EP1097249B1 - Verfahren zur herstellung einer panzerung für ein metallisches bauteil - Google Patents
Verfahren zur herstellung einer panzerung für ein metallisches bauteil Download PDFInfo
- Publication number
- EP1097249B1 EP1097249B1 EP99939334A EP99939334A EP1097249B1 EP 1097249 B1 EP1097249 B1 EP 1097249B1 EP 99939334 A EP99939334 A EP 99939334A EP 99939334 A EP99939334 A EP 99939334A EP 1097249 B1 EP1097249 B1 EP 1097249B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- slip
- accordance
- particles
- layer
- alitization
- 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
Links
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 armor for a metal Component that is provided on its surface.
- Armorings or brushed coverings are e.g. on engine components, e.g. seal tips of labyrinth seals or blade tips, provided to their To counteract processing during brushing operations during operation. Since the Efficiency of a compressor or turbine largely depends on the gap size depends between the rotating and the standing component, it will be with increasing processing, e.g. the blade tips, reduced.
- the armor usually works its way into an intake lining when the engine is operating an opposite, second component.
- Such run-in coverings are abradable and mostly consist of a corrosion and erosion-resistant layer. Armoring of the engine component is particularly necessary if the Strength and hardness of the run-in coatings to increase erosion and temperature resistance is increased and the processing of the engine components additionally strengthened.
- the armor ensures that the brushing process is minimal Gap is formed between the armor and the intake coating.
- an MCrAIY powder is used applied by galvanic application to the component to be armored, where the necessary hard particles in the bath, e.g. BN, are included.
- This Particles are etched free after application.
- Such a process is expensive and consuming.
- the subsequent etching is due to the lack Environmental compatibility and the necessary covering of the material disadvantageous.
- a contour adapted to the component contour is used
- the solder foil is attached to the component by gluing or the like.
- BN particles are in the solder foil inserted.
- the solder foil is then melted by heat treatment and the BN particles embedded in it. This procedure is also proportionate expensive and complex. In addition, the connection between the particles and the component is insufficient.
- JP 55-82765 A it is known that consisting of a Ni or Co base alloy Substrate first with a mixture of ceramic, aluminum and metal powder to coat to ensure the heat resistance of the long-term high temperature exposure Improve layer. This is followed by a layer of one with one Binder-provided Ni powder, a heat treatment and the alitation by a Pack process.
- the first layer should consist of the mixture containing ceramics prevent Al from penetrating into the substrate from the layer and hence the layer due to the depletion of Al their heat resistance is reduced.
- JP 55-082759 A discloses a method for improving the thermal resistance a coating that is based on a substrate made of a Ni or Co-based alloy is applied, during coating a metal powder or an alloy powder mixed with ceramic elements and then applied to the substrate becomes. A binder and a subsequent heat treatment can be used be performed. 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 a method for manufacturing to create an armor of the type described at the outset, which can be manufactured can be carried out as easily as possible and high-quality armor results.
- the solution to this problem is characterized according to the invention by the steps: Producing a slip by mixing at least one of the elements Ni or powder containing Cr or Ce with a binder; Apply the slip on the surface to be armored; Add ceramic hard particles to the slip before or after application of the slip, the size of which is chosen so that they protrude over the layer after alitation; Drying the slip at one Temperature from room temperature to 300 ° C; and alitizing the slip layer.
- the advantage of this method is that the armor with a manufacturing technology simple processes can be applied to the component. Also are the hard, ceramic particles in the void fraction from 0 to 40% Slip layer embedded and firmly connected to the component.
- the particles become the slip mixed before application to the surface to be armored. In this way the particles are evenly distributed in the slurry in suspension.
- the particles are applied to the Slip used, e.g. a special arrangement of the particles on the to achieve armored surface.
- Particles of BN, SiC or Al 2 O 3 are preferably used, since these 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 is, the 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, Co, Pt or Pd. Instead of Y, Hf or Ce can also be used.
- the slip is applied to the surface of the component to be armored preferably by spraying, brushing or dipping, which means that the process is manufacturing-related can be carried out easily and inexpensively.
- spraying brushing or dipping
- dipping a means that the process is manufacturing-related can be carried out easily and inexpensively.
- Localized layers can also be applied in a simple manner, even geometrically apply complicated components. In addition, they are not expensive and complex Spraying or evaporation systems required
- the slip layer is at a temperature of 750 to 1200 ° C is heat treated in argon or vacuum, the heat treating the Layer is preferably carried out over 1-4 hours using the slip layer to connect the component via diffusion.
- the final step Alit the layer at a temperature between 800 and 1200 ° C and one Duration 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 can, the armor is applied to the tip of the blade.
- z is not growing using a MCrAlY powder to make a slurry into a suspension mixed with a conventional inorganic binder. That is in the suspension MCrAlY powder with 80 - 90 wt .-%, the binder with 5 - 10 wt .-% and additional Water with 5-7% by weight.
- the grain sizes of the particles of the MCrAIY powder are between 5 and 120 ⁇ m. BN particles become into this flowable and sprayable mass introduced, the size of which is greater than that of the MCrAlY powder particles.
- the blade tip of a turbine blade is made into a mass Nickel-based alloy immersed in such a way that on the to be armored Blade tip forms a slip layer.
- it could contain the particles Slip e.g. also with a brush, forming a layer on the Blade tip to be applied.
