EP1561542A1 - Procédé d'enlèvement d'une couche d'un élément - Google Patents

Procédé d'enlèvement d'une couche d'un élément Download PDF

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Publication number
EP1561542A1
EP1561542A1 EP04002334A EP04002334A EP1561542A1 EP 1561542 A1 EP1561542 A1 EP 1561542A1 EP 04002334 A EP04002334 A EP 04002334A EP 04002334 A EP04002334 A EP 04002334A EP 1561542 A1 EP1561542 A1 EP 1561542A1
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EP
European Patent Office
Prior art keywords
layer
carried out
dry ice
turbine
component
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.)
Ceased
Application number
EP04002334A
Other languages
German (de)
English (en)
Inventor
Ralph Reiche
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
Priority to EP04002334A priority Critical patent/EP1561542A1/fr
Publication of EP1561542A1 publication Critical patent/EP1561542A1/fr
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
    • B24C1/086—Descaling; Removing coating films
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/003—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods using material which dissolves or changes phase after the treatment, e.g. ice, CO2
    • 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
    • C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C22/73—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process
    • C23C22/74—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process for obtaining burned-in conversion coatings
    • 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

Definitions

  • the invention is in the field of components with a Layer that needs to be removed.
  • Components such as compressor blades (compressor blades), which are used at room temperature or at not too high temperatures, are provided with protective layers against corrosion and erosion. These have, for example, an inorganic binder with a metal.
  • the metal serves as a galvanic element (sacrificial anode) and is therefore electrically conductively connected to the substrate of the component.
  • Such coatings are present in a compressor, for example. Up to the sixth stage on the blades, which experience, for example, temperatures up to 200 ° C.
  • the binder is a mixture of different acids and can be converted by heat treatment into a vitreous structure. Such a layer is known from EP 0 142 418 B1.
  • Gas turbine blades are exposed to very high temperatures. Therefore, they are made of high temperature resistant materials for the necessary high temperature strength. In particular, superalloys based on nickel or cobalt come into question here.
  • a protective layer or a protective layer system against oxidation, corrosion and / or heat insulation is applied to the main body of such a gas turbine blade.
  • a metallic alloy of the type MCrAlX where M is at least one element from the group iron (Fe), cobalt (Co) and nickel (Ni), Cr is chromium, Al is aluminum and X for yttrium and / or at least one element of the rare earths stands.
  • a corrosion protection layer is often applied a ceramic thermal barrier coating. This is resistant to high temperatures and serves to shield the metallic base body from direct contact with the hot gas.
  • a typical material for a ceramic thermal barrier coating is yttrium-stabilized zirconia, which is applied by, for example, atmospheric plasma spraying (APS).
  • DE-A-205 87 66 shows a cleaning process for metallic, radioactively contaminated surfaces by means of an ice blast. For slightly soluble precipitation on the surface also a use of dry ice is proposed.
  • DE-C-196 36 305 shows a method for the elimination of Coatings and coverings from a sensitive surface. It is about deposits such as soot, moss, pollutant deposits. By means of a dry ice jet is a gentle removal the coverings or coatings of the sensitive ones Substrates possible.
  • a ceramic thermal barrier coating is in contrast made of a hard, durable material. Furthermore a ceramic thermal barrier coating is just designed to Temperature changes and thermal stresses endure (EP 13 17 995 A1). For this purpose, usually a stalk-shaped Structure constructed, which compensates thermal transient voltages allowed. The ceramic thermal barrier coating should thus actually just against thermo-mechanical abrasion attempts be insensitive.
  • the object of the invention is to provide a method with a layer of organic binder from a substrate can be removed without damaging the substrate.
  • the invention provides a method for removing one Layer of the surface of a component according to claim 1 ready.
  • thermoplastic materials oil, plastic, paints or ceramics.
  • inorganic binder especially when heat treated and glassy, can not be assigned to any of the above groups.
  • the surface of the component can thus be easily and completely free from the layer and high quality smooth, for example.
  • compressor blade coatings of a turbine are to be removed or reapplied (reprocessing)
  • the following problems must be solved.
  • complete removal of the coatings and, on the other hand, simultaneous protection of other, adjacent rotor assemblies in the removal treatment and cleaning of the stratified blades and the rotor assemblies of interfering blasting agent residues, application of the new coating and residue-free removal of covers.
  • the rotor is still installed with its blades in the turbine or removed from the turbine.
  • the blades are still mounted on a wheel disc or extended are also individually.
  • the stripping can take place with the inventive method on the fully assembled rotor. This eliminates the disassembly and assembly of the turbine blades when servicing a turbine.
  • the dry ice jet is also used for cleaning the component, in particular the gas turbine blade.
  • a cleaning is to be carried out in particular before coating a turbine blade. Any contamination may affect the adhesion of the applied coating.
  • the cleaning agent used such as sand when sandblasting, to include foreign material in the surface to be cleaned.
  • a dry ice jet this danger is avoided because the dry ice sublimates residue-free.
  • FIG. 1 shows a device 15 for removing layer material from the surface of a gas turbine blade 20.
