WO1999067438A1 - Procede de realisation d'un blindage pour un composant metallique - Google Patents

Procede de realisation d'un blindage pour un composant metallique Download PDF

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Publication number
WO1999067438A1
WO1999067438A1 PCT/DE1999/001753 DE9901753W WO9967438A1 WO 1999067438 A1 WO1999067438 A1 WO 1999067438A1 DE 9901753 W DE9901753 W DE 9901753W WO 9967438 A1 WO9967438 A1 WO 9967438A1
Authority
WO
WIPO (PCT)
Prior art keywords
slip
particles
component
carried out
layer
Prior art date
Application number
PCT/DE1999/001753
Other languages
German (de)
English (en)
Inventor
Gerhard Wydra
Original Assignee
MTU MOTOREN- UND TURBINEN-UNION MüNCHEN 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 MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH filed Critical MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH
Priority to JP2000556077A priority Critical patent/JP2002518600A/ja
Priority to DE59901139T priority patent/DE59901139D1/de
Priority to EP99939334A priority patent/EP1097249B1/fr
Publication of WO1999067438A1 publication Critical patent/WO1999067438A1/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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/18—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
    • C23C10/26—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions more than one element being diffused

Definitions

  • the invention relates to a method for producing armoring for a metallic component which is provided on the surface thereof.
  • Armouring or brushing contributions are e.g. on engine components, e.g. Sealing tips of labyrinth seals or blade tips, intended to counteract their processing during brushing operations during operation. Since the efficiency of a compressor or a turbine depends to a large extent on the gap size between the rotating and the stationary component, it is increased with increasing processing, e.g. the blade tips, reduced.
  • the armor usually works itself into an inlet lining of an opposing, second component during operation of the engine.
  • Such run-in coverings can be rubbed off and usually consist of a corrosion and erosion-resistant layer.
  • Armoring of the engine component is particularly necessary if the strength and hardness of the inlet linings are increased to increase the erosion and temperature resistance and the processing of the engine components is additionally increased.
  • the armor ensures that a minimal gap is formed between the armor and the run-in coating during the brushing process.
  • an MCrAlY powder is applied to the component to be armored by galvanic application, w c- in the bath the necessary hard particles, such as e.g. BN, are included. These particles are etched free after application. Such a process is expensive and complex. The subsequent etching in particular is disadvantageous due to the lack of environmental compatibility and the necessary covering of the material.
  • a solder foil adapted to the component contour is attached to the component by gluing or the like. Then BN particles are inserted into the solder foil. The solder foil is then melted by heat treatment and the BN particles embedded therein. This procedure is also reasonably expensive and complex. In addition, the connection between the particles and the component is insufficient.
  • JP 55-82765 A it is known to first coat the substrate consisting of a Ni or Co-based alloy with a mixture of ceramic, Al and metal powder in order to improve the heat resistance of the long-term exposure to high temperature . This is followed by a layer of a Ni powder provided with a binder, a heat treatment and the alitation by a packing process.
  • the first layer of the ceramic-containing mixture is intended to prevent Al from penetrating into the substrate from the layer and the layer consequently losing its heat resistance due to the depletion of Al.
  • JP 55-082759 A discloses a method for improving the thermal resistance of a coating which is applied to a substrate made of a Ni or Co-based alloy, a metal or alloy powder being mixed with ceramic elements during coating and then applied the substrate is applied.
  • a binder can be used and a subsequent heat treatment can be carried out.
  • the method is used for components of e.g. Gas turbines used, which are exposed to hot gas corrosion.
  • the object of the present invention is to provide a method for producing armor of the type described at the outset, which can be carried out as simply as possible in terms of production technology and results in high-quality armor.
  • This object is achieved according to the invention by the steps: producing a slip by mixing a powder containing at least one of the elements Ni or Cr or Ce with a binder; Applying the slip to the surface to be armored; Adding ceramic hard particles to the slip before or after applying the slip, the size of which is selected so that it protrudes over the layer after the alitation; Drying the slip at a temperature from room temperature to 300 ° C; and alitizing the slip layer.
  • the advantage of this method is that the armor can be applied to the component using a simple manufacturing process.
  • the hard, ceramic particles are embedded in the slip layer, which has a void fraction of 0 to 40%, and are firmly connected to the component.
