EP1088907B1 - Procédé de réalisation d'un blindage pour un composant métallique - Google Patents

Procédé de réalisation d'un blindage pour un composant métallique Download PDF

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Publication number
EP1088907B1
EP1088907B1 EP00120803A EP00120803A EP1088907B1 EP 1088907 B1 EP1088907 B1 EP 1088907B1 EP 00120803 A EP00120803 A EP 00120803A EP 00120803 A EP00120803 A EP 00120803A EP 1088907 B1 EP1088907 B1 EP 1088907B1
Authority
EP
European Patent Office
Prior art keywords
slurry
layer
powder
component
application
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.)
Expired - Lifetime
Application number
EP00120803A
Other languages
German (de)
English (en)
Other versions
EP1088907A1 (fr
Inventor
Thomas Dr. Cosack
Gerhard Wydra
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1088907A1 publication Critical patent/EP1088907A1/fr
Application granted granted Critical
Publication of EP1088907B1 publication Critical patent/EP1088907B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • C23C10/54—Diffusion of at least chromium
    • C23C10/56—Diffusion of at least chromium and at least aluminium
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step

Definitions

  • the invention relates to a method for producing an armor for a metallic Component provided on its surface.
  • Armor or scratches are e.g. on engine components, e.g. seal tips of labyrinth seals or blade tips, provided to their Counteract processing during touch-ups during operation. Since the Efficiency of a compressor or turbine to a large extent on the gap size between the rotating and the stationary component, he is with increasing processing, e.g. the blade tips, reduced.
  • engine components e.g. seal tips of labyrinth seals or blade tips
  • the armor works in the operation of the engine usually in an inlet lining an opposite, second component.
  • Such inlet linings are abradable and usually consist of a corrosion and erosion resistant layer.
  • An armor of the engine component is required in particular when the Strength and hardness of the inlet coverings to increase erosion and temperature resistance is increased and the processing of engine components in addition strengthened. By the armor is achieved that the Anstreifvorgang a minimum Gap between the armor and the inlet lining is formed.
  • an MCrAlY powder is used applied by electroplating on the component to be coated, wherein in the bath, the required hard particles, e.g. BN, are included. These Particles are etched free after application.
  • Such a method is expensive and consuming.
  • the subsequent etching is due to the lack of Environmental compatibility and the required covering of the component disadvantageous.
  • JP 55-82765 A which consists of a Ni or Co base alloy Substrate first with a mixture of ceramic, Al and metal powder To coat, the heat resistance of the long-lasting high temperature loaded Layer to improve. Then follows a layer of one with a Binder provided by Ni powder, a heat treatment and an Alit Schlu by Pack process. In this case, the first layer of the mixture containing ceramic prevent Al from penetrating the layer into the substrate and thus the layer through the depletion of Al loses its heat resistance.
  • JP 55-082759 A discloses a method for improving the thermal resistance a coating applied to a substrate of a Ni or Co base alloy is applied, wherein during coating a metal or an alloy powder mixed with ceramic elements and then applied to the substrate becomes. It can be a binder used and a subsequent heat treatment be performed. The method is applied to components of e.g. Used gas turbines, which are exposed to hot gas corrosion.
  • the object of the present invention is to provide a method for manufacturing To create an armor of the type described above, which is manufacturing technology easy to carry out and a high-quality armor results.
  • the advantage of this method is that the armor with a manufacturing technology simple method can be applied to the component.
  • the hard particles are the Slip before application on the surface to be coated mixed. To this Way, the particles are uniform in the slurry present in a suspension distributed.
  • the hard particles after application in the slip layer is used, resulting e.g. a special arrangement of the particles on the surface to be clad.
  • the starting powder consists of MCrAlY, the starting powder - like the adding powder - preferably in a grain size distribution of 5 to 120 microns is present.
  • the M stands for at least one of the elements Ni or Co. Instead of Y, Hf or Ce can also be used.
  • the application of the slurry on the surface to be coated of the component takes place preferably by spraying, brushing or dipping, whereby the process manufacturing technology easy and inexpensive to do.
  • Applying can be easily localized layers also on geometric Apply complicated components. Moreover, no expensive and elaborate Spraying or evaporation systems required.
  • the slip layer be coated in inert gas, e.g. in argon, or im Vacuum is heat treated, wherein the heat treatment of the layer about 1-4 Hours, preferably over about 2 hours, are performed to the slip layer to connect with the component and the hard particles via diffusion.
  • inert gas e.g. in argon, or im Vacuum is heat treated, wherein the heat treatment of the layer about 1-4 Hours, preferably over about 2 hours, are performed to the slip layer to connect with the component and the hard particles via diffusion.
  • the metallic component is preferably made of a nickel or cobalt-based alloy, wherein the component is an engine building, e.g. a turbine blade, his can, on whose blade tip the armor is applied.
  • the addition powder makes up to 35% by weight of the total weight of starting materials. and adding powder.
  • an MCrAlY powder with an addition powder mixed into a suspension with a conventional inorganic binder In the Suspension is the binder with 5-10 wt .-% and additionally water with 5-7 Wt .-% before.
  • the particle sizes of the powder particles are between 5 and 120 ⁇ m.
  • These flowable and sprayable mass are introduced BN particles whose size is above that of the powder particles.
  • the particle-containing Slip e.g. also with a brush to form a layer on the blade tip be applied.
  • the suspension is in suspension, still moist slurry or the slip layer at room temperature dried for about 1.5 hours.
  • the dried slurry layer is then vacuumed at 1000 ° C for about 2 hours heat treated, in order to connect the slip layer with the material of the Turbine blade and to achieve with the hard particles by diffusion. While sintering the spherical MCrAlY particles at least partially together. In addition, Ni can also escape from the base material and into the Schlikker harsh diffuse. After heat treatment are the ceramic hard particles from BN od. Like. Outward on the slip before and can this and protect the blade tip during operation.
  • the BN particles are firmly connected to the blade tip via the slip layer and may during operation of the gas turbine when rubbing in an opposite Cut in the inlet lining to avoid damage in this way To prevent the blade tip and the gap size between the rotating and keep the standing component as low as possible.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
  • Extrusion Moulding Of Plastics Or The Like (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (12)