  • a screw compressor 1 To produce a compressed air flow, a screw compressor 1, a surge tank 2, an adsorption dryer 3, a cooler 4 and a measuring system 5 are connected in series.
  • air is highly compressed, in particular to a pressure of 3 to 12 bar.
  • the expansion tank 2 serves to stabilize a constant mass flow.
  • the adsorption dryer 3 the air is dried and cooled in the cooler 4.
  • a measuring system 5 is used to record the compressed air parameters.
  • the compressed air stream is then fed to a pellet supply device 12.
  • dry ice pellets 6 are stored.
  • the dry ice pellets 6 are fed by means of a screw conveyor 7 via a rotary valve 8 to the compressed air flow and fed to it by means of a robot 9 movable Laval nozzle 10 (Fig. 3).
  • a dry ice jet 14 (FIG. 3) with, for example, speed of sound and strike a component 20, in particular a gas turbine blade 20, on the surface 40 of the layer 32, 36 to be removed or on the surface 38 of the substrate 30 of the component 20 (eg gas turbine blades ).
  • the gas turbine blade 20 is supported in a multi-axis retainer 22 so that the dry ice jet 14 can be directed to any point on the surface of the gas turbine blade 20.
  • b is an example of a longitudinal section through the Surface area of a component, in particular a Turbine blade 20 (compressor or Ver Whyrleit- or - moving blade) shown.
  • the layer 33, 32, 36 consists of at least one inorganic binder, wherein the binder is a mixture of at least two acids.
  • the binder may contain chromic acid ( H 2 CrO 3 ) and / or phosphorous acid (H 3 PO 3 ) and / or phosphoric acid (H 3 PO 4 ).
  • the binder is 100% inorganic binder.
  • the binder contains 20% phosphorous acid, 50% chromic acid and 30% phosphoric acid.
  • the phosphorous acid in the binder may be at least partially or entirely replaced by magnesium oxide (MgO).
  • composition and method of preparation is described in EP 0 142 418 B1 and forms part of this disclosure.
  • a heat treatment was carried out with this layer 33, 32, 36, so that a vitreous layer is formed on the substrate 30 of the component 20.
  • Glass-like means that the layer 33, 32, 36 has similar thermal and / or mechanical properties as a glass and differs from the thermal and / or mechanical properties of a metal and a ceramic.
  • this binder that is an acid mixture, for example, up to 50% of a metal, for example aluminum may be added.
  • This metal is added, for example, as a metal pigment and serves as a sacrificial material.
  • the layer 33, 32, 36 may also contain a metal phosphate formed by reaction of the binder components, in particular a chromium phosphate. Chromium phosphate is formed from the reaction of chromic acid and phosphoric acid.
  • a duplex layer 32, 36 or residues thereof can also be completely removed by means of the dry ice jet 14.
  • the layer system consists for example of a first layer 32 (base coat) and a second coat 36 (top coat).
  • the first layer 32 consists of an acid mixture which, as already described above, contains chromic acid, phosphorous acid and / or magnesium oxide and phosphoric acid.
  • the layer contains a metal as a sacrificial material against corrosion.
  • a second layer 36 which also consists of an acid mixture as described above, but does not contain any metal as a sacrificial material against corrosion.
  • the inorganic binder always forms one Matrix of duplex layer 32, 36.
  • the method can be applied to compressor run and guide vanes as well as turbine guide vanes and vanes Steam or gas turbines having such layers 33, 32, 36. Also housing parts of a turbine 100 ( Figure 4), the one Layer can also with the inventive Procedures are treated.
  • Compressor blades (blades and vanes) of turbines are used to prevent Corrosion and erosion coated with coating systems.
  • FIG. 4 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a compressor 105 which comprises, for example, blades with a inorganic binder containing layer 33, 32, 36, for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed of two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are in this case on an inner housing 138 a stator 143 attached, whereas the blades 120 a series 125, for example by means of a turbine disk (Wheel) 133 are mounted on the rotor 103.
  • a turbine disk (Wheel) 133 On the rotor 103 is coupled to a generator or a work machine (not shown).
  • the gas turbine 100 During operation of the gas turbine 100 is from the compressor 105 sucked and compressed by the intake 104 104 air 135.
  • the at the turbine end of the compressor 105th provided compressed air is the burners 107th guided and mixed there with a fuel.
  • the mixture is then to form the working medium 113 in the combustion chamber 110 burned.
  • the working medium 113 flows along the hot gas channel 111 past the vanes 130 and the blades 120.
  • the blades 120 relaxes the Working medium 113 pulse transmitting, so that the blades 120 drive the rotor 103 and this coupled to him Working machine.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the substrates may have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the material used is iron-, nickel- or cobalt-based superalloys. For example, superalloys are used, as are known from EP 1 204 776, EP 1 306 454, EP 1 319 729, WO 99/67435 or WO 00/44949; these writings are part of the revelation.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is yttrium (Y) and / or at least one element of the rare Erden) and have heat through a thermal barrier coating.
  • the thermal barrier coating consists for example of ZrO 2 Y 2 O 4 -ZrO 2 , ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced in the thermal barrier coating.
  • the vane 130 has an inner housing 138 of the Turbine 108 facing Leitschaufelfuß (not shown here) and a vane foot opposite Guide vane head on.
  • the vane head is the rotor 103 facing and on a mounting ring 140 of the stator 143rd established.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04002334A 2004-02-03 2004-02-03 Procédé d'enlèvement d'une couche d'un élément Ceased EP1561542A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04002334A EP1561542A1 (fr) 2004-02-03 2004-02-03 Procédé d'enlèvement d'une couche d'un élément

