WO2016121163A1 - タービン翼及びタービン並びにタービン翼の製造方法 - Google Patents
タービン翼及びタービン並びにタービン翼の製造方法 Download PDFInfo
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- WO2016121163A1 WO2016121163A1 PCT/JP2015/077152 JP2015077152W WO2016121163A1 WO 2016121163 A1 WO2016121163 A1 WO 2016121163A1 JP 2015077152 W JP2015077152 W JP 2015077152W WO 2016121163 A1 WO2016121163 A1 WO 2016121163A1
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- shroud
- airfoil
- gap
- turbine blade
- turbine
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
- B23K9/167—Arc welding or cutting making use of shielding gas and of a non-consumable electrode
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- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K10/00—Welding or cutting by means of a plasma
- B23K10/02—Plasma welding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K15/00—Electron-beam welding or cutting
- B23K15/0046—Welding
- B23K15/0053—Seam welding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K15/00—Electron-beam welding or cutting
- B23K15/0046—Welding
- B23K15/0093—Welding characterised by the properties of the materials to be welded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
- B23K26/24—Seam welding
- B23K26/28—Seam welding of curved planar seams
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/32—Bonding taking account of the properties of the material involved
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/23—Arc welding or cutting taking account of the properties of the materials to be welded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- 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
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
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- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- 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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
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- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/001—Turbines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/18—Dissimilar materials
- B23K2103/26—Alloys of Nickel and Cobalt and Chromium
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- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
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- 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
- F05D2220/32—Application in turbines in gas turbines
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- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
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- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
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- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/233—Electron beam welding
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- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/234—Laser welding
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- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/235—TIG or MIG welding
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- 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
- F05D2230/60—Assembly methods
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- 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
- F05D2260/20—Heat transfer, e.g. cooling
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- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Definitions
- the present disclosure relates to a turbine blade, a turbine, and a method for manufacturing the turbine blade.
- Patent Document 1 discloses a turbine stationary blade obtained by welding a cast blade portion and a shroud portion by welding.
- the blade and shroud are partially welded in the thickness direction of the shroud from the cooling surface side of the shroud in order to relieve thermal deformation restraint of the shroud.
- a gap unwelded portion is left in the vicinity of the high-temperature fluid surface of the shroud.
- At least one embodiment of the present invention aims to provide a turbine blade capable of suppressing a temperature rise of a welded portion.
- a turbine blade includes: A turbine blade provided along a radial direction of the turbine, An airfoil located in a fluid flow path of the turbine; A shroud portion located inside or outside the airfoil portion in the radial direction and having an opening into which an end portion of the airfoil portion is fitted, A gap is formed between a wall surface forming the opening of the shroud portion and an outer peripheral surface of the end portion of the airfoil portion, The wall surface of the shroud portion and the outer peripheral surface of the airfoil portion are joined to each other via a welded portion on the opposite side of the fluid flow channel across the gap, At least one of the shroud portion or the airfoil portion is provided with a cooling hole configured to open to the gap and supply a cooling fluid to the gap.
- the stress on the welded portion during the turbine operation Concentration can be suppressed.
- the cooling fluid is supplied from the cooling hole provided in at least one of the shroud part or the airfoil part to the gap formed between the shroud part and the airfoil part, the high-temperature fluid flowing through the fluid flow path is Intrusion into the gap can be prevented. Thereby, the temperature rise of the welding part located on the opposite side to the fluid flow path across the gap can be suppressed, and the life of the turbine blade can be improved.
- the shroud portion includes an inner shroud and an outer shroud respectively provided on the inner side and the outer side of the airfoil portion in the radial direction and having the opening,
- the gap is formed between the wall surface of each of the inner shroud and the outer shroud and the outer peripheral surface of each end of the airfoil portion,
- the wall surface of each of the inner shroud and the outer shroud and the outer peripheral surface of each end portion of the airfoil portion are on the opposite side of the fluid flow path across the gap, and via the welded portion. Are joined together.
- the cooling fluid is supplied from the cooling holes to the gaps formed between the inner shroud and the airfoil and between the outer shroud and the airfoil, and thus more effective. Therefore, it is possible to prevent the hot fluid from entering the gap. Thereby, the temperature rise of each welding part located on the opposite side to the fluid flow path side across each gap can be suppressed, and the life of the turbine blade can be further improved.
