EP0776985A1 - Procédé de disposition d'une couche métallique d'adhérence pour des couches isolantes sur articles métalliques - Google Patents

Procédé de disposition d'une couche métallique d'adhérence pour des couches isolantes sur articles métalliques Download PDF

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Publication number
EP0776985A1
EP0776985A1 EP96810768A EP96810768A EP0776985A1 EP 0776985 A1 EP0776985 A1 EP 0776985A1 EP 96810768 A EP96810768 A EP 96810768A EP 96810768 A EP96810768 A EP 96810768A EP 0776985 A1 EP0776985 A1 EP 0776985A1
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EP
European Patent Office
Prior art keywords
metallic
layer
binder
adhesive
powder
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.)
Granted
Application number
EP96810768A
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German (de)
English (en)
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EP0776985B1 (fr
Inventor
Reinhard Fried
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General Electric Switzerland GmbH
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ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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Publication of EP0776985A1 publication Critical patent/EP0776985A1/fr
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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
    • 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
    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • Y10T428/12049—Nonmetal component
    • Y10T428/12056—Entirely inorganic
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • Y10T428/12063—Nonparticulate metal component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • Y10T428/12063—Nonparticulate metal component
    • Y10T428/12097—Nonparticulate component encloses particles

Definitions

  • the invention relates to the field of materials technology. It relates to a method for applying a metallic adhesive layer for thermally sprayed ceramic thermal barrier coatings (TBC) to metallic components and to a metallic adhesive layer produced using this method.
  • TBC thermally sprayed ceramic thermal barrier coatings
  • the ceramic thermal insulation layers protect the coated metallic components from harmful thermal stresses, their complete presence is important for a sufficient service life of the components.
  • Components coated in this way are used in particular in the field of combustion technology, for example for combustion chamber parts or gas turbine blades.
  • the disadvantage of the metallic adhesive layers produced so far for ceramic thermal insulation layers is that they have insufficient roughness and therefore offer too little positive locking (undercuts), so that the layer thickness of the TBC layers is limited.
  • Layer thicknesses of approximately 0.2 to 0.4 mm are known, layer thicknesses of approximately 0.3 mm being most frequently encountered. If they are thicker, the risk of flaking increases rapidly. If they are thinner, the thermal insulation effect quickly diminishes.
  • recent developments are aimed at spraying coarse adhesive layers (approx. 0.6 mm), the necessary positive locking is missing.
  • a roughness typical of known metallic adhesive layers is around 30 ⁇ m.
  • the layers cannot be sprayed rougher, since the dimension of the powder particles to be melted is limited to approx. 10 to 50 ⁇ m depending on the coating process (different spraying temperatures and spray speeds) and the liquid powder particles flatten out when they hit the substrate (cf. B. Heine: " Thermally sprayed layers ", metal, 49th year, 1/1995, p.51-57).
  • the layer thickness of the TBC ceramic layer can be increased by low-speed flame spraying, but such layers cannot withstand thermal shock.
  • the invention tries to avoid all these disadvantages. It is based on the object of developing a metallic adhesive layer and a method for applying this adhesive layer for ceramic thermal insulation layers on a metallic base body, with which it is possible compared to the known prior art to subsequently thermally spray and fix ceramic thermal insulation layers of greater thickness.
  • the layers should adhere stably and be insensitive to impact.
  • the advantages of the invention include that these processes produce adhesive layers that are very rough compared to the prior art.
  • the soldered or sintered metal powder particles represent very stable and form-fitting anchors for the TBC layer to be sprayed on, so that comparatively thick, stably adhering ceramic thermal insulation layers can be produced.
