EP1831427A1 - Methode de fabrication d'un component d'une turbine et le component d'une turbine - Google Patents

Methode de fabrication d'un component d'une turbine et le component d'une turbine

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Publication number
EP1831427A1
EP1831427A1 EP05797128A EP05797128A EP1831427A1 EP 1831427 A1 EP1831427 A1 EP 1831427A1 EP 05797128 A EP05797128 A EP 05797128A EP 05797128 A EP05797128 A EP 05797128A EP 1831427 A1 EP1831427 A1 EP 1831427A1
Authority
EP
European Patent Office
Prior art keywords
component
mei
treatment
layer
turbine
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
EP05797128A
Other languages
German (de)
English (en)
Inventor
Rene Jabado
Daniel Körtvelyessy
Ralph Reiche
Michael Rindler
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 EP05797128A priority Critical patent/EP1831427A1/fr
Publication of EP1831427A1 publication Critical patent/EP1831427A1/fr
Ceased legal-status Critical Current

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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
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F1/00—Etching metallic material by chemical means
    • 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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/02—Pretreatment of the material to be coated
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25F—PROCESSES FOR THE ELECTROLYTIC REMOVAL OF MATERIALS FROM OBJECTS; APPARATUS THEREFOR
    • C25F3/00—Electrolytic etching or polishing
    • C25F3/02—Etching
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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

