EP0397731A1 - Objet metallique, notamment aube de turbine a gaz pourvue d'un revetement de protection. - Google Patents

Objet metallique, notamment aube de turbine a gaz pourvue d'un revetement de protection.

Info

Publication number
EP0397731A1
EP0397731A1 EP89901530A EP89901530A EP0397731A1 EP 0397731 A1 EP0397731 A1 EP 0397731A1 EP 89901530 A EP89901530 A EP 89901530A EP 89901530 A EP89901530 A EP 89901530A EP 0397731 A1 EP0397731 A1 EP 0397731A1
Authority
EP
European Patent Office
Prior art keywords
layer
coating layer
metal object
object according
coating
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
EP89901530A
Other languages
German (de)
English (en)
Other versions
EP0397731B1 (fr
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
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Publication of EP0397731A1 publication Critical patent/EP0397731A1/fr
Application granted granted Critical
Publication of EP0397731B1 publication Critical patent/EP0397731B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • 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

  • Metal object in particular gas turbine blade with protective coating
  • 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.
  • Many components which are exposed to hot gas, in particular in gas turbines, are subject to thermal, mechanical and erosive stresses and are also to a large extent corrosive influences. Coverings 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 by high-temperature corrosion (HTK).
  • HTK high-temperature corrosion
  • the corrosion exciters 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 forms 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 from the literature in large numbers for different purposes.
  • DE-C-28 26 910 it is known from DE-C-28 26 910 to provide metal objects with a graduated coating.
  • 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 about 925 ° C. are described.
  • DE-C-28 26 909 discloses a further double layer for metal objects subjected to such loads, 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 2 different types of attack for high-temperature corrosion after investigations which have become known.
  • Fig. 1 shows that in addition to the high-temperature corrosion already mentioned in the range of approximately 850 ° C. (hereinafter referred to as HTKI), whereas the known protective layers are designed, there is another strong corrosion mechanism which has a maximum in the range of approximately 700 * C.
  • Fig. 1 shows a diagram in which the rate of corrosion versus temperature is plotted.
  • the object of the present invention is therefore to create a combination of protective layers which makes a metal object resistant to both known attack techniques e ⁇ , HTKI and HTKII and thus increases the service life of the component.
  • a metal object with the coatings according to the characterizing features of claim 1 is proposed. Then the component is first provided with a layer which, owing to its thickness or composition, has great resistance 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 internally, so that there is a temperature gradient from the outermost layer to the interior of the component inner layer against the attack mechanism designed at lower temperatures, while the outer layer should protect against corrosion at high temperatures.
  • a component does not in principle 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 subsequently 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 stresses of different parts 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 two 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, the possible layer thickness also increasing with increasing proportion of iron or manganese, which of course reduces the service life HTKII conditions increased.
  • a support layer can also 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 elements from the group of rare earths, yttrium, scandium, hafnium, zirconium, Niobium, tantalum, silicon. If at all, aluminum should only be present in small amounts, namely less than 5%, preferably even less than 3.
  • the rest of the layer consists of one or a mixture of the elements iron, cobalt, nickel, in which case production-related impurities can be added.
  • the chromium content can be chosen lower, namely between 15 and 50%, to achieve an equally good effect. , preferably between about 20 and 30%.
  • Claim 5 teaches that the second coating layer should belong to the MCrAlY type.
  • Such layers are also known per se according to the prior art, e.g. B. again from DE-C 28 26 910.
  • this combination in particular results in a particularly long service life of the metal objects at 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%, rest of at least one of the elements made of cobalt, nickel, and manufacturing-related impurities.
  • the second coating layer should be applied by plasma spraying, in particular low-pressure plasma spraying.
  • a diffusion barrier layer can significantly increase the service life.
  • Such a layer can consist, for example, of titanium nitride or titanium carbide.
  • one possibility of protection against particularly high temperatures is to prevent the temperatures from reaching the metallic layers.
  • This can be achieved by 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.
  • it can be advantageous according to claim 9 to oxidize the surface of the second coating layer before the thermal barrier layer is applied.
  • a total coating thickness of over 0.3 mm can be achieved.
  • 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 hinder 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, e.g. B. cooled components, locally different temperatures occur, such as in systems that are operated at times at full load and sometimes 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 further similar or different coatings.

Landscapes

  • 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)

Abstract

La présente invention concerne des couches de protection multiples pour objets métalliques (1), notamment des aubes de turbine à gaz. Sachant qu'il existe deux mécanismes de corrosion différents, qui conditionnent la durée de vie de tels objets, on applique deux couches protectrices superposées dont la couche intérieure (2) protège contres les attaques de la corrosion à des température comprises entre 600°C et 800°C (HTKII), et la couche extérieure (3) offre une protection optimale contre la corrosion à des températures comprises entre 800°C et 900°C (HTKI). En outre, on peut encore prévoir comme revêtement de protection extrême une couche (6) formant barrière thermique. On préfèrera comme première couche de revêtement (2) une couche de diffusion présentant une teneur en chrome supérieure à 50 % et une teneur en fer et/ou en manganèse supérieure à 10 %, et comme seconde couche de revêtement (3) une couche de MCrAlY, avec par exemple environ 30 % de chrome, environ 7 % d'aluminium et environ 0,7 % d'yttrium, qui seront appliquées par projection au plasma à pression réduite.
EP89901530A 1988-02-05 1989-01-19 Objet metallique, notamment aube de turbine a gaz pourvue d'un revetement de protection Expired - Lifetime EP0397731B1 (fr)

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 true EP0397731A1 (fr) 1990-11-22
EP0397731B1 EP0397731B1 (fr) 1993-04-14

Family

ID=6346731

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89901530A Expired - Lifetime EP0397731B1 (fr) 1988-02-05 1989-01-19 Objet metallique, notamment aube de turbine a gaz pourvue d'un revetement de protection

Country Status (5)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5967755A (en) * 1995-07-25 1999-10-19 Siemens Aktiengesellschaft Product with a metallic basic body and method for manufacturing a product

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0786017B1 (fr) * 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
WO1996035825A1 (fr) * 1995-05-08 1996-11-14 Helmut Tannenberger Piece pour utilisation a temperatures elevees et son procede de production
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 (fr) * 2003-10-17 2005-04-20 Siemens Aktiengesellschaft Couche protectrice pour proteger un élément structurel contre la corrosion et l'oxydation aux temperatures hautes et élément structurel
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
EP1892311B1 (fr) * 2006-08-23 2010-03-31 Siemens Aktiengesellschaft Aube de turbine avec une système de revêtement
EP2206805A1 (fr) * 2009-01-08 2010-07-14 Siemens Aktiengesellschaft Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium
EP2557201A1 (fr) * 2011-08-09 2013-02-13 Siemens Aktiengesellschaft Alliage, couche de protection et composant

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 (fr) * 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO8907159A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5967755A (en) * 1995-07-25 1999-10-19 Siemens Aktiengesellschaft Product with a metallic basic body and method for manufacturing a product

Also Published As

Publication number Publication date
EP0397731B1 (fr) 1993-04-14
JPH03503184A (ja) 1991-07-18
WO1989007159A1 (fr) 1989-08-10
DE58904084D1 (de) 1993-05-19
IN171444B (fr) 1992-10-17

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