  • the two powders are first mixed intensively and then this mixture is applied to the metallic surface of the base material. This results in a more uniform distribution of the powder particles and also shortens the process time.
  • a thin layer of the adhesive powder is additionally applied to the adhesive layer by means of spraying processes, for example protective gas plasma spraying.
  • spraying processes for example protective gas plasma spraying.
  • solder material material of the same type as the base material and boron-free or low-boron solders are advantageously used as solder material. This reduces possible brittle phase formation.
  • the method according to the invention can be used locally for repair purposes as well as for coating new parts.
  • the metallic adhesive layer produced according to the invention consists of a solder layer wetting the surface of the metallic component with spherical or spiky adhesive powder particles firmly soldered therein, or additionally of a thin sprayed, in particular protective gas plasma-sprayed layer of the same type of material as the adhesive powder particles or of a layer onto the surface of the metallic component protective gas plasma-sprayed protective layer with adhesive powder particles sintered onto its surface.
  • This metallic adhesive layer guarantees stable adhesion of the thermally sprayed ceramic thermal insulation layers, allows greater layer thicknesses and leads to good emergency running properties.
  • the height of the adhesive powder particles is approximately as large as the layer thickness of the ceramic thermal insulation layer to be sprayed on. This makes the layer almost insensitive to impacts, because impacts are essentially absorbed by metal.
  • a guide vane of a gas turbine as an example of a metallic component 1 to be coated. It consists of the metallic base material (substrate) 2, in this case the alloy IN 939 with the following chemical composition: Bal. Ni; 22.5% Cr; 19.0% Co; 2.0% W; 1.0% Nb; 1.4% Ta; 3.7% Ti; 1.9% Al; 0.1 Zr; 0.01 B; 0.15 C.
  • the blade is provided with a corrosion and oxidation layer on the gas-carrying surfaces (MCrAlY, e.g. SV201473: Bal. Ni; 25% Cr; 5% Al; 2.5% Si; 0.5% Y; 1 % Ta).
  • this blade is coated on the leading edge, the pressure side of the blade and on the channel walls with an approximately 0.3 mm thick thermal insulation layer made of ytrium-stabilized zirconium oxide with the following composition: Bal. ZrO 2 incl 2.5% HfO 2 ; 7-9% Y 2 O 3 ; ⁇ 3% others.
  • the gas turbine guide vane After an operating time of 25,000 hours, the gas turbine guide vane is reconditioned. It is ascertained that the thermal insulation layer is no longer present due to thermal overloading and erosion at the leading edge of the sheet and on the channel wall (see hatched areas in FIG. 1). Since the shovel did no further damage is not a total re-coating for cost reasons, but a partial repair of the thermal insulation layer is sought. Due to the fact that a particularly strong attack of the TBC occurs systematically at the points described above, the TBC layer should not only be of the same thickness, but should be made as thick as possible.
  • the ceramic layer is more flexibly bonded to the metallic substrate 2 by grading the transition between metal and ceramic using a special adhesive layer.
  • the blade 1 is cleaned of coarse dirt (combustion residues) in the water vapor jet. Then any adhering deposits are removed using soft sandblasting (e.g. fine aluminum powder, 2 bar blasting pressure, 20 cm distance). The still intact ceramic thermal insulation layer must not be removed.
  • soft sandblasting e.g. fine aluminum powder, 2 bar blasting pressure, 20 cm distance.
  • the blade parts that are not to be coated are covered, for example with a sheet metal template, and the surfaces to be coated are blasted (e.g. fine silicon carbide, blasting pressure 4 bar, distance 40 mm), so that any TBC residues and any oxides are removed.
  • a sheet metal template e.g. fine silicon carbide, blasting pressure 4 bar, distance 40 mm
  • the alloy NB 150 (Bal.Ni; 15% Cr; 3.5% B; 0.1% C) is used as the solder material a melting point of 1055 ° C and a soldering range of 1065 to 1200 ° C used.
  • approximately equal amounts by weight of adhesive powder 4 and solder powder 5 are advantageous. Of course, other proportions can also be selected.
  • the packing density of the particles is not of crucial importance, because dense packing is suitable, but less dense packing is also sufficient.
