EP1692372A1 - Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur - Google Patents

Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur

Info

Publication number
EP1692372A1
EP1692372A1 EP04801187A EP04801187A EP1692372A1 EP 1692372 A1 EP1692372 A1 EP 1692372A1 EP 04801187 A EP04801187 A EP 04801187A EP 04801187 A EP04801187 A EP 04801187A EP 1692372 A1 EP1692372 A1 EP 1692372A1
Authority
EP
European Patent Office
Prior art keywords
barrier coating
thermal barrier
housing
insulation layer
heat insulation
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Withdrawn
Application number
EP04801187A
Other languages
German (de)
English (en)
Inventor
Friedhelm Schmitz
Kai Wieghardt
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 EP04801187A priority Critical patent/EP1692372A1/fr
Publication of EP1692372A1 publication Critical patent/EP1692372A1/fr
Withdrawn legal-status Critical Current

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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • 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
    • C23C28/341—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 carbide 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
    • 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
    • C23C28/347—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 layers adapted for cutting tools or wear applications
    • 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
    • C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/047—Nozzle boxes
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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

  • thermal barrier coating for a housing of a steam turbine and a steam turbine
  • the invention relates to the use of a thermal barrier coating according to claim 1 or 2 and a steam turbine according to claim 29.
  • Thermal insulation layers which are applied to components, are known from the field of gas turbines, as they are e.g. are described in EP 1 029 115 or WO 00/25005.
  • the thermal barrier coating is applied in the colder area of a steam inflow area.
  • GB 1 556 274 discloses a turbine disk with a thermal barrier coating in order to reduce the heat input into the thinner areas of the turbine disk.
  • US 4, 405,284 discloses a two-layer ceramic outer layer to improve the abrasion behavior.
  • the patent specification 723 476 discloses a housing which is made in two parts and has an outer ceramic layer which is made thick.
  • the housing parts of one housing are arranged one above the other, but not axially next to one another.
  • Thermal insulation layers allow components to be used at higher temperatures than the base material alone or extend the service life.
  • Known base materials enable operating temperatures of a maximum of 1000 ° C - 1100 ° C, whereas a coating with a thermal insulation layer enables operating temperatures of up to 1350 ° C in gas turbines.
  • the radial and axial clearances between the rotor and stator are essential for the efficiency of a steam turbine.
  • the deformation of the steam turbine housing is to position the guide vanes in relation to the rotor blades attached to the shaft.
  • These housing deformations contain thermal components (from heat input) and viscoplastic components (from component creep or relaxation).
  • impermissible viscoplastic deformations adversely affect their function (e.g. valve tightness).
  • the object of the invention is to overcome the problems mentioned.
  • the object is achieved by the use of a thermal barrier coating for a housing for a steam turbine according to claim 1 or 2.
  • the object is further solved 'by a steam turbine according to claim 29, having a thermal barrier coating with locally differing parameters (materials, porosity, thickness). Local means regions of the surfaces of one or more components of a turbine that are spatially delimited from one another.
  • the thermal barrier coating does not necessarily only serve that
  • the controlled influencing of the deformation behavior in the case of a radial gap between the turbine rotor and the turbine stator, that is to say the turbine blade and a housing, has an advantageous effect by minimizing this radial gap. Minimizing the radial gap leads to an increase in the efficiency of the turbine.
  • the controlled deformation behavior advantageously allows axial gaps in a steam turbine, in particular between the rotor and the housing, to be set and minimized in a controlled manner.
  • an integral temperature of the housing is lower than the temperature of the shaft due to the application of the thermal barrier coating, so that the radial gap between the rotor and stator, i.e. between the blade tip and the housing or between the guide blade tip and the shaft, during operation (higher temperatures than room temperature) is smaller than during assembly (room temperature).
  • a reduction in the transient thermal deformation of housings and their adaptation to the deformation behavior of the mostly thermally inert turbine shaft also brings about a reduction in the radial play to be provided. Applying a thermal barrier coating also reduces viscous creep deformation and the component can be used for longer.
  • the thermal barrier coating can advantageously be used for newly manufactured, used (i.e. no repair is necessary) and remanufactured components.
  • FIG. 5 1, 2, 3, 4 possible arrangements of a thermal insulation layer of a component
