EP1639152A1 - Method for producing a protective layer, protective layer, use thereof, and part provided with a protective layer - Google Patents
Method for producing a protective layer, protective layer, use thereof, and part provided with a protective layerInfo
- Publication number
- EP1639152A1 EP1639152A1 EP04738733A EP04738733A EP1639152A1 EP 1639152 A1 EP1639152 A1 EP 1639152A1 EP 04738733 A EP04738733 A EP 04738733A EP 04738733 A EP04738733 A EP 04738733A EP 1639152 A1 EP1639152 A1 EP 1639152A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- protective layer
- layer
- phosphate
- silicate
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/007—Preventing corrosion
-
- 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
- C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
-
- 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
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
-
- 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
- C23D—ENAMELLING OF, OR APPLYING A VITREOUS LAYER TO, METALS
- C23D5/00—Coating with enamels or vitreous layers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
- Y10T428/252—Glass or ceramic [i.e., fired or glazed clay, cement, etc.] [porcelain, quartz, etc.]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
- Y10T428/258—Alkali metal or alkaline earth metal or compound thereof
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
- Y10T428/259—Silicic material
Definitions
- the invention relates to a method for producing a protective layer according to the preamble of patent claim 1. Furthermore, the invention relates to a protective layer according to the preamble of patent claim 10, a component with a protective layer and the use of the protective layer.
- components When components, in particular components of gas turbines, are operated at high temperatures, their free surfaces are exposed to strongly eroding, corrosive and oxidizing conditions.
- such components can consist, for example, of a nickel-based or cobalt-based superalloy.
- the components are coated. From DE 198 07 636 C1 and DE 199 09 675 A1 coatings for protection against corrosion, oxidation or erosion are known.
- the present invention is based on the problem of creating a novel method for producing a protective layer and a novel protective layer. Furthermore, it is within the scope of the invention to propose a component with a protective layer and a use for such a protective layer.
- At least one paint material is provided, the paint material being a phosphate or silicate, preferably mixed with particles. At least one layer of the or each paint material is applied to a component to be protected against erosion. The or each applied layer of lacquer is converted into a layer of glass.
- a plurality of lacquer layers are applied to the component either on a phosphate basis or on a silicate basis, the lacquer layers differing in the added particles.
- the one with the The component coated with lacquer layers is heated and then cooled, a phosphate glass bond or a silicate glass bond being formed between the lacquer layers originally separated from one another.
- the protective layer according to the invention is characterized by the features of independent claim 10.
- the component according to the invention is in claim 16, the use according to the invention is defined in claims 18 and 19.
- the protective layer according to the invention can with a layer sequence of at least two different layers, for. B. a layer of varnish based on phosphate or silicate with added aluminum powder and / or with added hollow spheres and a layer of varnish based on phosphate or silicate with added ceramic particles and / or nitrite particles, be repeated several times and thus form a so-called "multilayer".
- Fig. 2 a rotor of a gas turbine with integral blading.
- FIGS. 1 and 2 show a blade of a gas turbine
- FIG. 2 shows a rotor of a gas turbine with integral blading. Both components are coated with the protective layer according to the invention, which is applied to the same in the sense of the method according to the invention.
- the surfaces of the component to be coated are preferably coated prior to coating blasted in order to obtain a shiny metallic surface on the component.
- any other method can of course be used to obtain a bright metallic surface.
- a first main step at least one paint material is provided, the or each paint material being based on phosphate or silicate and particles being added to the or each paint material.
- a second main step at least one layer of the or each coating material is applied to a component to be protected against erosion.
- the or each applied lacquer layer is converted into a glass layer.
- the paint material is a phosphate or a silicate in which particles are embedded. If a component to be coated is to be coated with several layers of lacquer, several lacquer materials are provided which either consist of phosphate or silicate and which differ in the added particles. It is within the scope of the present invention to add an aluminum powder or hollow spheres to the phosphate-based or silicate-based coating material. Such a paint material is then preferably used for a paint layer or coating close to the component. Furthermore, it is within the scope of the present invention to provide a coating material based on phosphate or silicate, to which ceramic particles or nitrite particles are added as particles.
- Such a lacquer material is preferably used for an outer lacquer layer or coating remote from the component. It is therefore within the meaning of the present invention to coat a component to be coated and protected against erosion with a plurality of layers of coating materials, these coating material layers being constructed either on a silicate basis or on a phosphate basis.
- the individual layers differ in the particles added to the phosphate or silicate. Depending on whether the layer is applied near or far from the component, i.e. depending on The tasks to be performed by the lacquer layer and thus the particles added to the phosphate or silicate differ from whether the lacquer layer forms an inner or an outer coating.