  • FIG. 2 shows schematically a cross section of the different layers after application.
  • the surface coated in this way can now be brought into the soldering furnace horizontally, vertically or overhead.
  • the solder 5 and the adhesive powder 4 remain in place until the solder has melted and has wetted and soldered the substrate surface and the surface of the adhesive powder particles.
  • the soldering is carried out in a high vacuum oven at 5x10 -6 mbar, 1080 ° C and a holding time of 15 min.
  • Fig. 3 shows schematically a cross section of the different layers after the soldering process.
  • the solder 5 has completely wetted the surface to be repaired and the adhesive powder particles 4 are firmly soldered.
  • the surface looks metallic matt silvery shiny.
  • the diffusion zone is only very small due to the short soldering time and the relatively low soldering temperature.
  • the blade is again covered with a template and provided with a 0.5 mm thick ceramic thermal insulation layer 6, here made of calcium-stabilized zirconium oxide (MetaCeram 28085), the zirconium oxide being applied using a known flame spraying process.
  • a ceramic thermal insulation layer 6 here made of calcium-stabilized zirconium oxide (MetaCeram 28085), the zirconium oxide being applied using a known flame spraying process.
  • Fig. 4 shows schematically the layer structure according to the flame spraying process.
  • the fastening of the zirconium oxide can be compared to a push button technique.
  • the zirconium oxide has a strong form fit and many undercuts, in contrast to conventional adhesive geometries, which at best only have a small form fit.
  • the anchoring of the zirconium oxide (TBC) layer on the component is very stable.
  • flame spraying is therefore also suitable for spraying the TBC layers onto the adhesive layers according to the invention. The latter has the advantage that portable coating devices can be used for this.
  • Another advantage of the invention is the high thermal shock resistance of the layers.
  • Process-coated metallic component 1 was then thermocycled in a hot gas stream (heating at about 50 degrees / min gas temperature, 2 minutes holding at 1000 ° C., cooling at 100 degrees / s gas temperature to 500 ° C.). Even after 70 cycles, the layer has not yet come off.
  • Another advantage is the excellent emergency running properties of the TBC layers thermally sprayed onto the adhesive layer according to the invention.
  • the ceramic layer 6, in this case the zirconium oxide only flakes off above the adhesive powder 4. Due to the large positive fit, the TBC layer 6 does not fall out between the adhesive powder particles 4, so that the ceramic thermal insulation layer 6 is retained at least in the thickness of the adhesive powder particles 4 (approx. 200 ⁇ m). This is shown schematically in FIG. 5. This result leads to the assumption that both the leading edge and the The duct wall of the repaired guide vane can withstand the removal of the thermal insulation layer longer than the thinner and less anchored original thermal insulation layer.
  • Fig. 6 shows a perspective view of a thermal insulation panel for hot gas flow, which is to be provided in the new state with a thermally sprayed thermal insulation layer as thick as possible.
  • the thermal insulation board consists of the alloy MAR M 247, which has the following chemical composition: Bal. Ni; 8.2-8.6% Cr; 9.7-10.3% Co; 0.6-0.8% Mo; 9.8-10.2% W; 2.9-3.1% Ta; 5.4-5.6% Al; 0.8-1.2% Ti; 1.0-1.6% Hf; 0.14-0.16% C).
  • the metallic component 1 to be coated is blasted with relatively coarse silicon carbide (particle diameter ⁇ 200 ⁇ m) in an oxide-free and rough manner (10 to 30 ⁇ m).
  • the surface to be coated is then thinly coated with organic binder 3, for example with a brush.
  • Under a trickling device for coarse spherical adhesive powder 4 (SV 20 14 73 with the following chemical composition: Bal.Ni; 25% Cr; 5% Al; 2.5% Si; 0.5% Y; 1% Ta) with a grain diameter of
  • the plate 1 to be coated is moved back and forth 150 to 300 ⁇ m until a uniform distribution of the highly corrosion-resistant adhesive powder 4 has taken place on the adhesive layer.
  • the individual powder particles should be 0.3 to 0.6 mm apart.
  • Amdry Alloy DF 5 which has a high Al content with a slightly reduced B content in addition to the high Cr content, is selected as the solder.
  • the exact composition is as follows: Bal. Ni; 13% Cr; 3% Ta; 4% Al; 2.7% B; 0.02% Y.