  • FIG. 5 6 a gradient of the porosity within the thermal insulation layer of a component
  • 7, 9 the influence of a temperature difference on a component
  • Figure 8 is a steam turbine
  • FIG. 18 shows the influence of a thermal barrier coating on the service life of a reprocessed component.
  • Figure 1 shows a first embodiment of a component 1 for use in the invention.
  • Component 1 is a component or housing, in particular a housing 335 of an inflow region 333 of a turbine (gas,
  • the heat insulation layer 7 is in particular a ceramic layer made, for example, of zirconium oxide (partially stabilized, fully stabilized by yttrium oxide) and / or magnesium oxide) and / or titanium oxide, and is for example thicker than 0.1 mm. So thermal insulation layers 7, which consist 100% of either zirconium oxide or titanium oxide, can be used.
  • the ceramic layer can be applied by means of known coating methods such as atmospheric plasma spraying (APS), vacuum plasma spraying (VPS), low pressure plasma spraying (LPPS), and by chemical or physical coating methods (CVD, PVD).
  • FIG. 2 shows a further embodiment of component 1 for the use according to the invention.
  • At least one intermediate protective layer 10 is arranged between the substrate 4 and the heat insulation layer 7.
  • the intermediate protective layer 10 serves to protect against corrosion and / or oxidation of the substrate 4 and / or for better connection of the thermal insulation layer to the substrate 4. This is particularly the case when the thermal insulation layer consists of ceramic and the substrate 4 consists of a metal.
  • the intermediate protective layer 10 for protecting a substrate 4 against corrosion and oxidation at a high temperature essentially has, for example, the following elements (details of the proportions in percent by weight): 11.5 to 20.0 wt% chromium, 0.3 to 1.5 wt % Silicon, 0.0 to 1.0 wt% aluminum, 0.0 to 0.7 wt% yttrium and / or at least one equivalent metal from the group comprising scandium and the rare earth elements, remainder iron, cobalt and / or Nickel and manufacturing-related impurities;
  • the metallic intermediate protective layer 10 consists of 12.5 to 14.0 wt% chromium, 0.5 to 1.0 wt% silicon, 0.1 to 0.5 wt% aluminum, 0.0 to 0.7 wt% yttrium and / or at least one equivalent metal from the group comprising scandium and the rare earth elements, remainder iron and / or cobalt and / or nickel as well as production-related impurities. It is preferred if the rest is only iron
  • the composition of the intermediate protective layer 7 based on iron shows particularly good properties, so that the protective layer 7 is excellently suitable for application to ferritic substrates 4.
  • the thermal expansion coefficients of substrate 4 and intermediate protective layer 10 can be matched to one another very well or even be the same, so that there is no thermally caused stress build-up between substrate 4 and intermediate protective layer 10 (thermal mismatch). match), which could cause the intermediate contactor layer 10 to flake off.
  • the substrate 4 is then a ferritic base alloy, a steel or a nickel or cobalt-based super alloy, in particular a 1% CrMoV steel or a 10 to 12 percent chromium steel.
  • ferritic substrates 4 of the component 1 consist of a
  • FIG. 3 shows a further exemplary embodiment of component 1 for the use according to the invention.
  • An erosion protection layer 13 now forms the outer surface on the heat insulation layer 7. It consists in particular of a metal or a metal alloy and protects the component 1 against erosion and / or wear, as is the case in particular in steam turbines 300, 303 (FIG. 8) which have scaling in the superheated steam area, where mean flow velocities of about 50m / s (ie 20 - 100m / s), and pressures of up to 400 bar occur.
  • the heat insulation layer 7 has a certain open and / or closed porosity.
  • the wear / erosion protection layer 13 preferably has a higher density and consists of alloys based on iron, chromium, nickel and / or cobalt or MCrAlX or, for example, NiCr 80/20 or with admixtures of boron (B) and silicon (Si) NiCrSiB or NiAl (for example Ni: 95%, AI 5%).
  • a metallic erosion protection layer 13 can be used in steam turbines 300, 303, since the operating temperatures in steam turbines 300, 303
  • Steam inflow range 33 is a maximum of 800 ° C or 850 ° C. For such temperature ranges, there are enough metallic layers that have a sufficiently large necessary erosion protection over the period of use of the component 1.
  • Metallic erosion protection layers 13 in gas turbines on a ceramic thermal barrier coating 7 are not possible there everywhere, since metallic erosion protection layers 13 as the outer layer cannot withstand the maximum individual temperatures of up to 1350 ° C. Ceramic erosion protection layers 13 are also conceivable.
  • chromium carbide Cr 3 C 2
  • WC-CrC-Ni a mixture of tungsten carbide, chromium carbide and nickel
  • chromium carbide with the addition of nickel Cr 3 C 2 -Ni
  • Cr 3 C 2 -Ni nickel
  • Cr 3 C 2 -NiCr nickel chromium carbide with the addition of nickel
  • Cr 3 C 2 -NiCr nickel chromium carbide with a Portion of 83 wt% chromium carbide and 17 wt% nickel as well as a mixture of chromium carbide and nickel chromium (Cr 3 C 2 -NiCr) for example with a proportion of 75 wt% chromium carbide and 25 wt% nickel chromium as well as yttrium stabilized zirconium oxide for example with a weight proportion of 80 wt% zirconium oxide and 20 wt% yttrium oxide.
