EP1318273A2 - Aube de turbine revêtu - Google Patents

Aube de turbine revêtu Download PDF

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Publication number
EP1318273A2
EP1318273A2 EP02012119A EP02012119A EP1318273A2 EP 1318273 A2 EP1318273 A2 EP 1318273A2 EP 02012119 A EP02012119 A EP 02012119A EP 02012119 A EP02012119 A EP 02012119A EP 1318273 A2 EP1318273 A2 EP 1318273A2
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EP
European Patent Office
Prior art keywords
turbine blade
coolant gas
turbine
thermal barrier
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02012119A
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German (de)
English (en)
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EP1318273B1 (fr
EP1318273A3 (fr
Inventor
Shoju Masaki
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IHI Corp
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IHI Corp
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Publication of EP1318273A3 publication Critical patent/EP1318273A3/fr
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    • 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
    • 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
    • C23C28/34—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
    • 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
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling
    • 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 present invention relates to a turbine blade for use in a turbine engine, and the like, further particularly to a structure of a thermal barrier coat applied to an outer peripheral surface of the turbine blade, a manufacturing method of the turbine blade, and a strip judging method of the thermal barrier coat.
  • a turbine blade for use in a turbine engine is requested to fulfill a predetermined aerodynamic capability and mechanical capability in a high-temperature gas atmosphere.
  • the mechanical capability of a material drops, and it is therefore necessary to maintain the temperature of the turbine blade lower than a predetermined temperature.
  • a means In order to set the temperature of the turbine blade to be lower than a predetermined value, a means has heretofore been taken to dispose a coolant gas port in the outer peripheral surface of the turbine blade and emit a coolant gas onto the outer peripheral surface of the turbine blade through an internal air gap. Moreover, the means includes applying a thermal barrier coat onto the outer peripheral surface of the turbine blade, prevent a high-temperature gas from directly contacting the turbine blade, and prevent the temperature of the material of the turbine blade from rising.
  • Fig. 1 is a structure diagram of a conventional turbine blade.
  • Fig. 2 is an A-A sectional view of Fig. 1
  • Figs. 3B and 3C are sectional detailed diagrams of the conventional turbine blade. The structure of the conventional turbine blade will be described hereinafter with reference to these drawings.
  • the turbine blade means a turbine rotor blade or a turbine stator blade.
  • Fig. 1 shows an example of the turbine rotor blade.
  • a turbine rotor blade 1 is constituted of a turbine blade 2, blade base portion 3 and blade mounting portion 4.
  • the turbine blade 2 is a columnar structure which outer peripheral surface has a blade shape, which root portion is fixed to the blade base portion 3, and which tip end is a free end. On the other hand, with the turbine stator blade, the tip end is also fixed to the other base portion of the turbine stator blade.
  • a coolant gas supply port 5 and coolant gas exhaust port 6 are disposed in the blade mounting portion 4, extend through the blade base portion 3 and are connected to an internal air gap of the turbine blade as described later.
  • the turbine blade 2 is constituted of a turbine blade main body 10 and thermal barrier coat 20.
  • the turbine blade main body 10 is a columnar structure 11 which includes internal air gaps 12 and a plurality of coolant gas ports 13 and has a blade-shaped section.
  • the internal air gaps 12 are air gaps disposed inside the columnar structure 11 so that a coolant gas passes, the columnar structure is divided into a plurality of chambers, and the chambers are connected to one another.
  • the internal air gap 12 in a tip edge of the turbine blade is connected to the coolant gas supply port 5, and the internal air gap 12 in a rear edge of the turbine blade is connected to the coolant gas exhaust port 6.
  • the coolant gas ports 13 are densely disposed in a region where the temperature of the outer surface of the turbine blade easily rises.
  • the coolant gas ports 13 are holes disposed in the outer peripheral surface of the columnar structure 11.
  • the coolant gas ports 13 are connected to the internal air gaps 12.
  • Each coolant gas port 13 has a diameter, for example, of 0.4 to 0.5 mm.
  • the thermal barrier coat 20 is an insulating layer with which the outer peripheral surface of the turbine blade main body 10 (columnar structure 11) is coated, and is constituted of a topcoat 21, interface 22 and bond coat 23.