- the component to be protected against erosion is preferably coated with a plurality of layers of the paint materials provided.
- the coating is done by painting, i.e. by dipping, spraying or brushing. These coating processes can be carried out using simple means and therefore inexpensively.
- the coated component After the lacquer technology application of the or each layer to the component to be protected against erosion, the coated component is subjected to a conversion process.
- the coated component is heated and then cooled. It is in the spirit of the present invention that the phosphate-based or silicate-based lacquer layers are converted into a glass during this conversion process.
- the coated component is heated and finally cooled without crystallization of the coating materials based on phosphate or silicate taking place.
- an antifouling layer to the component as the final cover layer.
- an antifouling layer Under fouling the deposition of dirt particles or organisms on material surfaces. So-called antifouling coatings therefore prevent contaminants from adhering to the surface of the component. Different antifouling coatings are known from the prior art. The selection of a suitable antifouling layer is the responsibility of the specialist addressed here.
- the erosion-resistant protective layer to the gas-flow components of a gas turbine, in particular an aircraft engine. These can be all components of a gas turbine around which gas flows. However, it is preferred to use the protective layer according to the invention on blades of a gas turbine or on rotors with integral blades, namely on so-called Bjaded Disks (Blisks) or so-called Baths Rings (Blings).
- Blisks Bjaded Disks
- Baths Rings Baths Rings
- the blade 10 comprises an airfoil 1 1, which can consist of a fiber-reinforced plastic and which is attached to a metallic blade root 12 made of a titanium-based alloy.
- a blade 10 is used, for example, in a compressor of a gas turbine and is fixed with its blade root 12 to a rotor ring or a rotor carrier.
- the formation of the airfoil 1 1 from fiber-reinforced plastic proves to be advantageous in terms of weight reduction. Disadvantages, however, are insufficient wear behavior against erosion.
- the blade 10 is coated with a protective layer 13, the protective layer 13 being applied to the airfoil 11 or the entire blade 10 in the sense of the inventive method described above.
- the protective layer 13 accordingly essentially consists of a phosphate glass or a silicate glass with particles embedded in the phosphate glass or in the silicate glass. Depending on the distance from the surface of the airfoil 11, different particles are embedded in the phosphate glass or the silicate glass.
- An aluminum powder is embedded in proximity to the surface of the component or of the airfoil 11. Alternatively, hollow spheres can also be embedded. Ceramic particles or nitrite particles can be embedded in the phosphate glass or silicate glass in the distance from the component.
- An antifouling layer is preferably applied as the final cover layer.
- FIG. 2 shows an integrally bladed rotor 14 in a gas turbine (not shown in detail).
- the rotor 14 has on its peripheral surface 15 a plurality of generally equidistantly arranged and essentially radial blades 16 which are an integral part of the rotor 14.
- Such a rotor 14 with integral blading is also referred to as a bladed disk (blisk) or bladed ring (bling), depending on whether the rotor is designed as a disk or a ring.
- Such a rotor 10 with integral blading can have poor wear behavior with respect to erosion.
- the latter has a protective layer 17 according to the invention. To avoid repetitions, reference is made to the above explanations for this protective layer 17.
- a protective layer against erosion for the gas-flow components of an aircraft engine by providing a component with at least one layer of a coating material based on phosphate or silicate.
- Different particles can be embedded in the phosphate-based or silicate-based coating material.
- the coated component is subjected to a conversion process, the phosphate or silicate being converted into a phosphate glass or silicate glass.
- the individual layers of lacquer either form a phosphate glass bond or a silicate glass bond. The individual layers differ in the particles added to the phosphate or the silicate.
- the protective layer according to the invention can be produced inexpensively using simple means.
- the properties of the protective layer can be precisely adjusted by selecting and layering different layers.
