EP0397731B1 - Metallgegenstand, insbesondere gasturbinenschaufel mit schutzbeschichtung - Google Patents

Metallgegenstand, insbesondere gasturbinenschaufel mit schutzbeschichtung Download PDF

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Publication number
EP0397731B1
EP0397731B1 EP89901530A EP89901530A EP0397731B1 EP 0397731 B1 EP0397731 B1 EP 0397731B1 EP 89901530 A EP89901530 A EP 89901530A EP 89901530 A EP89901530 A EP 89901530A EP 0397731 B1 EP0397731 B1 EP 0397731B1
Authority
EP
European Patent Office
Prior art keywords
coating layer
layer
chromium
approximately
component according
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
EP89901530A
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German (de)
English (en)
French (fr)
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EP0397731A1 (de
Inventor
Friedhelm Schmitz
Norbert Czech
Bruno Deblon
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.)
Siemens AG
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Siemens AG
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Filing date
Publication date
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Publication of EP0397731A1 publication Critical patent/EP0397731A1/de
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Publication of EP0397731B1 publication Critical patent/EP0397731B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/023—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 only coatings only including layers of metallic material only coatings of metal elements only

Definitions

  • the present invention relates to a metal object, in particular a component of a gas turbine plant, for. B. a blade, according to the preamble of claim 1.
  • a metal object in particular a component of a gas turbine plant, for. B. a blade, according to the preamble of claim 1.
  • Many components exposed to hot gas, particularly in gas turbines, are subject to thermal, mechanical and erosive stresses and are also to a large extent corrosive influences. Coatings that form from salts, the origin of which can be attributed to fuel and air pollution, together with some gaseous substances lead to corrosive damage from high-temperature corrosion (HTK).
  • the corrosion pathogens can be very heterogeneous.
  • the type and origin of the fuels and, on the other hand, the composition of the combustion air determine the different types of attack that come about through different chemical mechanisms.
  • the combustion air may contain heavy metals, alkalis and / or chlorides.
  • coating layers including multiple coatings for components exposed to hot gas, are known in large numbers from the literature for different purposes.
  • the innermost layer is a diffusion layer mainly containing chromium.
  • the graded coating described is generally intended to protect the metal object against heat corrosion, in which case corrosion tests at temperatures of approximately 925 ° C. are described.
  • DE-C-28 26 909 discloses a further double layer for metal objects loaded in this way, an inner partial layer containing portions of the elements aluminum, chromium and yttrium.
  • US Pat. No. 3,649,225 also describes double layers which are intended to prevent high-temperature corrosion.
  • the lower, generally thin layer does not itself serve as protection against external attack, but only improves the durability and adhesion of the upper layer.
  • the known layer systems protect a component against oxidation and corrosion at very high temperatures, but intensive studies have shown that the known layers do not simultaneously protect against a different type of corrosion attack at temperatures between 600 ° and 800 ° C. As can be seen from FIG. 1 of the drawing, there are two different types of attack for high-temperature corrosion after investigations have become known.
  • Fig. 1 shows that in addition to the already mentioned high-temperature corrosion in the range of about 850 ° C (hereinafter referred to as HTKI), against which the known protective layers are designed, there is another strong corrosion mechanism which has a maximum in the range of about 700 ° C Has. 1 shows a diagram in which the corrosion rate is plotted against the temperature.
  • HTKI high-temperature corrosion in the range of about 850 ° C
  • Has. 1 shows a diagram in which the corrosion rate is plotted against the temperature.
  • DE-A 31 04 581 already points to the additional problem of corrosion at lower temperatures in gas turbines.
  • a silicon-rich layer on the outside of a layer that is corrosion-resistant to high temperatures, which forms aluminides, in order to improve the corrosion resistance against attacks at medium temperatures.
  • the object of the present invention is therefore to create a combination of protective layers which makes a metal object more resistant to both known attack mechanisms, HTKI and HTKII, and thus increases the service life of the component.
  • the component is first provided with a layer which, owing to its thickness or composition, is highly resistant to attack mechanisms at temperatures of 600 ° to 800 ° C. Furthermore, a second coating layer is applied, which is particularly resistant to attacks at 800 ° to 900 ° C.
  • This structure is based on the knowledge that components which are exposed to hot gas are generally cooled on the inside, so that there is a temperature gradient from the outermost layer to the interior of the component. Therefore, the inner layer is initially designed against the attack mechanism at a lower temperature, while the outer layer should protect against corrosion at high temperatures.