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04002334A EP1561542A1 (fr) 2004-02-03 2004-02-03 Procédé d'enlèvement d'une couche d'un élément

Publications (1)

Publication Number Publication Date
EP1561542A1 true EP1561542A1 (fr) 2005-08-10

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EP04002334A Ceased EP1561542A1 (fr) 2004-02-03 2004-02-03 Procédé d'enlèvement d'une couche d'un élément

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2446056A (en) * 2007-01-23 2008-07-30 Alstom Technology Ltd Removing coatings using a dry ice blast
DE102007022174B3 (de) * 2007-05-11 2008-09-18 Voestalpine Stahl Gmbh Verfahren zum Erzeugen und Entfernen einer temporären Schutzschicht für eine kathodische Beschichtung
WO2009032221A1 (fr) 2007-08-28 2009-03-12 Rem Technologies Inc Procédé pour inspecter et remettre en état des composants mécaniques
WO2009106042A1 (fr) * 2008-02-26 2009-09-03 Mtu Aero Engines Gmbh Procédé pour le nettoyage de pièces de turbine à gaz
DE102009053630A1 (de) * 2009-11-17 2011-05-19 Bayerische Motoren Werke Aktiengesellschaft Katalysatorreinigung
WO2012022510A1 (fr) 2010-08-19 2012-02-23 Voestalpine Stahl Gmbh Procédé pour conditionner la surface d'éléments en tôle d'acier trempés protégés contre la corrosion

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0142418A1 (fr) * 1983-10-19 1985-05-22 Sermatech International Inc. Particles d'aluminium sphériques dans des revêtements
EP1317995A1 (fr) * 2001-12-05 2003-06-11 Siemens Aktiengesellschaft Procédé et dispositif de lissage de surface d'une aube de turbine à gaz
EP1321625A1 (fr) * 2001-12-21 2003-06-25 Siemens Aktiengesellschaft Methode permettant d'enlever une couche métallique
US6585569B2 (en) * 2000-12-28 2003-07-01 General Electric Company Method of cleaning gas turbine compressors using crushed, solid material capable of sublimating

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0142418A1 (fr) * 1983-10-19 1985-05-22 Sermatech International Inc. Particles d'aluminium sphériques dans des revêtements
US6585569B2 (en) * 2000-12-28 2003-07-01 General Electric Company Method of cleaning gas turbine compressors using crushed, solid material capable of sublimating
EP1317995A1 (fr) * 2001-12-05 2003-06-11 Siemens Aktiengesellschaft Procédé et dispositif de lissage de surface d'une aube de turbine à gaz
EP1321625A1 (fr) * 2001-12-21 2003-06-25 Siemens Aktiengesellschaft Methode permettant d'enlever une couche métallique

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2446056A (en) * 2007-01-23 2008-07-30 Alstom Technology Ltd Removing coatings using a dry ice blast
GB2446056B (en) * 2007-01-23 2011-10-19 Alstom Technology Ltd Method for treating a thermally loaded component
DE102007022174B3 (de) * 2007-05-11 2008-09-18 Voestalpine Stahl Gmbh Verfahren zum Erzeugen und Entfernen einer temporären Schutzschicht für eine kathodische Beschichtung
US9822436B2 (en) 2007-05-11 2017-11-21 Voestalpine Stahl Gmbh Method for the production and removal of a temporary protective layer for a cathodic coating
WO2009032221A1 (fr) 2007-08-28 2009-03-12 Rem Technologies Inc Procédé pour inspecter et remettre en état des composants mécaniques
EP2195139B1 (fr) * 2007-08-28 2014-11-12 REM Technologies, Inc. Procédé pour inspecter et remettre en état des composants mécaniques
US9180568B2 (en) 2007-08-28 2015-11-10 Rem Technologies, Inc. Method for inspecting and refurbishing engineering components
WO2009106042A1 (fr) * 2008-02-26 2009-09-03 Mtu Aero Engines Gmbh Procédé pour le nettoyage de pièces de turbine à gaz
DE102009053630A1 (de) * 2009-11-17 2011-05-19 Bayerische Motoren Werke Aktiengesellschaft Katalysatorreinigung
WO2012022510A1 (fr) 2010-08-19 2012-02-23 Voestalpine Stahl Gmbh Procédé pour conditionner la surface d'éléments en tôle d'acier trempés protégés contre la corrosion
DE102010037077A1 (de) 2010-08-19 2012-02-23 Voestalpine Stahl Gmbh Verfahren zum Konditionieren der Oberfläche gehärteter korrosionsgeschützter Bauteile aus Stahlblech

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