  • the bond coat 23 is a foundation treated layer with which the surface of the turbine blade main body is coated, and examples thereof include oxidation-resistance coatings represented by NiCoCrAlY, PtAl, and the like.
  • the interface 22 is a layer between the topcoat 21 and the bond coat 23, and is, for example, Al 2 O 3 , and the like.
  • the topcoat 21 is a layer forming the outer peripheral surface, and examples thereof include a ceramics coating represented by ZrO 2 -7%Y 2 O 3 , and the like.
  • the thickness of the topcoat 21 is in a range of 100 to 300 ⁇ m
  • the interface 22 has a thickness of 1 ⁇ m
  • the bond coat 23 has a thickness of 100 ⁇ m.
  • the turbine rotor blade 1 is attached to a turbine disc.
  • a turbine engine steadily runs, a high-temperature gas flows around the turbine blade, and the turbine disc receives an aerodynamic force and rotates.
  • the coolant gas is supplied to the coolant gas supply port 5 via the turbine disc.
  • the coolant gas enters the internal air gaps 12 from the coolant gas supply port 5 via the blade mounting portion 4 and blade base portion 3.
  • a part of the coolant gas is blowed out to the outer surface of the turbine blade 2 through the coolant gas ports 13.
  • the remaining coolant gas flows outwards via the coolant gas exhaust port 6 through a plurality of chambers, blade mounting portion 4, and blade base portion 3.
  • the coolant gas is blowed out onto the outer periphery of the turbine blade flows along the surface of the turbine blade, and prevents the ambient high-temperature gas from directly contacting the turbine blade.
  • the outer periphery of the turbine blade is coated with the thermal barrier coat 20, and a heat of high-temperature gas is prevented from being directly conducted to the turbine blade main body.
  • the material can be prevented from having a high temperature, and the mechanical strength can be maintained.
  • the turbine blade having caused the above-described phenomenon has heretofore been changed in a periodic inspection.
  • the temperature of the high-temperature gas has heretofore been set to be relatively low during the run.
  • the turbine blade can be run at 1300°C.
  • the temperature of the high-temperature gas is lowered to 1000°C, and the engine is run. Therefore, there is a problem that the efficiency of the turbine engine cannot be raised further in the present situation.
  • the present invention has been developed in consideration of the above-described problem, and an object thereof is to provide a turbine blade which can be run by raising a temperature of a high-temperature gas than is possible today, a manufacturing method of the turbine blade, and a strip judging method of a thermal barrier coat.
  • a turbine blade (2) which outer peripheral surface has a blade shape, comprising: a turbine blade main body (10) having a blade-shaped section and including an internal air gap (12) disposed inside to allow a coolant gas to pass and a plurality of coolant gas ports (13) disposed in the outer peripheral surface so that the ports can be connected to the internal air gap; and a thermal barrier coat (20) as an insulating layer with which the outer peripheral surface of the turbine blade main body is coated, wherein the thermal barrier coat fills in at least some of the coolant gas ports.
  • the turbine blade main body (10) has a columnar structure with a blade-shaped section including the internal air gap (12) and the plurality of coolant gas ports (13), the outer peripheral surface of the turbine blade main body is coated with the thermal barrier coat (20) as the insulating layer, and the thermal barrier coat fills in some of the coolant gas ports. Therefore, the coolant gas is blowed out from the coolant gas ports via the internal air gap 12 to cool the turbine blade main body during a usual run.
  • the thermal barrier coat is stripped, the coolant gas is also blowed out from the coolant gas ports of the stripped portion, the turbine blade is cooled with more coolant gas than during the usual run, and the temperature of the turbine blade can be prevented from rising.
  • the thermal barrier coat (20) fills in the coolant gas ports the number of which exceeds 20% of the total number of coolant gas ports (13).
  • the thermal barrier coat (20) fills in the coolant gas ports the number of which exceeds 20% of the total number of coolant gas ports (13). Therefore, when a part of the thermal barrier coat is stripped, the number of coolant gas ports of the stripped portion increases, the turbine blade is cooled with the coolant gas having an amount increased by about over 20%, and the temperature of the turbine blade can be prevented from rising.
  • a manufacturing method of a turbine blade which outer peripheral surface has a blade shape comprising: a turbine blade main body preparing step (A) of preparing a turbine blade main body (10) with a blade-shaped section including an internal air gap (12) disposed inside to allow a coolant gas to pass and a plurality of coolant gas ports (13) disposed in the outer peripheral surface so that the coolant gas ports can be connected to the internal air gap; a sealing step (B) for filling a sealer into at least some of the coolant gas ports; and a coating step (C) for disposing an insulating layer on an outer surface of the turbine blade main body after the sealing step.