- the airfoil portion has a hollow portion configured to allow the cooling fluid to flow;
- the cooling hole includes a first cooling hole configured to communicate the hollow portion of the airfoil portion with the gap.
- the cooling fluid flowing through the hollow portion can be supplied to the gap through the first cooling hole configured to communicate the hollow portion of the airfoil portion with the gap. Hot fluid can be prevented from entering the gap.
- a shielding plate that is provided in the shroud portion and that forms a cooling passage configured to allow the cooling fluid to flow together with an inner wall surface of the shroud portion;
- the cooling hole includes a second cooling hole configured to communicate the cooling passage in the shroud portion with the gap.
- the cooling fluid flowing through the cooling passage through the second cooling hole configured to communicate the cooling passage formed by the inner wall surface of the shroud portion and the shielding plate and the gap. Can be supplied to the gap, and hot fluid can be prevented from entering the gap.
- the weld in any one of the above configurations (1) to (4), includes a first weld along the extending direction of the gap. (6) In some embodiments, in any one of the above configurations (1) to (5), the weld includes a second weld along the width direction of the gap. According to the configuration of (5) or (6) above, the airfoil portion and the shroud portion can be firmly joined by the first welded portion and / or the second welded portion.
- the shroud portion has an injection hole provided around the gap so as to open to the fluid flow path and configured to eject the cooling fluid,
- the said injection hole inclines with respect to the said radial direction so that it may approach the said airfoil part as it goes to the said fluid flow path side.
- the cooling fluid is ejected from the ejection holes provided in the shroud portion toward the airfoil portion around the gap, so that the high temperature fluid in the fluid flow path can enter the gap. Can be suppressed.
- an edge of the opening facing the fluid flow path in the shroud portion is an extension of the airfoil portion.
- the cross-sectional shape along the current direction is a curved shape.
- a turbine according to at least one embodiment of the present invention includes a rotor including a turbine blade having any one of the configurations (1) to (8).
- the stress on the welded portion during the turbine operation Concentration can be suppressed.
- the cooling fluid is supplied from the cooling hole provided in at least one of the shroud part or the airfoil part to the gap formed between the shroud part and the airfoil part, the high-temperature fluid flowing through the fluid flow path is Intrusion into the gap can be prevented. Thereby, the temperature rise of the welding part located on the opposite side to the fluid flow path across the gap can be suppressed, and the life of the turbine blade can be improved.
- a method for manufacturing a turbine blade according to at least one embodiment of the present invention includes: A turbine blade manufacturing method comprising: an airfoil portion provided in a fluid flow path of a turbine; and a shroud portion having an opening into which an end portion of the airfoil portion is fitted.
- a cooling hole formed in at least one of the shroud part or the airfoil part is formed in a gap formed between a wall surface forming the opening of the shroud part and an outer peripheral surface of the end part of the airfoil part.
- the turbine blade obtained by the method of (10) above slight deformation of the airfoil portion and the shroud portion is allowed by the gap formed between the shroud portion and the airfoil portion. Stress concentration on the weld can be suppressed. Further, since the cooling fluid is supplied to the gap formed between the shroud portion and the airfoil portion from the cooling hole provided in at least one of the shroud portion or the airfoil portion, the high-temperature fluid flowing through the combustion gas passage Can be prevented from entering the gap. Thereby, the temperature rise of the welding part located on the opposite side to the fluid flow path across the gap can be suppressed, and the life of the turbine blade can be improved.
- the method further includes a casting step of casting the airfoil portion and the shroud portion.
- the structure of the cast product is relatively simple compared to the case where the airfoil portion and the shroud portion are integrally cast. Become. For this reason, the defect at the time of casting can be reduced and a yield can be improved.
- the shroud portion includes an inner shroud and an outer shroud respectively provided on one end side and the other end side of the airfoil portion and having the opening
- the cooling hole is formed in the gap formed between the wall surface forming the opening of each of the inner shroud and the outer shroud and the outer peripheral surface of each end of the airfoil portion.