  • an intermediate protective layer 10 can also be present (FIG. 4).
  • FIG. 5 shows a heat insulation layer 7 with a gradient of the porosity. Pores 16 are present in the thermal barrier coating 7. In.
  • the density p of the thermal insulation layer 7 increases in the direction of an outer surface (direction of arrow).
  • FIGS. 7a, b show the influence of the thermal barrier coating 7 on the thermally induced deformation behavior of the component 1.
  • FIG. 7a shows a component without a thermal barrier coating. Two different temperatures prevail on two opposite sides of the substrate 4, a higher temperature T max and a lower temperature T m i n, whereby a radial temperature difference dT is given (4).
  • the substrate 4 extends in the area of higher temperature T max due to thermal expansion significantly higher than in the region of the smaller temperature T m i n. This different expansion causes an undesirable deformation of a housing.
  • a thermal insulation layer 7 is present on the substrate 4, the substrate 4 and the thermal insulation layer 7 together being, for example, just as thick as the substrate 4 in FIG. 7a.
  • the steam turbine has a high-pressure sub-turbine 300 and a medium-pressure sub-turbine 303, each with an inner casing 312 and an outer casing 315 surrounding it.
  • the medium pressure turbine section 303 is designed with two passages. It is also possible for the medium-pressure turbine section 303 to be single-flow.
  • a bearing 318 is arranged along the axis of rotation 306 between the high-pressure sub-turbine 300 and the medium-pressure sub-turbine 303, the turbine shaft 309 having a bearing region 321 in the bearing 318.
  • the turbine shaft 309 is supported on a further bearing 324 next to the high-pressure sub-turbine 300.
  • the high-pressure turbine section 300 has a shaft seal 345.
  • the turbine shaft 309 is sealed off from the outer housing 315 of the medium-pressure partial turbine 303 by two further shaft seals 345.
  • the turbine shaft 309 in the high-pressure sub-turbine 300 has the high-pressure rotor blades 354, 357.
  • the medium-pressure partial turbine 303 has a central steam inflow region 333 with the inner housing 335 and the outer housing 334.
  • the turbine shaft 309 Associated with the steam inflow region 333, the turbine shaft 309 has a radially symmetrical shaft shield 363, a cover plate, on the one hand for dividing the steam flow into the two flows of the medium-pressure turbine section 303 and for preventing direct contact of the hot steam with the turbine shaft 309.
  • the turbine shaft 309 has a second region in housings 366, 367 of the blading regions with the medium-pressure rotor blades 354, 342 in the medium-pressure turbine part 303.
  • the hot steam flowing through the second blading area flows from the medium-pressure sub-turbine 303 from an outflow connection 369 to a low-pressure sub-turbine, not shown, which is connected downstream in terms of flow technology.
  • the turbine shaft 309 is composed of two sub-turbine shafts 309a and 309b, which are firmly connected to one another in the region of the bearing 318.
  • the steam inflow region 333 of any steam turbine type has a heat insulation layer 7 and / or an erosion protection layer 13.
  • the controlled deformation behavior by applying a thermal barrier coating can in particular increase the efficiency of a steam turbine 300, 303. This is done, for example, by minimizing the radial gap (radial, i.e. perpendicular to axis 306) between the rotor and stator parts (housing) (Fig. 16, 17). An axial gap 378 (parallel to axis 306) can also be minimized by the controlled deformation behavior of the blading of the rotor and housing.
  • thermal barrier coating 7 only refer to components 1 of a steam turbine 300, 303 by way of example.
  • FIG. 9 shows the effect of locally different temperatures on the axial expansion behavior of a component.
  • FIG. 9a shows a component 1 which expands (dl) due to an increase in temperature (dT).
  • the thermal linear expansion dl is indicated by dashed lines.
  • a mounting, storage or fixation of the component 1 allows this expansion.
  • FIG. 9b also shows a component 1 that expands due to an increase in temperature.
  • the temperatures in different areas of the component 1 are different.
  • the temperature T 333 is greater than the temperature T 366 of the subsequent blading region (housing 366) and larger than in a further, subsequent housing 367 (T 3S7 ).
  • T 3S7 a further, subsequent housing 367
  • the reference numeral 333 g ieic_ ⁇ the thermal expansion of the inflow region 333, if all the areas or housing 333, 366, 367, a uniform increase in temperature would experience.
  • the temperature in the inflow region 333 is higher than in the surrounding housings 366 and 367, the inflow region 333 expands more than is indicated by the dashed lines 333 '.
  • the inflow region 333 Since the inflow region 333 is arranged between the housing 366 and a further housing 367, the inflow region 333 cannot expand freely, so that there is an uneven deformation behavior. By applying the thermal barrier coating 7, the deformation behavior should be controlled and / or evened out.
  • FIG. 10 shows an enlarged representation of a region 333 of the steam turbine 300, 303.