  • the turbine blade main body preparing step (A) comprises: preparing the turbine blade main body (10) with the blade-shaped section having the internal air gap (12) and the plurality of coolant gas ports (13).
  • the sealing step (B) comprises: filling the sealer into at least some of the coolant gas ports.
  • the coating step (C) after the sealing step comprises: disposing the insulating layer on the outer surface of the turbine blade main body. Therefore, the filled sealer prevents the insulating material from being embedded in the coolant gas ports, and the outer surface of the turbine blade main body is coated with the insulating layer.
  • the outer surface of the columnar structure with the blade-shaped section having the internal air gap and the plurality of coolant gas ports is coated with the thermal barrier coat as the insulating layer, and the thermal barrier coat fills in at least some of the coolant gas ports.
  • This turbine blade can be manufactured.
  • the sealing step (B) comprises: filling the sealer into the coolant gas ports the number of which exceeds 20% of the total number of the coolant gas ports.
  • the sealer in the sealing step (B), the sealer is filled into the coolant gas ports the number of which exceeds 20% of the total number of the coolant gas ports. Therefore, a turbine blade (2) can be manufactured in which the outer surface of the columnar structure with the blade-shaped section including the internal air gap and the plurality of coolant gas ports is coated with the thermal barrier coat as the insulating layer, and the thermal barrier coat (20) fills in the number over 20% of the total number of the coolant gas ports.
  • a manufacturing method of a turbine blade comprising: a sealer removing step (D) for removing the sealer after the coating step (C).
  • the sealer removing step (D) after the coating step (C) the sealer is removed. Therefore, the outer surface of the columnar structure with the blade-shaped section including the internal air gap and the plurality of coolant gas ports is coated with the thermal barrier coat as the insulating layer, and nothing is filled in the coolant gas ports closed by the thermal barrier coat.
  • the thermal barrier coat is stripped, the coolant gas is quickly blowed out even from the coolant gas ports of the stripped portion, the turbine blade is cooled with more coolant gas than during the usual run, and the temperature of the turbine blade can be prevented from rising.
  • the turbine blade constituted as described above can be manufactured.
  • a strip judging method of a thermal barrier coat comprising the steps for: preparing a turbine using the above-described turbine blade (2); detecting consumption of a coolant gas supplied to the turbine blade; and judging the presence of a strip of the thermal barrier coat (20) by a fluctuation of the consumption.
  • the turbine using the turbine blade (2) is prepared, the consumption of the coolant gas supplied to the turbine blade is detected, and the presence/absence of the strip of the thermal barrier coat is judged by the fluctuation of the consumption. Therefore, when the strip of the thermal barrier coat occurs during the run of the turbine, the consumption of the coolant gas increases, the presence of the strip of the thermal barrier coat can be known by detecting the increase and, for example, a means for preventing an abnormal temperature rise of the turbine can quickly be taken.
  • Fig. 4 is a structure diagram of an embodiment of the present invention.
  • Fig. 5 is an A-A sectional view
  • Figs. 6B and 6C are sectional detailed diagrams of a turbine blade according to the present invention. The structure of the turbine blade according to the present invention will be described with reference to the drawings.
  • the turbine blade means a turbine rotor blade or a turbine stator blade.
  • Fig. 4 shows an example of the turbine rotor blade.
  • a turbine rotor blade 1 is constituted of a turbine blade 2, blade base portion 3 and blade mounting portion 4.
  • the turbine blade 2 is a columnar structure which outer peripheral surface has a blade shape, which root portion is fixed to the blade base portion 3, and which tip end is a free end. On the other hand, with the turbine stator blade, the tip end is also fixed to the other base portion of the turbine stator blade.
  • a coolant gas supply port 5 and coolant gas exhaust port 6 are disposed in the blade mounting portion 4, extend through the blade base portion 3 and are connected to an internal air gap described later of the turbine blade.
  • the turbine blade 2 is constituted of a turbine blade main body 10 and thermal barrier coat 20.
  • the turbine blade main body 10 is a columnar structure 11 which includes internal air gaps 12 and a plurality of coolant gas ports 13 and which has a blade-shaped section.