Definitions

  • the invention relates to a method for producing a component according to claim 1, in which an oxide layer can form ⁇ and a component according to claim 14 or 15.
  • bil ⁇ often an oxide layer, where "metal" atoms from the component to the interface component metal oxide and diffuse the component depleted in the region below the oxide layer to the metal element ⁇ sem.
  • Hot gas-loaded components in gas turbines are often protected by thermal barrier coatings on MCrAlX adhesion promoter layers.
  • the adhesion of the thermal barrier coating on the MCrAlX layer is essentially generated by an aluminum oxide layer between the MCrAlX layer and the thermal barrier coating.
  • the thermal oxide (TGO) layer grows during operation until it eventually fails adhesion.
  • the MCrAlX layers are provided with a platinization, which is supposed to slow down the growth of the TGO as a diffusion barrier.
  • this process is expensive because pure platinum is used and an additional coating process increases costs.
  • the platinum diffuses into the substrate of the component.
  • refurbishment the reprocessing of the component, to a change in the known reprocessing processes, since the platinum leads to an increased attack of acid on the substrate.
  • the object is achieved by a method according to claim 1. It is a further object of the invention to istzei ⁇ a component, in which an oxide layer is formed slower.
  • FIG. 6 shows a turbine blade
  • FIG. 7 shows a combustion chamber element
  • FIG. 8 shows a gas turbine
  • Figure 1 shows an example of a component 1, which is treated by the method according to the invention.
  • the component 1 consists for example of a metallic substrate 4.
  • the substrate 4 may be an elementary metal or an alloy. Of course, secondary phases may also be present.
  • Turbine blades 120, 130 (FIG. 6), heat shield elements 155 (FIG. 7) of gas turbines 100 (FIG. 8) or steam turbines, the substrate 4 is an iron, cobalt or nickel based superalloy.
  • a corrosion protection ⁇ or primer layer 7 is present on the substrate 4, for example. It consists in the case Turbine components usually made of an alloy of the type MCrAlX.
  • the corrosion protection layer 7 may have been alitiert and / or chromed in the region of its outer surface 22, so that in the protective layer 7, a surface region 13 has formed, the protective layer opposite the other underlying area of the corrosion 7 an increased concentra ⁇ tion of aluminum and / or chromium.
  • Figure 2 shows an example of a further component 1, may be treated with ⁇ means of the inventive method.
  • the component has no corrosion protection ⁇ layer and is for example in the region of its outer surface 25 alitized and / or chromed, located so that a surface region is formed 10, 4 (for example, tion of a superalloy) over the remaining substrate a has increased concentration of aluminum and / or chromium.
  • an oxide layer Mel y Me2 z O x forms and / or a mixture of MeIO x and Me2O x at least one element MeI, Me2, wherein the at least one element MeI, Me2, for example, a metal oxide-forming element
  • the corrosion protection layer 7, the aged anticorrosive layer 7, the substrate 4 or the alitATOR substrate 4 is subjected to a treatment in which the Metal or the alloy is depleted at least one element MeI, Me2, which forms an oxide layer 28 (Fig. 3).
  • the Metal or the alloy is depleted at least one element MeI, Me2, which forms an oxide layer 28 (Fig. 3).
  • voids or locally depleted regions 16 form in the crystal lattice. There is no or little removal of a layer region at the surface 22, 25 instead. Rather, in the corrosion protection layer 7 or the substrate 4 (not shown), only depleted regions are formed on this element MeI, Me2.
  • Corrosion protection layer 7 or a substrate 4 is valid: the layer region which is depleted of the element aluminum and / or chromium, but is preferably thinner than the layer region 10, 13, which was alitiert or chromed.
  • the elements are either aluminum or chromium resp. Chromium and aluminum, to which the substrate 4 or the layer 7 is depleted.
  • the thus treated surface 22, 25 can be slightly pre-oxidized prior to use and forms the oxide layer 28, in which case a ceramic thermal barrier coating 19 (FIG. 3, dashed line on the right) can be applied.
  • a ceramic thermal barrier coating 19 FIG. 3, dashed line on the right
  • the oxide layer 28 continues to grow on the corrosion protection layer 7.
  • the ceramic thermal barrier coating 19 can also without pre-oxidation directly on the corrosion protection layer 7 or on the substrate 4 with the at least one element
  • the oxide layer 28 is formed during operation between the corrosion protection layer 7 and the ceramic thermal barrier coating 19.
  • the depletion of the substrate 4 or the corrosion protection layer 7 on at least one element MeI, Me2 takes place according to the invention, for example, by a treatment one in contact with a treatment fluid, ie by or more acids or.
  • a treatment fluid ie by or more acids or.
  • Bases or mixtures of bases an electrolyte treatment (ie applying an electrical voltage) or exposure of the component 1 in an environment with at least one halogen, in particular fluorine or chlorine, or at least one halide, as it is known from the Fluori- dionentivitesprozes s.
  • TGO grows much slower, in particular by up to approx. 20 ⁇ m per service cycle less than known from the prior art, whereby a gain of several thousand hours of operation of the component 1 is achieved at high temperatures.
  • the surface 22, 25 of the anticorrosive layer 7 or the substrate 4 can be roughened by the treatment, so that s Kluften 31 form ( Figure 4), resulting in a better adhesion of the ceramic thermal barrier coating 19 in particular a plasma sprayed thermal barrier coating (APS: atmospheric plasma spraying , VPS: Vacuum Plasma Spraying, LPPS: Low Pressure Plasma Spraying).
  • APS atmospheric plasma spraying
  • VPS Vacuum Plasma Spraying
  • LPPS Low Pressure Plasma Spraying
  • a corrosion protective layer 7 can for example be used whose chemical composition of EP 0786017 Bl, EP 0 412 397 Bl or EP 1 306 454 Al, EP 0 486 489 Bl, is known, wherein the chemical composition ⁇ reduction these corrosion protection layers To be the subject of this disclosure.
  • Figure 5 shows an enlarged view of the corrosion ⁇ protective layer 7 or the substrate. 4
  • the corrosion protection layer 7 consists for example of individual grains 37 (granular or columnar), which have grain boundaries 34 with one another.
  • an oxide layer is formed on the grain boundaries 34 at least in places, which is prepared in particular by the method according to the invention.
  • Used corrosion protection layers 7 are completely removed for reprocessing, wherein they are usually treated for 4 - 8 hours at an elevated temperature of 50 0 C - 80 0 C with an acid. The treatment times with one acid, one base, one
  • Electrolyte or a halogen / halide according to the inventions ⁇ to the invention method are considerably shorter in contrast. They are reduced to 50%, in particular to 25% of these usual treatment times, and amount to a maximum of 1 hour (h), in particular hh.
  • the treatment temperatures can remain the same, but are more at the lower end of the temperature ranges used for the removal of anticorrosive coatings.
  • the treatment time is in a hydrochloric acid, for example ⁇ with a concentration of 30%, at 50 0 C for 30 minutes.
  • the concentration of hydrochloric acid can be reduced to 5%, and also the treatment time is shorter, for example 10 minutes.
  • voltages of 0, 1 to 0, 34 volts are used.
  • FIG. 6 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and an airfoil 406.
  • the vane 130 may have tip at its vane 415 a further platform (not Darge ⁇ asserted).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a medium which flows past felblatt 406 at the spectacle ⁇ a leading edge 409 and a trailing edge on the 412th
  • blade 120, 130 for example, solid metallic materials are used in all regions 400, 403, 406 of the blade 120, 130.
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Stem-crystal structures which probably have longitudinally extending grain boundaries, but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
  • Refurbishment means that components 120, 130 may have to be freed from protective layers after use (eg by sandblasting). Thereafter, a removal of the corrosion and / or oxidation layers or. -Products . Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and has possibly. still film cooling holes 418 (dashed hinted ⁇ tet) on. As a protection against corrosion, the blade 120, 130 in ⁇ example corresponding, mostly metallic coatings (MCrAlX), which can be treated by the method according to the invention and as protection against heat mostly a ceramic coating.
  • MrAlX metallic coatings
  • FIG. 7 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 102 arranged around the turbine shaft 103 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 in its entirety is configured as a ringför ⁇ shaped structure which is positioned around the turbine shaft 103 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C. to 1600 ° C.
  • the combustion chamber wall 153 is on its side facing the working medium M facing side with a from heat shield elements 155 formed inner lining provided.
  • Each heat shield element 155 is the working medium side with a particularly hit ⁇ zebe drivingn protective layer or made of high-tempe ⁇ raturbe operatingm material. Due to the high temperatures in the interior of the combustion chamber 110 is also for the heat shield elements 155 and. provided for the holding elements, a cooling system.
  • the materials of the combustion chamber wall and its coatings may be similar to the turbine blades.
  • FIG. 8 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has an axis by a rotational ⁇ 102 rotatably mounted rotor 103, which is also referred to as the turbine rotor.
  • an intake housing 104 a compressor 105, for example a toroidal combustion chamber 110, in particular annular combustion chamber 106, with several ⁇ coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example a toroidal combustion chamber 110, in particular annular combustion chamber 106, with several ⁇ 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.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from 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 fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 unwinds on the rotor blades 120 in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and the rotor couples to it Work 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 highest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106.
  • substrates of the components may have a directional structure, i. H . they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • iron, nickel or cobalt-based alloys used Superle-.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; these writings are part of the revelation.
  • blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one member of the group
  • Iron [Fe], cobalt [Co], nickel [Ni], X is an active element and stands for yttrium [Y] and / or silicon and / or at least one rare earth element or element.
  • Hafnium [Hf]) which can be treated by the method according to the invention.
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 Bl, EP 0 412 397 B1 or EP 1 306 454 A1, which are intended to be part of this disclosure.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , d. H . it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide. By suitable coating methods such.
  • EB-PVD Electron beam evaporation
  • the guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not provide Darge ⁇ here) and a side opposite the guide-blade root vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • General Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Electrochemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Les composants de turbine forment, pendant leur utilisation, des couches d'oxyde qui, en raison de leur croissance rapide indésirable, entraînent une détérioration du substrat des composants. Selon le procédé de l'invention, le composant (1) est appauvri en un élément de sorte que la croissance de la couche d'oxyde (28) soit réduite.
EP05797128A 2004-12-30 2005-10-18 Methode de fabrication d'un component d'une turbine et le component d'une turbine Ceased EP1831427A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05797128A EP1831427A1 (fr) 2004-12-30 2005-10-18 Methode de fabrication d'un component d'une turbine et le component d'une turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04031008A EP1676938A1 (fr) 2004-12-30 2004-12-30 Methode de fabrication d'un component d'une turbine et le component d'une turbine
PCT/EP2005/055331 WO2006072479A1 (fr) 2004-12-30 2005-10-18 Procede pour produire un composant d'une turbine et composant d'une turbine
EP05797128A EP1831427A1 (fr) 2004-12-30 2005-10-18 Methode de fabrication d'un component d'une turbine et le component d'une turbine