  • the steam turbine 300, 303 in the vicinity of the inflow region 333 consists of an outer housing 334, at which temperatures, for example between 250 ° C. to 350 ° C., are present and one Inner housing 335, at which temperatures for example from 450 ° to 620 ° C, but also up to 800 ° C. prevail, so that there are, for example, temperature differences greater than 200 ° C.
  • the heat insulation layer 7 is applied to the inner housing 335 of the steam inflow region 333 on the inside 336. For example, no thermal insulation layer 7 is applied to the outside 337.
  • the application of a thermal insulation layer 7 reduces the heat input into the inner housing 335, so that the thermal expansion behavior of the housing 335 of the inflow region 333 and the overall deformation behavior of the housings 335, 366, 367 are influenced. As a result, the entire deformation behavior of the inner housing 334 or of the outer housing 335 can be set in a controlled manner and evened out.
  • the deformation behavior of a housing or of housings among one another can be adjusted by varying the thickness of the thermal insulation layer 7 (FIG. 12) and / or by applying different materials at different locations on the surface of the housing, see for example inner housing 335 in FIG. 13. Likewise, the porosity can be different at different locations on the inner housing 335 (FIG. 14).
  • the heat insulation layer 7 can be locally limited, for example only applied in the inner housing 335 in the region of the inflow region 333. Likewise, the thermal barrier coating 7 can only be applied locally in the blading area 366 (FIG. 11).
  • FIG. 12 shows a further exemplary embodiment of using a thermal insulation layer 7.
  • the thickness of the heat insulation layer 7 is thicker in the inflow area 333, for example at least 50% thicker than in the housing 366 of the blading area of the steam turbine 300, 303.
  • the heat input and thus the thermal expansion and thus the deformation behavior of the inner housing 334, consisting of the inflow region 333 and the housing 366 of the blading region, are adjusted in a controlled manner and made uniform (over the axial length) by the thickness of the thermal insulation layer 7.
  • a different material can be present in the area of the inflow area 333 than in the housing 366 of the blading area.
  • FIG. 13 shows different materials of the thermal barrier coating 7 in different housings 335, 366 of the component 1.
  • a thermal barrier coating 7 is applied in the areas or the housings 335, 366.
  • the heat insulation layer 8 in the area of the inflow area 333 consists of a first heat insulation layer material
  • the material of the heat insulation layer 9 in the housing 366 of the blading area consists of a second heat insulation layer material.
  • the different material for the thermal insulation layers 8, 9 achieves a different thermal insulation, as a result of which the deformation behavior of the area 333 and the area of the housing 366 are adjusted, in particular made more uniform. Higher insulation is set (333) where higher temperatures prevail.
  • the thickness and / or the porosity of the thermal insulation layers 8, 9 can be the same.
  • an erosion protection layer 13 can of course be arranged on the thermal insulation layers 8, 9.
  • FIG. 14 shows a component 1, 300, 303 in which different porosities of 20 to 30% are present in different housings 335, 366.
  • the inflow region 333 with the heat insulation layer 8 has a higher porosity than the heat insulation layer 9 of the housing of the blading region, as a result of which a higher thermal insulation is achieved in the inflow region 333 than through the heat insulation layer 9 in the housing 366 of the blading region.
  • the thickness and the material of the thermal insulation layers 8, 9 can also be different.
  • the porosity sets the heat insulation of a heat insulation layer 7 differently, as a result of which the deformation behavior of different areas / housings 333, 366 of a component 1 can be set.
  • thermal insulation layer 7 described above can be used in the pipelines connected downstream from a steam generator (for example a boiler) (for example duct 46, FIG. 15; inflow region 351, FIG. 8) for transporting the superheated steam or other superheated steam-carrying lines and fittings, such as, for example, Bypass lines, bypass valves or process steam lines of a power plant are applied to the inside of each.
  • a steam generator for example a boiler
  • duct 46, FIG. 15 for example duct 46, FIG. 15; inflow region 351, FIG. 8
  • the thermal insulation layer 7 described above can be used in the pipelines connected downstream from a steam generator (for example a boiler) (for example duct 46, FIG. 15; inflow region 351, FIG. 8) for transporting the superheated steam or other superheated steam-carrying lines and fittings, such as, for example, Bypass lines, bypass valves or process steam lines of a power plant are applied to the inside of each.
  • a steam generator for example a boiler
  • thermal barrier coating 7 of steam-carrying components in steam generators on the side, which is exposed to the hotter medium (flue gas or superheated steam).
  • hotter medium flue gas or superheated steam.
  • collectors or sections of a once-through boiler that are not heated should serve from steam or should be protected from the attack of hot media for other reasons.