  • the internal air gaps 12 are air gaps disposed inside the columnar structure 11 so that a coolant gas passes, the columnar structure is divided into a plurality of chambers, and the chambers are connected to one another.
  • the internal air gap 12 in a tip edge of the turbine blade is connected to the coolant gas supply port 5, and the internal air gap 12 in a rear edge of the turbine blade is connected to the coolant gas exhaust port 6.
  • the coolant gas ports 13 are holes disposed in an outer surface of the columnar structure 11.
  • the coolant gas ports 13 are connected to the internal air gaps 12.
  • Each coolant gas port 13 has a diameter, for example, of 0.4 to 0.5 mm.
  • coolant gas ports 13 are coated with a topcoat described later. Here, for the convenience of the description, particularly these coolant gas ports 13 will hereinafter be referred to as fireplug ports 14.
  • the coolant gas ports 13 are disposed at equal intervals in a portion which needs to be cooled.
  • the number of fireplug ports 14 is preferably not less than 20% of the total number of the coolant gas ports 13.
  • the fireplug ports 14 are preferably equally disposed in the plurality of coolant gas ports 13.
  • the fireplug ports 14 are loaded with a sealer 15.
  • the material of the sealer can be changed with the temperature in an applying step of the topcoat described later.
  • the sealer include resins such as epoxy resin, PEEK resin, and silicon rubber, simplex compounds such as CaO, AlF 3 , NaAlF 6 , AlPO 4 , and SiO 2 , and mixtures.
  • resins such as epoxy resin, PEEK resin, and silicon rubber
  • simplex compounds such as CaO, AlF 3 , NaAlF 6 , AlPO 4 , and SiO 2
  • mixtures such as CaO, AlF 3 , NaAlF 6 , AlPO 4 , and SiO 2
  • a mixture of AlPO 4 and SiO 2 can be used.
  • the sealer 15 may be removed beforehand, and nothing may be filled in the fireplug ports 14.
  • the thermal barrier coat 20 is an insulating layer with which the outer peripheral surface of the turbine blade main body is coated, and is constituted of a topcoat 21, interface 22 and bond coat 23.
  • the bond coat 23 is a foundation treated layer with which the surface of the turbine blade main body is coated, and examples thereof include oxidation-resistance coatings represented by NiCoCrAlY, PtAl, and the like.
  • the interface 22 is a layer between the topcoat 21 and the bond coat 23, and is, for example, Al 2 O 3 , and the like.
  • the topcoat 21 is a layer which forms the outer peripheral surface, and examples thereof include a ceramics coating represented by ZrO 2 -7%Y 2 O 3 , and the like.
  • the thickness of the topcoat 21 is in a range of 100 to 300 ⁇ m
  • the interface 22 has a thickness of 1 ⁇ m
  • the bond coat 23 has a thickness of 100 ⁇ m.
  • the turbine rotor blade 1 is attached to a turbine disc.
  • a turbine engine steadily runs, a high-temperature gas flows around the turbine blade, and the turbine disc receives an aerodynamic force and rotates.
  • the coolant gas is supplied to the coolant gas supply port 5 via the turbine disc.
  • the coolant gas enters the internal air gaps from the coolant gas supply port 5 via the blade mounting portion 4 and blade base portion 3.
  • a part of the coolant gas is blowed out to the outer surface of the turbine blade 2 through the coolant gas ports 13 excluding the fireplug ports 14.
  • the remaining coolant gas flows outwards via the coolant gas exhaust port 6 through a plurality of chambers, blade mounting portion 4, and blade base portion 3.
  • the coolant gas blowe out onto the outer periphery of the turbine blade flows along the surface of the turbine blade, and prevents the ambient high-temperature gas from directly contacting the turbine blade.
  • the outer periphery of the turbine blade is coated with the thermal barrier coat 20, and a heat of high-temperature gas is prevented from being directly conducted to the turbine blade main body.
  • the fireplug ports 14 in the region are exposed.
  • the sealer 15 is pushed outwards by the pressure of the coolant gas of the internal air gap, and the coolant gas is blowed out from the fireplug ports 14.
  • the coolant gas flows along the outer surface of the turbine blade main body from which the topcoat 21 is stripped.
  • the vicinity of the region from which the topcoat 21 is stripped is covered with the coolant gas blowed out from the ambient coolant gas ports 13 and the coolant gas blowed out from the fireplug ports, and the high-temperature gas is prevented from contacting the surface of the turbine blade main body.
  • the material since the heat of ambient high-temperature gas does not easily enter the turbine blade main body, the material can be prevented from a high temperature, and the mechanical strength of the material can be maintained.
  • the turbine blade main body is prepared including the internal air gap 12 disposed inside so that the coolant gas passes and the plurality of coolant gas ports 13 which are connected to the internal air gap 12 and disposed in the outer peripheral surface.