- An anti-fouling layer prevents dirt particles or organisms from sticking. Due to the fact that the individual lacquer layers form a phosphate glass bond or silicate glass bond after the conversion process, the problems of separate layers can be avoided. This avoids the risk of the coating flaking off.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10329049A DE10329049A1 (en) | 2003-06-27 | 2003-06-27 | Method for producing a protective layer, protective layer, use thereof and component with a protective layer |
PCT/DE2004/001283 WO2005005690A1 (en) | 2003-06-27 | 2004-06-19 | Method for producing a protective layer, protective layer, use thereof, and part provided with a protective layer |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1639152A1 true EP1639152A1 (en) | 2006-03-29 |
Family
ID=33521119
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04738733A Withdrawn EP1639152A1 (en) | 2003-06-27 | 2004-06-19 | Method for producing a protective layer, protective layer, use thereof, and part provided with a protective layer |
Country Status (4)
Country | Link |
---|---|
US (1) | US7736732B2 (en) |
EP (1) | EP1639152A1 (en) |
DE (1) | DE10329049A1 (en) |
WO (1) | WO2005005690A1 (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7314674B2 (en) * | 2004-12-15 | 2008-01-01 | General Electric Company | Corrosion resistant coating composition, coated turbine component and method for coating same |
US7544396B2 (en) * | 2005-03-10 | 2009-06-09 | General Electric Company | Electrostatic coating composition comprising corrosion resistant metal particulates and method for using 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 |
US8227078B2 (en) * | 2008-02-11 | 2012-07-24 | General Electric Company | Anti-fouling coatings for combustion system components exposed to slag, ash and/or char |
US8802225B2 (en) * | 2011-05-31 | 2014-08-12 | United Technologies Corporation | Article having vitreous monocoating |
US9926793B2 (en) | 2013-03-15 | 2018-03-27 | United Technologies Corporation | Blades and manufacture methods |
JP5928419B2 (en) * | 2013-08-22 | 2016-06-01 | トヨタ自動車株式会社 | Thermal barrier film and method for forming the same |
DE102020000848B4 (en) | 2020-02-05 | 2022-06-09 | OT Oberflächentechnik GmbH & Co. KG | Process for coating blades of compressors, turbines and propellers |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB123773A (en) | 1915-09-21 | 1919-03-13 | Owen David Lucas | Improvements in Cartridge Feed Mechanism and Magazines for Machine Guns. |
US3149001A (en) * | 1962-04-05 | 1964-09-15 | Aluminum Co Of America | Enameled aluminous metal product |
GB1123773A (en) * | 1966-01-31 | 1968-08-14 | Alchem Ltd | Refractory coating compositions |
US3522113A (en) * | 1968-01-02 | 1970-07-28 | Armco Steel Corp | Potassium silicate coated silicon steel article |
DE2743840B2 (en) * | 1977-09-29 | 1980-10-02 | Pfaelzische Emailschmelze Rolf Romanic Zweigniederlassung Der Ferro (Deutschland) Gmbh, 6750 Kaiserslautern | Process for the production of a highly abrasion-resistant, acid-resistant, enamel or Glaze coating with embedded Al2 O3 particles and application of the process |
US4347085A (en) * | 1981-04-23 | 1982-08-31 | Armco Inc. | Insulative coatings for electrical steels |
US4935387A (en) * | 1988-10-24 | 1990-06-19 | Corning Incorporated | Fiber-reinforced composite comprising mica matrix or interlayer |
US5985454A (en) * | 1990-02-05 | 1999-11-16 | Sermatech International Incorporated | Anti-fouling coating for turbomachinery |
DE19807636C1 (en) | 1998-02-23 | 1999-11-18 | Mtu Muenchen Gmbh | Process for producing a corrosion and oxidation resistant slip layer |
US6165600A (en) * | 1998-10-06 | 2000-12-26 | General Electric Company | Gas turbine engine component having a thermal-insulating multilayer ceramic coating |
DE19909675B4 (en) | 1999-03-05 | 2005-07-14 | Mtu Aero Engines Gmbh | Layer structure and method for its production |
WO2005003033A2 (en) * | 2002-12-23 | 2005-01-13 | Applied Thin Films, Inc. | Aluminum phosphate coatings |
-
2003
- 2003-06-27 DE DE10329049A patent/DE10329049A1/en not_active Ceased
-
2004
- 2004-06-19 EP EP04738733A patent/EP1639152A1/en not_active Withdrawn
- 2004-06-19 WO PCT/DE2004/001283 patent/WO2005005690A1/en active Application Filing
- 2004-06-19 US US10/562,653 patent/US7736732B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2005005690A1 * |
Also Published As
Publication number | Publication date |
---|---|
US7736732B2 (en) | 2010-06-15 |
DE10329049A1 (en) | 2005-01-13 |
US20060269759A1 (en) | 2006-11-30 |
WO2005005690A1 (en) | 2005-01-20 |
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Legal Events
Date | Code | Title | Description |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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17P | Request for examination filed |
Effective date: 20051208 |
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AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE FR GB |
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DAX | Request for extension of the european patent (deleted) | ||
RBV | Designated contracting states (corrected) |
Designated state(s): DE FR GB |
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17Q | First examination report despatched |
Effective date: 20070410 |
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GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
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INTG | Intention to grant announced |
Effective date: 20140128 |
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RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES GMBH |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 20140611 |
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RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES AG |