  • the insulating layer 7 on the outside of a boiler in particular a continuous boiler, in particular a Benson boiler, can achieve an insulating effect which results in a reduction in fuel consumption.
  • An erosion protection layer 13 can also be present on the heat insulation layers 8, 9.
  • the measures according to FIGS. 11, 12 and 13 set the axial play between the rotor and the stator (housing), since the thermal expansion is adjusted despite different temperatures or thermal expansion coefficients (dl 333 «dl 366 ) • The temperature differences also exist in the stationary one Condition of the turbine.
  • FIG. 15 shows a further application example for the use of a heat insulation layer 7, namely a valve housing 34 of a valve 31, into which a hot steam flows through an inflow channel 46.
  • the inflow channel 46 mechanically weakens the valve housing 34.
  • the valve 31 consists, for example, of a pot-shaped housing 34 and a cover or housing 37. Inside the housing part 34 there is a valve piston consisting of a valve cone 40 and a spindle 43. As a result of component creep, there is a non-uniform axial deformation behavior of the housing 40 and the cover 37. As indicated by dashed lines, the valve housing 34 would expand axially more in the region of the channel 46, so that the cover 37 tilts with the spindle 43 comes. As a result, the valve cone 34 is no longer seated correctly, so that the tightness of the valve 31 is reduced. By applying a thermal barrier coating 7 to an inside 49 of the housing 34, the deformation behavior is evened out, so that both ends 52, 55 of the housing 34 and the cover 37 expand uniformly.
  • the application of the thermal barrier coating serves to control the deformation behavior and thus to ensure the tightness of the valve 31.
  • FIG. 16 shows a stator 58, for example a housing 335, 366, 367 of a turbine 300, 303 and a rotating component 61 (rotor), in particular a turbine blade 120, 130, 342, 354.
  • a stator 58 for example a housing 335, 366, 367 of a turbine 300, 303 and a rotating component 61 (rotor), in particular a turbine blade 120, 130, 342, 354.
  • the temperature-time diagram T (t) for the stator 58 and the rotor 61 shows, for example, when the turbine 300, 303 is shut down, that the temperature T of the stator 58 drops faster than the temperature of the rotor 61.
  • the housing 58 shrinks more than the rotor 61 so that the housing 58 approaches the rotor. Therefore, there must be a corresponding distance d between the stator 58 and the rotor 61 in the cold state in order to prevent the rotor 61 from rubbing against the housing 58 in this operating phase.
  • the radial gap is 2.0 to 2.5 mm. In both cases, a reduction in this gap of 0.3 to 0.5 or to 0.8 mm can be achieved by reducing the temperature difference by 50K. As a result, less steam can flow past between the housing 58 and the turbine blade 61, so that the efficiency increases again.
  • a thermal insulation layer 7 is applied to the stator (non-rotating component) 58.
  • the thermal barrier coating 7 causes a greater thermal inertia of the stator 58 or the housing 335, which heats up more or faster.
  • the temperature-time diagram again shows the time course of the temperatures T of the stator 58 and the rotor 61. Due to the thermal barrier coating 7 on the stator 58, the temperature of the stator 58 does not rise so quickly and the difference between the two curves is less.
  • the thermal barrier coating 7 can also be applied to the rotor 61, for example the turbine blades 342, 354, 357, in order to achieve the same effect.
  • the distance-time diagram shows that there is a smaller distance d7 (d7 ⁇ di ⁇ ds) at room temperature RT, which does not lead to the stator 58 and rotor 61 touching.
  • FIG. 18 shows the influence of the application of a thermal barrier coating on a reworked component.
  • Refurbishment means that components that were in use may be repaired, i.e. that they are freed from corrosion and oxidation products, and cracks may be detected and repaired, for example, by filling with solder.
  • Each component 1 has a certain lifespan until it is 100% damaged.
  • the component for example a turbine blade or an inner housing 334
  • a certain percentage of the damage has been achieved.
  • the time course of the damage to component 1 is identified by reference numeral 22.
  • the damage curve would continue without a reprocessing using the dashed line 25.
  • the remaining operating time would be relatively short.
  • This course of the curve is significantly flattened compared to the curve course 25, so that such a coated component 1 can be used at least as long.
  • the lifespan of the component that has been inspected does not always have to be extended, but it can also be the sole intention to control and even out the deformation behavior of housing parts by the first or repeated application of the thermal insulation layer 7, thereby reducing the efficiency as described above by setting the radial gaps between the rotor and gear housing and the axial gap between the rotor and housing is increased.
  • the thermal insulation layer 7 can therefore advantageously also be applied to components 1 or housing parts that are not to be repaired.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Control Of Turbines (AREA)
  • Thermal Insulation (AREA)
  • Laminated Bodies (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