  • the structure of the turbine blade main body is the same as described above, and therefore the description thereof is omitted.
  • Some of the coolant gas ports 13 constitute the fireplug ports 14.
  • the sealer is filled in at least some of the plurality of coolant gas ports 13.
  • the sealer is filled in the coolant gas ports 13 the number of which exceeds 20% of the total number of coolant gas ports 13.
  • the material of the sealer is selected in accordance with a treatment temperature of a coating step as a post-step. Additionally, a heat-resistance temperature of the material of the sealer needs to be higher than an atmosphere temperature in which the turbine blade 2 is disposed in the coating step as the post-step.
  • the material of the sealer is selected from the resins such as the epoxy resin, PEEK resin, and silicon rubber.
  • the material of the sealer is selected from the simplex compounds such as CaO, AlF 3 , Na 3 AlF 6 , AlPO 4 , and SiO 2 , and mixtures of these compounds.
  • a mixture of AlPO 4 and SiO 2 may be selected.
  • the surface of the turbine blade main body 10 is coated with the bond coat. Subsequently, the surface of the bond coat is coated with the interface. Finally, the surface of the interface is coated with the topcoat.
  • the turbine blade is immersed in water, and the sealer is molten out.
  • the sealer may be left in the turbine blade main body.
  • the turbine using the turbine blade is prepared.
  • the presence/absence of the strip of the thermal barrier coat is judged by the fluctuation of the consumption of the coolant gas.
  • the temperature of the material of the turbine blade does not rise, and a predetermined mechanical capability can be maintained.
  • the temperature of the material of the turbine blade rises. Therefore, the gas temperature of the turbine can be raised, and turbine efficiency is enhanced.
  • the consumption of the coolant gas blowed out from the coolant gas ports is small, until the topcoat is stripped. Therefore, the whole mechanical efficiency of the turbine is enhanced.
  • the strip judging method of the thermal barrier coat according to the present invention when used, the strip of the topcoat can be confirmed even during the run of the turbine, and the turbine can appropriately be run. Moreover, when the topcoat is stripped, the turbine blade can quickly be changed.
  • the turbine blade of the present invention has the following effects.
  • the coolant gas is blowed out from the coolant gas ports via the internal air gap to cool the turbine blade main body.
  • the thermal barrier coat is stripped, the coolant gas is blowed out even from the coolant gas ports of the strip portion, the turbine blade is cooled with more coolant gas than during the usual run, and the temperature of the turbine blade can be prevented from rising.
  • the number of coolant gas ports of the stripped portion increases, the turbine blade is cooled with the coolant gas of the amount increased by over about 20%, and the temperature of the turbine blade can be prevented from rising.
  • the turbine blade can be manufactured in which the filled sealer prevents the insulating material from being buried in the coolant gas ports, the outer surface of the turbine blade main body can be coated with the insulating layer, the outer surface of the columnar structure with the blade-shaped section having the internal air gap and the plurality of coolant gas ports is coated with the thermal barrier coat as the insulating layer, and the thermal barrier coat fills in at least some of the coolant gas ports.
  • the sealer is filled in the coolant gas ports the number of which is 20% or more of the total number of coolant gas ports. Therefore, the turbine blade can be manufactured in which the outer surface of the columnar structure with the blade-shaped section having the internal air gap and the plurality of coolant gas ports is coated with the thermal barrier coat as the insulating layer, and the thermal barrier coat fills in the number of coolant gas ports exceeding 20% of the total number of coolant gas ports.
  • the turbine using the turbine blade is prepared, the consumption of the coolant gas supplied to the turbine blade is detected, the presence/absence of the strip of the thermal barrier coat is judged by the fluctuation of the consumption, the strip of the thermal barrier coat can be known during the run of the turbine and, for example, a means for preventing the abnormal temperature rise of the turbine can quickly be taken.
  • the turbine blade which can be run by raising the temperature of the high-temperature gas, the manufacturing method of the turbine blade, and the method of judging the strip of the thermal barrier coat.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP02012119A 2001-12-07 2002-05-31 Aube de turbine, procédé de fabrication d'une aube de turbine, et procédé d'évaluation du détachement d'une couche de protection thermique Revoked EP1318273B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2001374542 2001-12-07
JP2001374542A JP2003172102A (ja) 2001-12-07 2001-12-07 タービン翼とその製造方法とそのサーマルバリアコート剥離判断方法

