surface of the blade 10 a ceramic layer 44 having the shape of a helix with contiguous turns.
  • the jet 32 moves on the surface of the blade 12 at a resulting speed of 6 mm / s.
  • the powder flow rate is 70g / min, and the power of the torch is obtained with an arc intensity of 700A.
  • the setting of the torch is said to be "hot", the temperature of the deposit is 550 ° C., this temperature being measured at the surface of the deposit just after the passage of the jet 32 and at 10 mm behind the jet.
  • the substrate, the underlayer and the ceramic layer thus obtained are referenced 40, 42 and 44, respectively.
  • the cracks are referenced 50.
  • the cracks 50 are substantially vertical, ie substantially perpendicular to the substrate 40.
  • the two edges of the cracks 50 may be parallel or open towards the surface or to the underlayer 42.
  • the characteristic Cracks 50 are essential that they travel from the surface to the underlayer 42, through the entire thickness of the ceramic layer 44, as shown in the micrograph.
  • the cracks 50 form a locally irregular but statistically homogeneous and anisotropic network, these cracks 50 providing the thermal barrier with the required flexibility along a plane tangential to the substrate 40.
  • the density of cracks is defined as the average number cracks per millimeter intersecting any geometric line.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
EP04291265A 2004-05-18 2004-05-18 Verfahren zum Herstellen einer flexiblen Wärmedämmschich Withdrawn EP1645654A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04291265A EP1645654A1 (de) 2004-05-18 2004-05-18 Verfahren zum Herstellen einer flexiblen Wärmedämmschich

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04291265A EP1645654A1 (de) 2004-05-18 2004-05-18 Verfahren zum Herstellen einer flexiblen Wärmedämmschich

Publications (1)

Publication Number Publication Date
EP1645654A1 true EP1645654A1 (de) 2006-04-12

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EP04291265A Withdrawn EP1645654A1 (de) 2004-05-18 2004-05-18 Verfahren zum Herstellen einer flexiblen Wärmedämmschich

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EP (1) EP1645654A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012004525A1 (fr) 2010-07-06 2012-01-12 Snecma Barriere thermique pour aube de turbine, a structure colonnaire avec des colonnes espacees

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0765951A2 (de) * 1995-09-26 1997-04-02 United Technologies Corporation Verschleissfeste keramische Beschichtung
EP0897020A1 (de) * 1997-07-29 1999-02-17 Pyrogenesis Inc. Endabmessungsnahe Mehrschichtkomponenten einer Verbrennungsvorrichtung, gemäss des Vakuum-Plasmaspritzverfahrens und Verfahren zu dessen Herstellung
US5897921A (en) * 1997-01-24 1999-04-27 General Electric Company Directionally solidified thermal barrier coating
US6306517B1 (en) * 1996-07-29 2001-10-23 General Electric Company Thermal barrier coatings having an improved columnar microstructure
EP1295964A2 (de) * 2001-09-24 2003-03-26 Siemens Westinghouse Power Corporation Wärmesperrschicht mit Doppelmikrostruktur

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0765951A2 (de) * 1995-09-26 1997-04-02 United Technologies Corporation Verschleissfeste keramische Beschichtung
US6306517B1 (en) * 1996-07-29 2001-10-23 General Electric Company Thermal barrier coatings having an improved columnar microstructure
US5897921A (en) * 1997-01-24 1999-04-27 General Electric Company Directionally solidified thermal barrier coating
EP0897020A1 (de) * 1997-07-29 1999-02-17 Pyrogenesis Inc. Endabmessungsnahe Mehrschichtkomponenten einer Verbrennungsvorrichtung, gemäss des Vakuum-Plasmaspritzverfahrens und Verfahren zu dessen Herstellung
EP1295964A2 (de) * 2001-09-24 2003-03-26 Siemens Westinghouse Power Corporation Wärmesperrschicht mit Doppelmikrostruktur

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012004525A1 (fr) 2010-07-06 2012-01-12 Snecma Barriere thermique pour aube de turbine, a structure colonnaire avec des colonnes espacees
JP2013543073A (ja) * 2010-07-06 2013-11-28 スネクマ 間隔を空けて配置された柱を備える柱状構造を有しているタービンの羽根用の断熱層

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