  • the solder 5 is also applied evenly to the surface to be soldered using a suitable trickling device. It is also possible to mix adhesive powder 4 and solder 5 and then to sprinkle the mixture onto the surface coated with the cement binder 3 in one process step.
  • the soldering takes place in a high vacuum oven at 1100 ° C and 15 min holding time.
  • a thin layer 7 (approx. 50 ⁇ m) SV 20 14 73 is applied by means of protective gas plasma spraying.
  • this also results in fine toothing, which further increases the adhesive strength of thick TBC layers in thermal shock.
  • Fig. 7 shows schematically the formation of these layers.
  • a 1.5 mm thick ytrium-stabilized zirconium oxide layer is then sprayed as a TBC layer 6 using a known air plasma spraying method.
  • the component coated in this way proved to be resistant to thermal shock in a thermal shock test in a sand bed (1000 ° C. to room temperature).
  • a cooled guide vane made of the material CM 247 LC DS (chemical composition: Ba. Ni; 8.1% Cr; 9.2% Co; 0.5% Mo; 9.5% W; 3.2% Ta; 0.7% Ti; 5.6% Al; 0.01% Zr; 0.01% B; 0.07% C; 1.4% Hf), can be provided with a 0.7 to 0.8 mm thick TBC layer when new.
  • the blade is coated with the powder ProXon 21031 (nickel-based alloy) in the entire channel area using protective gas plasma spraying, about 0.2 mm thick (sprayed with low oxygen).
  • This powder has excellent resistance to oxidation and corrosion due to its high aluminum and chromium content.
  • a thin layer of binder 3 is applied to this roughly sprayed oxidation and corrosion protection layer 8.
  • a coarse adhesive powder 4 with a particle diameter of approximately 100 to 200 ⁇ m of the same composition is sprinkled on it.
  • the coating is then carried out in a high vacuum furnace under solution annealing conditions for CM 247 LS DS (several hours at 1220 to 1250 ° C).
  • the profile suction side and the areas of the cooling air holes in the guide vane are then covered.
  • the pressure side and the channel walls, which are coated with adhesive layer powder 4 are now coated using a known flame spraying system CastoDyn DS 8000 with MetaCeram 28085 (zirconium oxide / calcium stabilized) approx. 0.8 to 0.7 mm thick.
  • a cooled guide vane made of CM 247 LC DS is also to be provided with a thermal barrier coating.
  • a solder of the same type is used for soldering the coarse adhesive powder particles 4 made of ProXon 21031 4 CM 247 with an addition of 6% Cr; 3% Si; 2% Al and 0.5% B used.
  • the order is placed as described above, i.e.
  • the 150 to 200 ⁇ m adhesive powder 4 is sprinkled on the thin cement-binder layer 3 and the solder powder 5 in abundance.
  • the blade is then subjected to a heat treatment in which the base material 2 is solution-annealed and the solder 5 is partially melted .
  • An approximately 0.5 to 0.6 mm thick, Y-stabilized zirconium oxide thermal insulation layer is then applied to this blade surface prepared on the profile pressure side and the channel walls using a known air plasma spraying process.
  • thermal shock tests showed that the thermal insulation layer fastened in this way is superior to a conventionally produced layer. Even if a piece of the TBC layer bursts off for various reasons, this layer remains between the adhesive powder particles and thus guarantees good emergency running properties. If, on the other hand, the TBC layer flakes off in the case of conventionally coated blades, only minimal residues remain on the substrate, which in no case have a heat-insulating property. In addition, this example has shown that it is cheap to use boron-free or almost boron-free Solder to be used, since brittle phase formation with W-borides is hardly possible.
  • FIG. 9 finally shows a micrograph of a plate coated with the adhesive layer according to the invention.
  • the base material 2 is MAR M 247, NB 150 was used as lot 5 and the adhesive powder particles 4 consist of NiAl95 / 5.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Insulated Metal Substrates For Printed Circuits (AREA)
  • Ceramic Products (AREA)
  • Laminated Bodies (AREA)
EP96810768A 1995-12-02 1996-11-11 Procédé de disposition d'une couche métallique d'adhérence pour des couches isolantes sur articles métalliques Expired - Lifetime EP0776985B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19545025 1995-12-02
DE19545025A DE19545025A1 (de) 1995-12-02 1995-12-02 Verfahren zur Aufbringung einer metallischen Haftschicht für keramische Wärmedämmschichten auf metallische Bauteile