Publications (3)

Publication Number Publication Date
EP1318273A2 true EP1318273A2 (fr) 2003-06-11
EP1318273A3 EP1318273A3 (fr) 2004-12-29
EP1318273B1 EP1318273B1 (fr) 2006-11-29

Family

ID=19183089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02012119A Revoked EP1318273B1 (fr) 2001-12-07 2002-05-31 Aube de turbine, procédé de fabrication d'une aube de turbine, et procédé d'évaluation du détachement d'une couche de protection thermique

Country Status (5)

Country Link
US (1) US20030108424A1 (fr)
EP (1) EP1318273B1 (fr)
JP (1) JP2003172102A (fr)
CA (1) CA2385932C (fr)
DE (1) DE60216405T2 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1321629A2 (fr) * 2001-12-20 2003-06-25 General Electric Company Couche de barrière thermique ventilée
EP1655454A1 (fr) * 2004-11-09 2006-05-10 General Electric Company Paroi revêtue avec système de refroidissement
EP1669545A1 (fr) * 2004-12-08 2006-06-14 Siemens Aktiengesellschaft Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
EP3054105A1 (fr) * 2015-02-03 2016-08-10 General Electric Company Composant, composant de turbine à gaz et procédé de fabrication associé
EP2935836B1 (fr) * 2012-12-19 2022-01-19 Raytheon Technologies Corporation Fermeture de trous de refroidissement avec un agent de remplissage