  • a component does not always have to be completely provided with both layers, provided that the temperature load of individual areas is different.
  • the invention should therefore of course also include the double coating only in partial areas of the metal objects.
  • the proposed arrangement of the layers has the advantage that the service life of a component is increased in any case, even if the average prevailing attack mechanism is different at different locations on the component and is not necessarily known. If, for example, a special one well-cooled part of the component is mainly in the temperature range around 700 ° C even during full load operation, so the outermost protective layer, which is not optimized for this type of attack, is gradually destroyed, but then protects the layer underneath.
  • FIG. 2 shows an example of the effects of the double layer on the operating time in a diagram.
  • the consumption is plotted against the operating time and typical consumption curves for different temperature loads of different sub-areas of a component are shown.
  • FIG. 3 shows the effect of a thermal barrier layer over a corrosion protection layer in an internally cooled component.
  • the diagram shows 2 typical temperature profiles inside and outside the component and the protective layers.
  • a diffusion layer applied to the metal object with a chromium content greater than 50% is suitable as the first coating layer.
  • Such diffusion layers are known per se according to the prior art, in particular from DE-C-28 26 910. However, their beneficial effect compared to HTKII when combined with a second coating layer against HTKI was not recognized.
  • An additional amount of iron or manganese, e.g. B. 10 to 30% (all the following data are percentages by weight) the thickness of such a diffusion layer can be increased to over 0.130 mm, with an increasing proportion of iron or manganese also increasing the possible layer thickness, which of course increases the service life under HTKII conditions .
  • an overlay layer can alternatively be provided, which can be applied, for example, by low-pressure plasma spraying.
  • This layer should contain 30 to 55%, preferably about 40%, chromium and 0.5 to 2%, preferably about 1%, of at least one of the rare earth elements, yttrium, scandium, hafnium, zirconium, niobium, Tantalum, silicon. If at all, aluminum should only be present in small amounts, namely less than 3%.
  • the rest of the layer consists of one or a mixture of the elements iron, cobalt, nickel, and production-related impurities can also be added.
  • the chromium content can be chosen to be lower, namely between 15 and 50%, preferably between about 20 and 30%, to achieve an equally good effect. .
  • the second coating layer is said to belong to the MCrAlY type.
  • Such layers are basically known per se from the prior art, for. B. again from DE-C 28 21 910.
  • this combination in particular results in a particularly long service life of the metal objects at locally different temperatures.
  • the second coating layer should have the following composition: 15 to 40% chromium, preferably approximately 20 to 30%; 3 to 15% aluminum, preferably about 7 to 12%; 0.2 to 3% of at least one element from the group of rare earths, yttrium, tantalum, hafnium, scandium, zirconium, niobium, rhenium, silicon, preferably about 0.7%; The rest of at least one of the elements made of cobalt, nickel, as well as manufacturing-related impurities.
  • the second coating layer should be applied by plasma spraying, in particular low-pressure plasma spraying.
  • plasma spraying in particular low-pressure plasma spraying.
  • various coating methods come into consideration, as have already been described in DE-C-28 26 910, but low-pressure plasma spraying allows the application of particularly adhesive and oxide-free layers of greater layer thickness.
  • the outer coating layer may have a greater layer thickness than the inner one.
  • a diffusion barrier layer can significantly increase the service life.
  • Such a layer can consist, for example, of titanium nitride or titanium carbide.
  • thermal barrier layers on the outside of the metal object. These layers have the effect that the underlying metallic layers only have temperatures against which they are designed. In order to prevent the thermal barrier layer from flaking off, it can be advantageous according to claim 13 to oxidize the surface of the second coating layer before the thermal barrier layer is applied.
  • a component 1 has a first metallic coating layer 2, which is optimized against HTKII or is resistant due to its thickness. Above it is a second coating layer 3, which is resistant to HTKI. If necessary, there may be diffusion barrier layers 4, 5 between the base material 1 and the first coating layer 2 and / or between the first coating layer 2 and the second coating layer 3, which impede the concentration compensation of individual elements by diffusion. Finally, a thermal barrier layer 6, which protects against particularly high temperatures, can also be attached on the very outside.
  • the multiple coatings according to the invention are particularly suitable for blades and parts of gas turbines in which individual, for. B. cooled components, locally different temperatures occur, such as in systems that are operated temporarily at full load and secondly only at partial load.
  • thick multiple protective layers can be applied to such components, which usually consist of nickel-based alloys, which considerably extend the service life of the components, in particular of the blades.
  • the coatings described can, as far as this is economically justifiable, be supplemented by other similar or different coatings.