Publications (2)

Publication Number Publication Date
EP0776985A1 true EP0776985A1 (fr) 1997-06-04
EP0776985B1 EP0776985B1 (fr) 2001-12-19

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EP96810768A Expired - Lifetime EP0776985B1 (fr) 1995-12-02 1996-11-11 Procédé de disposition d'une couche métallique d'adhérence pour des couches isolantes sur articles métalliques

Country Status (11)

Country Link
US (1) US5894053A (fr)
EP (1) EP0776985B1 (fr)
JP (1) JP3983323B2 (fr)
CN (1) CN1161489C (fr)
AT (1) ATE211185T1 (fr)
CA (1) CA2188614C (fr)
CZ (1) CZ290920B6 (fr)
DE (2) DE19545025A1 (fr)
PL (2) PL182552B1 (fr)
RU (1) RU2209256C2 (fr)
UA (1) UA42001C2 (fr)

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EP1491657A1 (fr) * 2003-06-26 2004-12-29 ALSTOM Technology Ltd Méthode d'application d'un système de couches
EP1867749A1 (fr) * 2006-06-12 2007-12-19 Siemens Aktiengesellschaft Procédé de revêtement d'un matériau à une pièce
CN102127729A (zh) * 2011-02-18 2011-07-20 湖北工业大学 一种金属材料表面热喷涂涂层的钎焊强化方法
EP2034132A3 (fr) * 2007-09-06 2011-07-20 United Technologies Corporation Segment de virole avec joint d'étanchéité et procédé de fabrication associé
EP2460981A1 (fr) * 2010-12-01 2012-06-06 BBAT Berlin Brandenburg Aerospace Technology AG Revêtement d'isolation thermique pour un moteur de turbine à gaz
DE10332938B4 (de) * 2003-07-19 2016-12-29 General Electric Technology Gmbh Thermisch belastetes Bauteil einer Gasturbine