L'invention concerne l'utilisation d'une couche d'isolation thermique (7) pour le boîtier d'une turbine à vapeur afin d'uniformiser le comportement de déformation de divers composants en raison de l'échauffement différent des composants.
EP04801187A 2003-12-11 2004-12-01 Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur Withdrawn EP1692372A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04801187A EP1692372A1 (fr) 2003-12-11 2004-12-01 Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03028575A EP1541810A1 (fr) 2003-12-11 2003-12-11 Utilisation de revêtement de barrière thermique pour un élément d'une turbine à vapeur et une turbine à vapeur
EP04801187A EP1692372A1 (fr) 2003-12-11 2004-12-01 Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur
PCT/EP2004/013651 WO2005056985A1 (fr) 2003-12-11 2004-12-01 Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur

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EP1692372A1 true EP1692372A1 (fr) 2006-08-23

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EP03028575A Withdrawn EP1541810A1 (fr) 2003-12-11 2003-12-11 Utilisation de revêtement de barrière thermique pour un élément d'une turbine à vapeur et une turbine à vapeur
EP04801187A Withdrawn EP1692372A1 (fr) 2003-12-11 2004-12-01 Utilisation d'une couche d'isolation thermique pour le boitier d'une turbine a vapeur et turbine a vapeur

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US (3) US7614849B2 (fr)
EP (2) EP1541810A1 (fr)
JP (1) JP4563399B2 (fr)
KR (1) KR101260922B1 (fr)
CN (1) CN1890457B (fr)
BR (1) BRPI0417561A (fr)
CA (1) CA2548973C (fr)
RU (1) RU2362889C2 (fr)
WO (1) WO2005056985A1 (fr)

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WO2005056985A1 (fr) 2005-06-23
EP1541810A1 (fr) 2005-06-15
US8215903B2 (en) 2012-07-10
US20090280005A1 (en) 2009-11-12
KR20060123474A (ko) 2006-12-01
US8226362B2 (en) 2012-07-24
US7614849B2 (en) 2009-11-10
RU2006124740A (ru) 2008-01-20
CN1890457A (zh) 2007-01-03
BRPI0417561A (pt) 2007-03-27
CA2548973C (fr) 2011-01-25
KR101260922B1 (ko) 2013-05-06
JP2007514094A (ja) 2007-05-31
RU2362889C2 (ru) 2009-07-27
JP4563399B2 (ja) 2010-10-13
US20090232646A1 (en) 2009-09-17
CN1890457B (zh) 2011-06-08
US20070140840A1 (en) 2007-06-21
CA2548973A1 (fr) 2005-06-23

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