- the next step is the suspension in a suspension existing, still moist slip or the slip layer at room temperature dried over about 1.5 hours.
- the dried slip layer is then heat-treated in a vacuum at 1000 ° C. for 1 hour, to connect the slip layer with the material of the turkey blade to achieve by diffusion.
- the layer is then attached to Alitized at about 1100 ° C for 4 hours using a conventional method to make the compound the engine blade is further reinforced by diffusion and the slip layer to compact.
- Al penetrates the layer and the base material the turbine blade and ensures both a firm connection of the layer with the component as well as for a firm connection of the spherical MCrAIY particles with each other.
- the spherical MCrAlY particles at least sinter partly together.
- Ni can also be made from the base material emerge and diffuse into the slip layer. Stand after the alitation step the hard, ceramic particles of BN or the like. Outward via the slip layer from 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 touch one another while brushing against the gas turbine Cut in the run-in covering to prevent damage to prevent the blade tip and the gap size between the rotating and to 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)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims (12)
- Verfahren zum Herstellen einer Panzerung für eine Turbinenschaufel, die auf deren Schaufelspitze vorgesehen wird, gekennzeichnet durch die Schritte: Herstellen eines Schlickers durch Mischen eines wenigstens eines der Elemente Ni oder Cr oder Ce enthaltenden Pulvers mit einem Bindemittel; Auftragen des Schlickers auf die zu panzernde Oberfläche; Zugabe keramischer Hartpartikel zum Schlicker vor oder nach dem Auftragen des Schlickers, deren Größe so gewählt wird, daß sie nach einem Alitieren über die Schicht vorstehen; Trocknen des Schlickers bei einer Temperatur von Raumtemperatur bis 300 °C; und Alitieren der Schlickerschicht.
- Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Partikel dem Schlicker vor dem Auftragen zugemischt werden.
- Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Partikel nach dem Auftragen in den Schlicker eingesetzt werden.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß Partikel aus BN, SiC oder Al2O3 verwendet werden.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Schlicker aus einem Pulver aus MCrAIY hergestellt wird.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Pulver mit einer Korngrößenverteilung von 5 bis 120 µm vorliegt.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Auftragen durch Spritzen, Pinseln oder Tauchen durchgeführt wird.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Trocknen über 0,5 - 4 Stunden durchgeführt wird.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Schlickerschicht vor dem Alitieren bei einer Temperatur von 750 bis 1200 °C in Argon oder Vakuum wärmebehandelt wird.
- Verfahren nach Anspruch 9, dadurch gekennzeichnet, daß das Wärmebehandeln über 1 bis 4 Stunden durchgeführt wird.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Bauteil aus einer Legierung auf Nickel- oder Kobaltbasis besteht.
- Verfahren nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Alitieren bei einer Temperatur zwischen 800 und 1200 °C und einer Dauer von 1 bis 12 Stunden durchgeführt wird.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19827620A DE19827620C2 (de) | 1998-06-20 | 1998-06-20 | Verfahren zum Herstellen einer Panzerung für ein metallisches Bauteil und dessen Verwendung |
DE19827620 | 1998-06-20 | ||
PCT/DE1999/001753 WO1999067438A1 (de) | 1998-06-20 | 1999-06-16 | Verfahren zum herstellen einer panzerung für ein metallisches bauteil |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1097249A1 EP1097249A1 (de) | 2001-05-09 |
EP1097249B1 true EP1097249B1 (de) | 2002-04-03 |
Family
ID=7871567
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99939334A Expired - Lifetime EP1097249B1 (de) | 1998-06-20 | 1999-06-16 | Verfahren zur herstellung einer panzerung für ein metallisches bauteil |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP1097249B1 (de) |
JP (1) | JP2002518600A (de) |
DE (2) | DE19827620C2 (de) |
ES (1) | ES2176013T3 (de) |
WO (1) | WO1999067438A1 (de) |
Families Citing this family (10)
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 |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1427054A (en) * | 1973-09-19 | 1976-03-03 | Rolls Royce | Method of and mixture for aluminishing a metal surface |
IT1083665B (it) * | 1977-07-14 | 1985-05-25 | Fiat Spa | Procedimento per la realizzazione di rivestimenti per alte temperature su metalli e leghe metalliche |
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 |
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 |
-
1998
- 1998-06-20 DE DE19827620A patent/DE19827620C2/de not_active Expired - Fee Related
-
1999
- 1999-06-16 WO PCT/DE1999/001753 patent/WO1999067438A1/de active IP Right Grant
- 1999-06-16 DE DE59901139T patent/DE59901139D1/de not_active Expired - Fee Related
- 1999-06-16 JP JP2000556077A patent/JP2002518600A/ja not_active Abandoned
- 1999-06-16 ES ES99939334T patent/ES2176013T3/es not_active Expired - Lifetime
- 1999-06-16 EP EP99939334A patent/EP1097249B1/de not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
WO1999067438A1 (de) | 1999-12-29 |
ES2176013T3 (es) | 2002-11-16 |
JP2002518600A (ja) | 2002-06-25 |
DE19827620C2 (de) | 2003-12-18 |
DE59901139D1 (de) | 2002-05-08 |
DE19827620A1 (de) | 1999-12-23 |
EP1097249A1 (de) | 2001-05-09 |
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