Families Citing this family (8)

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US6749396B2 (en) * 2002-06-17 2004-06-15 General Electric Company Failsafe film cooled wall
US7095221B2 (en) * 2004-05-27 2006-08-22 Siemens Aktiengesellschaft Doppler radar sensing system for monitoring turbine generator components
US20090074576A1 (en) * 2006-04-20 2009-03-19 Florida Turbine Technologies, Inc. Turbine blade with cooling breakout passages
PL2322683T3 (pl) * 2009-11-16 2020-12-14 Siemens Aktiengesellschaft Sposób powlekania komponentu z częściowo zamkniętymi otworami i sposób otwierania otworów
EP2418357A1 (fr) * 2010-08-05 2012-02-15 Siemens Aktiengesellschaft Aube de turbine et procédé pour revêtement de la barrière thermique
KR101828543B1 (ko) * 2013-07-23 2018-02-12 한화테크윈 주식회사 터빈 블레이드 및 터빈 블레이드의 제조 방법
US10508553B2 (en) * 2016-12-02 2019-12-17 General Electric Company Components having separable outer wall plugs for modulated film cooling
CN110129859B (zh) * 2018-02-08 2021-09-21 通用电气公司 掩蔽元件中的孔并对元件进行处理的方法

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EP0510740A1 (fr) * 1991-04-26 1992-10-28 General Motors Corporation Méthode de revêtement de la surface d'un laminé poreux
EP0843026A1 (fr) * 1996-10-16 1998-05-20 Chromalloy Gas Turbine Corporation Placage des composants de turbine à gaz
US6039537A (en) * 1996-09-04 2000-03-21 Siemens Aktiengesellschaft Turbine blade which can be subjected to a hot gas flow

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US2641439A (en) * 1947-10-01 1953-06-09 Chrysler Corp Cooled turbine or compressor blade

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
EP0510740A1 (fr) * 1991-04-26 1992-10-28 General Motors Corporation Méthode de revêtement de la surface d'un laminé poreux
US6039537A (en) * 1996-09-04 2000-03-21 Siemens Aktiengesellschaft Turbine blade which can be subjected to a hot gas flow
EP0843026A1 (fr) * 1996-10-16 1998-05-20 Chromalloy Gas Turbine Corporation Placage des composants de turbine à gaz

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1321629A2 (fr) * 2001-12-20 2003-06-25 General Electric Company Couche de barrière thermique ventilée
EP1321629A3 (fr) * 2001-12-20 2004-07-14 General Electric Company Couche de barrière thermique ventilée
EP1655454A1 (fr) * 2004-11-09 2006-05-10 General Electric Company Paroi revêtue avec système de refroidissement
US7186091B2 (en) 2004-11-09 2007-03-06 General Electric Company Methods and apparatus for cooling gas turbine engine components
EP1669545A1 (fr) * 2004-12-08 2006-06-14 Siemens Aktiengesellschaft Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
US7909581B2 (en) 2004-12-08 2011-03-22 Siemens Aktiengesellschaft Layer system, use and process for producing a layer system
EP2935836B1 (fr) * 2012-12-19 2022-01-19 Raytheon Technologies Corporation Fermeture de trous de refroidissement avec un agent de remplissage
EP3054105A1 (fr) * 2015-02-03 2016-08-10 General Electric Company Composant, composant de turbine à gaz et procédé de fabrication associé
US9718735B2 (en) 2015-02-03 2017-08-01 General Electric Company CMC turbine components and methods of forming CMC turbine components

Also Published As

Publication number Publication date
CA2385932A1 (fr) 2003-06-07
DE60216405T2 (de) 2007-03-29
JP2003172102A (ja) 2003-06-20
CA2385932C (fr) 2007-07-17
EP1318273B1 (fr) 2006-11-29
EP1318273A3 (fr) 2004-12-29
DE60216405D1 (de) 2007-01-11
US20030108424A1 (en) 2003-06-12

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