  1. Procédé de fabrication d'un blindage pour un composant métallique, en particulier pour une aube de turbine, qui est prévu sur la surface du composant, caractérisé par les étapes de : fabrication d'une barbotine en mélangeant une solution de liant comprenant une poudre de départ contenant du Al et/ou du Cr et une poudre d'addition comportant au moins un élément appartenant au groupe de Al, Pt, Pd ou Si, la poudre d'addition, lorsqu'une poudre de départ ne contient que du Al, ne comportant aucun Al ; application de la barbotine sur la surface destinée à être blindée ; addition de particules céramiques dures en BN, SiC ou Al2O3 à la barbotine avant ou après l'application de la barbotine, dont la dimension est sélectionnée de sorte qu'elles dépassent de la couche après le traitement thermique, de sorte qu'en action elles puissent creuser des couches d'usure ou similaires ; séchage de la couche de barbotine à une température allant de la température ambiante jusqu'à 450°C ; et traitement thermique de la couche de barbotine à des températures allant de 750° à 1250°C.
  2. Procédé selon la revendication 1, caractérisé en ce que les particules dures sont mélangées à la barbotine avant l'application.
  3. Procédé selon la revendication 1, caractérisé en ce que les particules dures sont introduites dans la couche de barbotine après l'application.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la poudre de départ est constituée de MCrAIY, M représentant Ni, Co, ou une combinaison de Ni et de Co.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que les poudres comprennent respectivement une distribution granulométrique de 5 à 120 µm.
  6. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que l'application de la barbotine est réalisée par injection, badigeonnage ou trempage.
  7. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le séchage de la couche de barbotine est réalisé pendant 0,5 à 4 heures.
  8. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la couche de barbotine subit un traitement thermique dans un gaz protecteur, par exemple dans l'Argon, ou dans un vide.
  9. Procédé selon la revendication 8, caractérisé en ce que le traitement thermique est réalisé pendant 1 à 4 heures, de préférence pendant approximativement 2 heures.
  10. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le composant est constitué d'un alliage à base de nickel ou de cobalt.
  11. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le composant est une aube de turbine, sur le bout de laquelle est prévu le blindage.
  12. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la poudre d'addition représente jusqu'à 35% en masse du poids total composé des poudres de départ et d'addition.
EP00120803A 1999-09-29 2000-09-23 Procédé de réalisation d'un blindage pour un composant métallique Expired - Lifetime EP1088907B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19946650A DE19946650C2 (de) 1999-09-29 1999-09-29 Verfahren zum Herstellen einer Panzerung für ein metallisches Bauteil
DE19946650 1999-09-29