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JP3302589B2 (ja) * 1997-02-06 2002-07-15 株式会社日立製作所 セラミック被覆ガスタービン動翼
TW587967B (en) 2000-04-14 2004-05-21 Emitec Emissionstechnologie Housing with passivation layer and method for the production of a catalyst support structure with such a housing
US6279811B1 (en) 2000-05-12 2001-08-28 Mcgraw-Edison Company Solder application technique
DE10057187B4 (de) * 2000-11-17 2011-12-08 Alstom Technology Ltd. Verfahren für die Herstellung von Verbundaufbauten zwischen metallischen und nichtmetallischen Materialien
DE10117128A1 (de) * 2001-04-06 2002-10-10 Alstom Switzerland Ltd Verfahren zur Herstellung von Verbundaufbauten zwischen metallischen und nichtmetallischen Materialien
DE10117127B4 (de) * 2001-04-06 2009-12-31 Alstom Technology Ltd. Verbundaufbau zwischen metallischen und nichtmetallischen Materialien
DE10121019A1 (de) * 2001-04-28 2002-10-31 Alstom Switzerland Ltd Gasturbinendichtung
FR2827308B1 (fr) * 2001-07-12 2004-05-14 Snecma Moteurs Procede de reparation globale d'une piece revetue d'une barriere thermique
EP1275748A3 (fr) 2001-07-13 2004-01-07 ALSTOM (Switzerland) Ltd Revêtement resistant aux temperatures elevées avec des bosses localles enrobées et son procédé de fabrication
DE50202696D1 (de) 2001-08-14 2005-05-12 Alstom Technology Ltd Baden Verfahren zur Bearbeitung einer beschichteten Gasturbinenschaufel
EP1327702A1 (fr) 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Revêtement de liaison de type MCrAlY et procédé de depôt de ce revêtement de liason de type MCrAlY
US6679680B2 (en) * 2002-03-25 2004-01-20 General Electric Company Built-up gas turbine component and its fabrication
US7066235B2 (en) * 2002-05-07 2006-06-27 Nanometal, Llc Method for manufacturing clad components
US6759151B1 (en) 2002-05-22 2004-07-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Multilayer article characterized by low coefficient of thermal expansion outer layer
US6733908B1 (en) 2002-07-08 2004-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Multilayer article having stabilized zirconia outer layer and chemical barrier layer
EP1411210A1 (fr) * 2002-10-15 2004-04-21 ALSTOM Technology Ltd Méthode de déposition d'un revêtement de type MCrAlY résistant à la fatigue et à l'oxydation
US7338699B2 (en) 2002-10-31 2008-03-04 Tosoh Corporation Island projection-modified part, method for producing the same, and apparatus comprising the same
EP1422054A1 (fr) * 2002-11-21 2004-05-26 Siemens Aktiengesellschaft Structure laminée pour de turbine à gaz
EP1437426A1 (fr) * 2003-01-10 2004-07-14 Siemens Aktiengesellschaft Procédé de production des structures monocristallines
DE10357180A1 (de) * 2003-12-08 2005-06-30 Alstom Technology Ltd Verbundaufbau zwischen metallischen und nichtmetallischen Materialien
US20050238894A1 (en) * 2004-04-22 2005-10-27 Gorman Mark D Mixed metal oxide ceramic compositions for reduced conductivity thermal barrier coatings
EP1645653A1 (fr) * 2004-10-07 2006-04-12 Siemens Aktiengesellschaft Revêtement protecteur
US7378132B2 (en) * 2004-12-14 2008-05-27 Honeywell International, Inc. Method for applying environmental-resistant MCrAlY coatings on gas turbine components
US20060222776A1 (en) * 2005-03-29 2006-10-05 Honeywell International, Inc. Environment-resistant platinum aluminide coatings, and methods of applying the same onto turbine components
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US20100047526A1 (en) * 2008-08-19 2010-02-25 Merrill Gary B Subsurface inclusions of spheroids and methodology for strengthening a surface bond in a hybrid ceramic matrix composite structure
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EP1491657A1 (fr) * 2003-06-26 2004-12-29 ALSTOM Technology Ltd Méthode d'application d'un système de couches
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DE59608498D1 (de) 2002-01-31
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JP3983323B2 (ja) 2007-09-26
DE19545025A1 (de) 1997-06-05
CN1160088A (zh) 1997-09-24
CA2188614A1 (fr) 1997-06-03
CA2188614C (fr) 2005-10-04
ATE211185T1 (de) 2002-01-15
PL182552B1 (pl) 2002-01-31
PL317298A1 (en) 1997-06-09
CZ290920B6 (cs) 2002-11-13
CN1161489C (zh) 2004-08-11
RU2209256C2 (ru) 2003-07-27
JPH09176818A (ja) 1997-07-08
EP0776985B1 (fr) 2001-12-19
PL181404B1 (pl) 2001-07-31
US5894053A (en) 1999-04-13

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