- Each airfoil portion is inserted into the opening of each of the inner shroud and the outer shroud,
- the wall surface of the inner shroud and the outer shroud and the outer peripheral surface of each end portion of the airfoil portion are welded on the opposite side of the fluid flow path across the cooling hole.
- the cooling fluid is supplied from the cooling holes to the gaps formed between the inner shroud and the airfoil portion and between the outer shroud and the airfoil portion. Since it is supplied, it is possible to prevent the hot fluid from entering the gap more effectively. Thereby, the temperature rise of each welding part located on the opposite side to the fluid flow path side across each gap can be suppressed, and the life of the turbine blade can be further improved.
- a turbine blade capable of suppressing a temperature rise in a weld is provided.
- FIG. 4 is a cross-sectional view taken along the line CC shown in FIG. 3. It is a figure which shows the turbine blade which concerns on one Embodiment, Comprising: It is an expanded sectional view of the part applicable to the A section shown in FIG. It is a figure which shows the turbine blade which concerns on one Embodiment, Comprising: It is an expanded sectional view of the part applicable to the A section shown in FIG.
- FIG. 1 is a schematic structure figure showing a gas turbine provided with a turbine concerning one embodiment.
- a gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and a combustion gas. And a turbine 6 configured to be rotationally driven by.
- a generator (not shown) is connected to the turbine 6, and power generation is performed by the rotational energy of the turbine 6.
- the compressor 2 is provided on the compressor casing 10, the inlet side of the compressor casing 10, and penetrates the compressor casing 10 and a turbine casing 22, which will be described later, through the air intake 12 for taking in air.
- the rotor 8 provided and various blades disposed in the compressor casing 10 are provided.
- the various blades are an inlet guide blade 14 provided on the air intake 12 side, a plurality of stationary blades 16 fixed on the compressor casing 10 side, and a rotor so as to be alternately arranged with respect to the stationary blades 16. 8 and a plurality of blades 18 implanted in 8.
- the compressor 2 may include other components such as a bleed chamber (not shown).
- the air taken in from the air intake 12 passes through the plurality of stationary blades 16 and the plurality of moving blades 18 and is compressed into high-temperature and high-pressure compressed air.
- the high-temperature and high-pressure compressed air is sent from the compressor 2 to the subsequent combustor 4.
- the combustor 4 is disposed in the casing 20. As shown in FIG. 1, a plurality of combustors 4 may be arranged in a ring shape around the rotor 8 in the casing 20.
- the combustor 4 is supplied with fuel and compressed air generated by the compressor 2, and burns the fuel to generate combustion gas that is a working fluid of the turbine 6. Then, the combustion gas is sent from the combustor 4 to the subsequent turbine 6.
- the turbine 6 includes a turbine casing 22 and various blades disposed in the turbine casing 22.
- the various blades include a plurality of stationary blades 24 fixed to the turbine casing 22 side, and a plurality of moving blades 26 implanted in the rotor 8 so as to be alternately arranged with respect to the stationary blades 24. .
- the plurality of stationary blades 24 or the plurality of moving blades 26 include a turbine blade 100 described in detail below.
- the stationary blades 5 of each stage are arranged at equal intervals in the circumferential direction of the rotor 8, and are fixed to the turbine casing 22 side, and a plurality of turbine static blades radially extending toward the rotor 8 side.
- a wing body airfoil portion 30
- the rotor blades 26 at each stage are arranged at equal intervals in the circumferential direction of the rotor 8, are fixed to the rotor 8 side, and extend radially toward the turbine casing 22 side.
- a wing body (airfoil portion 30) is provided.
- the turbine 6 is provided with a bypass passage (not shown) through which air inside the compressor 2 is supplied from the compressor 2 by bypassing the combustor 4. The air supplied to the turbine 6 through this bypass flow path is circulated inside the turbine stationary blade body and the turbine rotor blade body as a cooling fluid G2 (see FIG. 3).
- the turbine 6 may include other components such as outlet guide vanes.
- the combustion gas G ⁇ b> 1 passes through the plurality of stationary blades 24 and the plurality of moving blades 26, so that the rotor 8 is rotationally driven. Thereby, the generator connected with the rotor 8 is driven.