Publications (1)

Publication Number Publication Date
EP1831427A1 true EP1831427A1 (fr) 2007-09-12

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EP04031008A Withdrawn EP1676938A1 (fr) 2004-12-30 2004-12-30 Methode de fabrication d'un component d'une turbine et le component d'une turbine
EP05797128A Ceased EP1831427A1 (fr) 2004-12-30 2005-10-18 Methode de fabrication d'un component d'une turbine et le component d'une turbine

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EP04031008A Withdrawn EP1676938A1 (fr) 2004-12-30 2004-12-30 Methode de fabrication d'un component d'une turbine et le component d'une turbine

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US (1) US8518485B2 (fr)
EP (2) EP1676938A1 (fr)
WO (1) WO2006072479A1 (fr)

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EP2119805A1 (fr) * 2008-05-15 2009-11-18 Siemens Aktiengesellschaft Procédé de fabrication d'une couche adhésive optimisée par l'évaporation partielle de la couche adhésive
SG161130A1 (en) * 2008-11-06 2010-05-27 Turbine Overhaul Services Pte Methods for repairing gas turbine engine components
EP2435595B1 (fr) * 2009-05-26 2020-07-29 Siemens Aktiengesellschaft Système de revêtement stratifié présentant une couche de mcralx et une couche riche en chrome, ainsi que procédé pour sa production
US10711361B2 (en) * 2017-05-25 2020-07-14 Raytheon Technologies Corporation Coating for internal surfaces of an airfoil and method of manufacture thereof

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Also Published As

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US8518485B2 (en) 2013-08-27
US20100047592A1 (en) 2010-02-25
WO2006072479A1 (fr) 2006-07-13
EP1676938A1 (fr) 2006-07-05

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