  • the particles are mixed into the slurry before being applied to the surface to be armored. In this way, the particles are evenly distributed in the slurry present in a suspension.
  • the particles are inserted into the slip after application, which means e.g. can achieve a special arrangement of the particles on the surface to be armored.
  • Particles of BN, SiC or ALO are preferably used, since they are harder than the slip layer and can cut into run-in coatings or the like during operation.
  • the slip is made from a powder of MCrAIY, the powder preferably being in a grain size distribution of 5 to 120 ⁇ m.
  • the M stands for at least one of the elements Ni, Co, Pt or Pd. Instead of Y, Hf or Ce can also be used.
  • the slip is preferably applied to the surface of the component to be armored by spraying, brushing or dipping, as a result of which the process can be carried out easily and inexpensively in terms of production technology.
  • spraying brushing or dipping
  • locally delimited layers can also be applied in a simple manner to geometrically complex components.
  • no expensive and complex spraying or evaporation systems are required
  • Drying of the slip, which is present in a suspension together with the organic or inorganic binder, is preferred for 0.5-4 hours carried out, a duration of 1 - 2 hours has proven to be particularly advantageous.
  • the slip layer is heat-treated at a temperature of 750 to 1200 ° C. in argon or vacuum, the heat treatment of the layer preferably being carried out for 1-4 hours in order to connect the slip layer to the component by diffusion.
  • the final step of alitizing the layer is carried out at a temperature between 800 and 1200 ° C. and for a period of 1-12 hours.
  • the metallic component preferably consists of an alloy based on nickel or cobalt, the component being an engine component, e.g. a turbine blade, the armor is applied to the tip of the blade.
  • an MCrAlY powder is first mixed into a suspension with a customary inorganic binder to produce a slip.
  • the MCrAlY powder is present in the suspension with 80-90% by weight, the binder with 5-10% by weight and additionally water with 5-7% by weight.
  • the grain sizes of the particles of the MCrAlY powder are between 5 and 120 ⁇ m.
  • BN particles with a size larger than that of the MCrAlY powder particles are introduced into this flowable and sprayable mass.
  • the blade tip of a turbine blade made of a nickel-based alloy is then immersed in the mass in such a way that a slip layer forms on the blade tip to be armored.
  • the slip containing the particles could also be applied, for example, with a brush to form a layer on the Blade tip to be applied.
  • the still moist slurry or the slip layer present in a suspension is dried at room temperature for about 1.5 hours.
  • the dried slip layer is then heat-treated in a vacuum at 1000 ° C. for 1 hour in order to achieve a bond between the slip layer and the material of the turbine blade by diffusion. Subsequently, the layer is alitated at about 1,100 ° C. for 4 hours using a conventional method in order to further strengthen the connection of the engine blade by diffusion and to compact the slip layer.
  • AI penetrates the layer and the base material of the turbine blade and ensures both a firm connection of the layer with the component and a firm connection of the spherical MCrAlY particles with each other.
  • the spherical MCrAlY particles sinter together at least partially.
  • Ni can also escape from the base material and diffuse into the slip layer.
  • the hard, ceramic particles of BN or the like protrude outward beyond the slip layer and can protect them and the blade tip during operation.
  • the BN particles are firmly connected to the blade tip via the slip layer and can cut into an opposing inlet lining during the operation of the gas turbine, in order to prevent damage to the blade tip and the gap size between the rotating and the stationary component as far as possible to keep low.

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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé permettant de réaliser un blindage destiné à un composant métallique, par exemple une pointe d'aube de turbine, ce blindage devant être réalisé sur la surface concernée dudit composant. Ce procédé est simple en ce qui concerne la technique de production et bon marché en ce qui concerne sa réalisation, et il comporte les étapes suivantes: production d'une barbotine par mélange d'une poudre contenant au moins un des éléments Ni, Cr ou Ce avec un liant; application de la barbotine sur la surface à blinder; adjonction de particules céramiques avant ou après l'application de la barbotine; séchage de la barbotine à une température comprise entre la température ambiante et 300 °C; et calorisation de la couche de barbotine.
PCT/DE1999/001753 1998-06-20 1999-06-16 Procede de realisation d'un blindage pour un composant metallique WO1999067438A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
JP2000556077A JP2002518600A (ja) 1998-06-20 1999-06-16 金属製部材用被覆の製造方法
DE59901139T DE59901139D1 (de) 1998-06-20 1999-06-16 Verfahren zur herstellung einer panzerung für ein metallisches bauteil
EP99939334A EP1097249B1 (fr) 1998-06-20 1999-06-16 Procede de realisation d'un blindage pour un composant metallique