- An exhaust chamber 29 is connected to the downstream side of the turbine casing 22 via an exhaust casing 28. The combustion gas after driving the turbine 6 is discharged to the outside through the exhaust casing 28 and the exhaust chamber 29.
- FIG. 2 is a perspective view showing a stationary blade including a turbine blade according to an embodiment.
- FIG. 3 is a perspective view of a turbine blade according to an embodiment. 4 is a cross-sectional view taken along the line CC of FIG. It is sectional drawing.
- the turbine blade 100 may be applied to the rotor blade 26.
- the turbine blade 100 is provided along the radial direction of the turbine 6, and is located in the fluid flow path 72 in which the combustion gas G ⁇ b> 1 from the combustor 4 flows in the turbine 6.
- the airfoil part 30 and the shroud part 40 located on the outer side or the inner side in the radial direction of the turbine 6 with respect to the airfoil part 30 are provided.
- the shroud portion 40 includes an outer shroud 40 ⁇ / b> A provided outside the airfoil portion 30 in the radial direction of the turbine 6 and an inner shroud 40 ⁇ / b> B provided inside the airfoil portion 30.
- the unit structure U of the turbine blade 100 including one airfoil portion 30 and a pair of outer shrouds (40A, 40B) provided for the airfoil portion 30 is A plurality of circumferentially connected blades 24 may be configured.
- Each shroud part 40 (40A, 40B) of each unit structure U has a connecting part 40a, and the connecting part 40a may be connectable via a connecting part 40a of an adjacent unit structure U. .
- the fluid flow path 72 through which the combustion gas G1 flows is formed in a range where the airfoil portions 30 are arranged with the outer shroud 40A and the inner shroud 40B as partition walls.
- the shroud portion 40 (40A, 40B) has an opening 42 (42A, 42B), and the opening 42 (42A, 42B) has an end portion 32 ( 32A, 32B) are fitted.
- the airfoil portion 30 and the shroud portion 40 (40A, 40B) are joined to each other via the welded portion 51A.
- the airfoil portion 30 includes a hollow portion 74 provided so as to penetrate along the radial direction of the turbine 6.
- a cooling fluid G2 from the compressor 2 flows through the hollow portion 74, and the high temperature fluid (combustion gas G1) flowing through the fluid flow path 72 by cooling the airfoil portion 30 with the cooling fluid G2.
- the airfoil 30 is protected from damage caused by heat.
- the airfoil portion 30 is provided with a plurality of holes (not shown) communicating the hollow portion 74 and the fluid flow path 72, and the cooling fluid G2 from the hollow portion 74 passes through the holes, thereby allowing the airfoil portion 30 to pass more. You may come to cool effectively.
- the turbine blade 100 may include only one of the outer shroud 40A and the inner shroud 40B having the above-described configuration.
- FIGS. 5 to 11 are views showing a turbine blade according to an embodiment
- FIGS. 5 to 10 are enlarged sectional views of a portion corresponding to the portion A or the portion shown in FIG.
- It is an expanded sectional view of the part applicable to A part and B part shown in FIG. 4 shows the vicinity of the welded portion 51A where the airfoil portion 30 and the outer shroud 40A are joined, but the portion near the welded portion 51B where the airfoil portion 30 and the inner shroud 40B are joined.
- a certain B section may have a configuration similar to the configuration of the A section shown in FIGS.
- “outer shroud 40A” is described as “shroud portion 40”, and “A” indicating an element on the outer shroud side is omitted in the reference numeral.
- a gap 50 is formed between the wall surface 43 that forms the opening 42 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30.
- the wall surface 43 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30 are joined via a welded portion 51 on the side opposite to the fluid flow path 72 with the gap 50 interposed therebetween. Since the gap 50 formed between the shroud portion 40 and the airfoil portion 30 allows slight deformation of the airfoil portion 30 and the shroud portion 40, stress concentration on the welded portion 51 during the operation of the turbine 6. Can be suppressed.
- the welded portion 51 extends along the extending direction of the gap 50 (the extending direction of the airfoil portion 30 in FIGS. 5 to 8).
- a first weld 52 is included.
- the welded portion 51 includes second welded portions 54 (54 a to 54 c) along the width direction of the gap 50.