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP89901530A 1988-02-05 1989-01-19 Metallgegenstand, insbesondere gasturbinenschaufel mit schutzbeschichtung Expired - Lifetime EP0397731B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3803517 1988-02-05
DE3803517 1988-02-05

Publications (2)

Publication Number Publication Date
EP0397731A1 EP0397731A1 (de) 1990-11-22
EP0397731B1 true EP0397731B1 (de) 1993-04-14

Family

ID=6346731

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89901530A Expired - Lifetime EP0397731B1 (de) 1988-02-05 1989-01-19 Metallgegenstand, insbesondere gasturbinenschaufel mit schutzbeschichtung

Country Status (5)

Country Link
EP (1) EP0397731B1 (enrdf_load_stackoverflow)
JP (1) JPH03503184A (enrdf_load_stackoverflow)
DE (1) DE58904084D1 (enrdf_load_stackoverflow)
IN (1) IN171444B (enrdf_load_stackoverflow)
WO (1) WO1989007159A1 (enrdf_load_stackoverflow)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6156133A (en) * 1995-07-25 2000-12-05 Siemens Aktiengesellschaft Method for manufacturing a product with a metallic basic body
US11092034B2 (en) 2011-08-09 2021-08-17 Siemens Energy Global Gmbh & Co, Kg Alloy, protective layer and component

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996012049A1 (de) * 1994-10-14 1996-04-25 Siemens Aktiengesellschaft Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung
WO1996035825A1 (en) * 1995-05-08 1996-11-14 Helmut Tannenberger Workpiece for high-temperature uses and process for producing it
DE19815473A1 (de) 1998-04-07 1999-10-14 Ghh Borsig Turbomaschinen Gmbh Heißgasführendes Gassammelrohr einer Gasturbine
CH695689A5 (de) * 2001-05-23 2006-07-31 Sulzer Metco Ag Verfahren zum Erzeugen eines wärmedämmenden Schichtsystems auf einem metallischen Substrat.
EP1524334A1 (de) * 2003-10-17 2005-04-20 Siemens Aktiengesellschaft Schutzschicht zum Schutz eines Bauteils gegen Korrosion und Oxidation bei hohen Temperaturen und Bauteil
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
US20070116875A1 (en) 2005-11-22 2007-05-24 United Technologies Corporation Strip process for superalloys
ES2342552T3 (es) * 2006-08-23 2010-07-08 Siemens Aktiengesellschaft Alabe de turbina con un sistema de recubrimiento.
EP2206805A1 (de) * 2009-01-08 2010-07-14 Siemens Aktiengesellschaft MCrAIX-Schicht mit unterschiedlichen Chrom- und Aluminiumgehalten

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3649225A (en) * 1969-11-17 1972-03-14 United Aircraft Corp Composite coating for the superalloys
FR2207198B1 (enrdf_load_stackoverflow) * 1972-10-23 1976-08-20 Onera (Off Nat Aerospatiale)
US4284688A (en) * 1978-12-21 1981-08-18 Bbc Brown, Boveri & Company Limited Multi-layer, high-temperature corrosion protection coating
US4326011A (en) * 1980-02-11 1982-04-20 United Technologies Corporation Hot corrosion resistant coatings

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6156133A (en) * 1995-07-25 2000-12-05 Siemens Aktiengesellschaft Method for manufacturing a product with a metallic basic body
US11092034B2 (en) 2011-08-09 2021-08-17 Siemens Energy Global Gmbh & Co, Kg Alloy, protective layer and component

Also Published As

Publication number Publication date
IN171444B (enrdf_load_stackoverflow) 1992-10-17
DE58904084D1 (de) 1993-05-19
WO1989007159A1 (en) 1989-08-10
EP0397731A1 (de) 1990-11-22
JPH03503184A (ja) 1991-07-18

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