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19827620.6 1998-06-20
DE19827620A DE19827620C2 (de) 1998-06-20 1998-06-20 Verfahren zum Herstellen einer Panzerung für ein metallisches Bauteil und dessen Verwendung

Publications (1)

Publication Number Publication Date
WO1999067438A1 true WO1999067438A1 (fr) 1999-12-29

Family

ID=7871567

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1999/001753 WO1999067438A1 (fr) 1998-06-20 1999-06-16 Procede de realisation d'un blindage pour un composant metallique

Country Status (5)

Country Link
EP (1) EP1097249B1 (fr)
JP (1) JP2002518600A (fr)
DE (2) DE19827620C2 (fr)
ES (1) ES2176013T3 (fr)
WO (1) WO1999067438A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19946650C2 (de) * 1999-09-29 2003-11-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Panzerung für ein metallisches Bauteil
US7314674B2 (en) * 2004-12-15 2008-01-01 General Electric Company Corrosion resistant coating composition, coated turbine component and method for coating same
US7601400B2 (en) * 2005-03-10 2009-10-13 General Electric Company Liquid electrostatic coating composition comprising corrosion resistant metal particulates and method for using same
DE102005055200A1 (de) * 2005-11-19 2007-05-24 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Einlaufbelags
DE102006028297A1 (de) * 2006-06-20 2007-12-27 Mtu Aero Engines Gmbh Verfahren zur Reparatur von Einlaufbelägen
DE102007003735B4 (de) * 2007-01-25 2010-07-01 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schutzbeschichtung sowie Schutzbeschichtung
DE102009008510A1 (de) * 2009-02-11 2010-08-12 Mtu Aero Engines Gmbh Beschichtung und Verfahren zum Beschichten eines Werkstücks
DE102014222024A1 (de) * 2014-10-29 2016-06-16 MTU Aero Engines AG Schlicker und Verfahren zur Herstellung einer Oxidations- und Korrosionsbeständigen Diffusionschicht
DE102015213555A1 (de) * 2015-07-20 2017-03-09 MTU Aero Engines AG Dichtrippenpanzerung und Verfahren zur Herstellung derselben
DE102015221482A1 (de) * 2015-11-03 2017-05-04 MTU Aero Engines AG Diffusionsschichten

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2244011A1 (fr) * 1973-09-19 1975-04-11 Rolls Royce
FR2397468A1 (fr) * 1977-07-14 1979-02-09 Fiat Spa Procede de preparation de revetements protecteurs pour metaux et alliages metalliques destines a etre utilises a temperatures elevees
DE2910962B1 (de) * 1979-03-21 1980-09-25 Josef Adam Verfahren zum Aufbringen einer matrixbildenden metallischen darin eingebetteten Schicht mit verschleissfestem Material auf einen Traeger
JPS58197203A (ja) * 1982-05-12 1983-11-16 Toshiba Corp 耐摩耗性被覆層の形成方法
JPS6089503A (ja) * 1983-10-21 1985-05-20 Toshiba Mach Co Ltd 耐摩耗材の被覆方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2244011A1 (fr) * 1973-09-19 1975-04-11 Rolls Royce
FR2397468A1 (fr) * 1977-07-14 1979-02-09 Fiat Spa Procede de preparation de revetements protecteurs pour metaux et alliages metalliques destines a etre utilises a temperatures elevees
DE2910962B1 (de) * 1979-03-21 1980-09-25 Josef Adam Verfahren zum Aufbringen einer matrixbildenden metallischen darin eingebetteten Schicht mit verschleissfestem Material auf einen Traeger
JPS58197203A (ja) * 1982-05-12 1983-11-16 Toshiba Corp 耐摩耗性被覆層の形成方法
JPS6089503A (ja) * 1983-10-21 1985-05-20 Toshiba Mach Co Ltd 耐摩耗材の被覆方法

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 008, no. 043 (M - 279) 24 February 1984 (1984-02-24) *
PATENT ABSTRACTS OF JAPAN vol. 9, no. 235 (M - 415) 21 September 1985 (1985-09-21) *

Also Published As

Publication number Publication date
EP1097249B1 (fr) 2002-04-03
ES2176013T3 (es) 2002-11-16
JP2002518600A (ja) 2002-06-25
DE19827620A1 (de) 1999-12-23
EP1097249A1 (fr) 2001-05-09
DE59901139D1 (de) 2002-05-08
DE19827620C2 (de) 2003-12-18

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