- the turbine blade 100 can firmly join the airfoil portion 30 and the shroud portion 40 by the first welded portion 52 or the second welded portion 54 (54a to 54c).
- the blade The mold part 30 and the shroud part 40 can be joined more firmly.
- At least one of the shroud portion 40 and the airfoil portion 30 is provided with cooling holes (34, 44) configured to open to the gap 50 and supply the cooling fluid G 2 to the gap 50. Since the cooling fluid G2 is supplied from the cooling holes (34, 44) to the gap 50 formed between the shroud portion 40 and the airfoil portion 30, the high-temperature fluid (combustion gas G1) flowing through the fluid flow path 72 is supplied. ) Can be prevented from entering the gap 50. Thereby, the temperature rise of the welding part 51 (52, 54) located on the opposite side to the fluid flow path 72 across the gap 50 can be suppressed, and the life of the turbine blade 100 can be improved.
- the cooling hole includes a first cooling hole 34 provided in the airfoil portion 30.
- the first cooling hole 34 is provided so as to communicate the hollow portion 74 of the airfoil portion 30 with the gap 50. Since the cooling fluid G2 flowing through the hollow portion 74 can be supplied to the gap 50 through the first cooling hole 34 configured in this way, the high-temperature fluid (combustion gas G1) flowing through the fluid flow path 72 can be supplied to the gap 50. Can be prevented from entering.
- a plurality of such first cooling holes 34 may be provided circumferentially in the airfoil portion 30 or may be provided in the radial direction of the turbine 6. By providing a plurality of first cooling holes 34, it is possible to more effectively prevent the high temperature fluid (combustion gas G ⁇ b> 1) flowing through the fluid flow path 72 from entering the gap 50.
- the cooling hole includes a second cooling hole 44 provided in the shroud portion 40.
- the turbine blade 100 includes a shielding plate 48 provided in the shroud portion 40, so that the cooling fluid G ⁇ b> 2 from the compressor 2 flows between the inner wall surface 45 of the shroud portion 40 and the shielding plate 48.
- a cooling passage 49 configured as described above is formed.
- the second cooling hole 44 is arranged to allow the cooling passage 49 in the shroud portion 40 and the gap 50 to communicate with each other.
- the cooling fluid flowing through the cooling passage 49 can be supplied to the gap 50 through the second cooling hole 44 configured as described above, and the high-temperature fluid (combustion gas G1) flowing through the fluid flow path 72 enters the gap 50. Can be prevented.
- a plurality of such second cooling holes 44 may be provided circumferentially in the shroud portion 40 or may be provided in the radial direction of the turbine 6. By providing a plurality of second cooling holes 44, it is possible to more effectively prevent the high temperature fluid (combustion gas G ⁇ b> 1) flowing through the fluid flow path 72 from entering the gap 50.
- each of the turbine blades 100 is provided with the first cooling hole 34.
- the first cooling hole 34 is not provided, and the second cooling hole 34 is provided. Only the hole 44 may be provided. As shown in FIG. 6, both the first cooling hole 34 and the second cooling hole 44 may be provided in the turbine blade 100.
- the shroud portion 40 may be provided with an injection hole 46 different from the cooling hole (second cooling hole 44).
- the shroud portion 40 is provided with an injection hole 46 so as to open to the fluid flow path 72 around the gap 50.
- the turbine blade 100 includes a shielding plate 48 provided in the shroud portion 40, as in the embodiment shown in FIG. 6, and between the inner wall surface 45 of the shroud portion 40 and the shielding plate 48.
- a cooling passage 49 configured to allow the cooling fluid G2 from the compressor 2 to flow therethrough is formed.
- the injection hole 46 is formed so as to be inclined with respect to the radial direction of the turbine 6 so as to approach the airfoil portion 30 from the cooling passage 49 toward the fluid passage 72, and the cooling passage in the shroud portion 40. 49 is configured to eject cooling fluid flowing through 49.
- the cooling fluid is injected from the injection hole 46 provided in the shroud portion 40 toward the airfoil portion 30, so that the high temperature fluid in the fluid flow path 72 is further prevented from entering the gap 50. be able to.