Publications (2)

Publication Number Publication Date
EP1088907A1 EP1088907A1 (fr) 2001-04-04
EP1088907B1 true EP1088907B1 (fr) 2005-08-10

Family

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Family Applications (1)

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EP00120803A Expired - Lifetime EP1088907B1 (fr) 1999-09-29 2000-09-23 Procédé de réalisation d'un blindage pour un composant métallique

Country Status (3)

Country Link
EP (1) EP1088907B1 (fr)
AT (1) ATE301735T1 (fr)
DE (2) DE19946650C2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009008510A1 (de) * 2009-02-11 2010-08-12 Mtu Aero Engines Gmbh Beschichtung und Verfahren zum Beschichten eines Werkstücks

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004034410A1 (de) * 2004-07-16 2006-02-02 Mtu Aero Engines Gmbh Schutzschicht zum Aufbringen auf ein Substrat und Verfahren zur Herstellung einer Schutzschicht
EP2842662B1 (fr) * 2013-09-03 2020-08-05 MTU Aero Engines GmbH Blindage de pointe pour des aubes en titane
CN109280955A (zh) * 2018-11-20 2019-01-29 沈阳工学院 一种耐高温耐磨MCrAlSiC复合涂层

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FR618485A (fr) * 1926-07-05 1927-03-10 Metallisator Berlin Aktien Ges Procédé pour la production de revêtements en aluminium sur des métaux
BE757636A (fr) * 1969-11-03 1971-04-01 Deutsche Edelstahlwerke Ag Procede de protection en surface pour objets metalliques
US3741791A (en) * 1971-08-05 1973-06-26 United Aircraft Corp Slurry coating superalloys with fecraiy coatings
IT1083665B (it) * 1977-07-14 1985-05-25 Fiat Spa Procedimento per la realizzazione di rivestimenti per alte temperature su metalli e leghe metalliche
JPS5582761A (en) * 1978-12-15 1980-06-21 Hitachi Ltd Coating method for platinum group metal onto cobalt alloy
DE2910962C2 (de) * 1979-03-21 1981-07-02 Josef 4250 Bottrop Adam Verfahren zum Aufbringen einer matrixbildenden metallischen Schicht mit darin eingebettetem verschleißfestem Material auf einen Träger
JPS6089503A (ja) * 1983-10-21 1985-05-20 Toshiba Mach Co Ltd 耐摩耗材の被覆方法
DE3420869C2 (de) * 1984-06-05 1986-11-27 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8900 Augsburg Verfahren zur Herstellung eines metallischen Schutzüberzuges auf metallischen Werkstücken
US4937042A (en) * 1986-11-28 1990-06-26 General Electric Company Method for making an abradable article
DE69109077T2 (de) * 1991-01-31 1995-12-14 Gen Electric Aluminisieren von Gegenständen, geschützt durch ein thermisch gesperrtes Überzugssystem.
US5807428A (en) * 1997-05-22 1998-09-15 United Technologies Corporation Slurry coating system
DE19824792B4 (de) * 1998-06-03 2005-06-30 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Haftschicht für eine Wärmedämmschicht
DE19827620C2 (de) * 1998-06-20 2003-12-18 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Panzerung für ein metallisches Bauteil und dessen Verwendung

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009008510A1 (de) * 2009-02-11 2010-08-12 Mtu Aero Engines Gmbh Beschichtung und Verfahren zum Beschichten eines Werkstücks

Also Published As

Publication number Publication date
DE50010908D1 (de) 2005-09-15
ATE301735T1 (de) 2005-08-15
DE19946650C2 (de) 2003-11-27
DE19946650A1 (de) 2001-09-13
EP1088907A1 (fr) 2001-04-04

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