- the edge 41 of the opening 42 facing the fluid flow path 72 in the shroud portion 40 has a curved cross-sectional shape along the extending direction of the airfoil portion 30. It may be. Since the edge 41 of the shroud portion 40 is curved as described above, when the end portion 32 of the airfoil portion 30 is fitted into the opening 42 of the shroud portion 40 when the turbine blade 100 is assembled, the opening of the shroud portion 40 is opened. Even if the edge 41 of the 42 and the airfoil portion 30 come into contact with each other, the surface of the airfoil portion 30 is hardly damaged. Thereby, the lifetime of the turbine blade 100 can be further improved.
- the method for manufacturing the turbine blade 100 includes an insertion step and a welding step described below.
- the end portion 32 of the airfoil portion 30 is fitted into the opening 42 of the shroud portion 40.
- a gap 50 is formed between the wall surface 43 forming the opening 42 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30, and the shroud portion 40 or the airfoil portion 30.
- the cooling holes (the first cooling holes 34 or the second cooling holes 44) formed in at least one of them are opened in the gap 50 (insertion step).
- the wall surface 43 of the shroud portion 40 and the outer peripheral surface 33 of the airfoil portion 30 are welded on the opposite side of the fluid flow path 72 across the cooling hole (the first cooling hole 34 or the second cooling hole 44). (Welding step). In the welding step, the cooling hole (the first cooling hole 34 or the second cooling hole 44) and the cooling hole (the first cooling hole 34) so that the gap 50 remains on the fluid flow path 72 side from the opening position. Alternatively, the weld 51 is formed in the gap 50 only on the side opposite to the fluid flow path 72 when viewed from the second cooling hole 44).
- the first weld 52 along the extending direction of the gap 50 shown in FIGS. 5 to 8 and 10 includes the wall surface 43 of the opening 42 formed by the flange 47 of the shroud 40 and the end 32 of the airfoil 30.
- the outer peripheral surface 33 is formed into an I-shaped groove shape in which both are abutted to each other, and welding is performed from the side opposite to the fluid flow path 72. Then, by performing incomplete penetration welding instead of through welding at the time of welding, a slit (gap) is formed between the wall surface 43 of the opening 42 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30. 50) is formed.
- the welding method for example, various welding methods such as laser welding, electron beam welding, plasma welding, and TIG welding can be used.
- the depth of the slit to be formed (the length in the extending direction of the gap 50) is determined by the penetration depth at the time of welding, but the penetration depth at the time of welding can be controlled by welding conditions.
- the flow rate of the cooling gas can be adjusted by adjusting the width of the slit (gap 50) formed during welding. That is, the cooling fluid G2 is caused to flow through the cooling hole (the first cooling hole 34 or the second cooling hole 44) at such a pressure that the combustion gas G1 does not enter the gap 50, thereby preventing the combustion gas G1 from entering the gap 50. Can do. In this manner, the efficiency of the turbine 6 can be appropriately maintained by appropriately adjusting the flow rate of the cooling fluid G2 flowing through the cooling hole (the first cooling hole 34 or the second cooling hole 44).
- the second welded portion 54 (54a to 54c) along the width direction of the gap 50 shown in FIGS. 9 to 11 includes the wall surface 43 of the opening 42 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30.
- Welding can be performed from the wall surface 76 side opposite to the wall surface 43 forming the gap 50 among the wall surfaces of the shroud portion 40 or from the inner peripheral side of the airfoil portion 30.
- the penetration depth can be increased by increasing the number of layers of welding, so that it is relatively easy to obtain a desired penetration depth.
- a slit (gap 50) is formed relatively easily between the wall surface 43 of the opening 42 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30.
- the second welded portion 54 is formed by three layers indicated by 54a to 54c.
- various welding methods such as laser welding and electron beam welding can be used.
- either the airfoil portion 30 or the shroud portion 40 has a flange, and the other abuts against the flange. Has a tangent surface.
- the airfoil portion 30 has the flange 101, and the outer shroud 40 ⁇ / b> A is in contact with the flange 101 84.
- the inner shroud 40 ⁇ / b> B has a flange 102
- the airfoil portion 30 has a contact surface 86 that contacts the flange 102.
- first, welding is performed so as to join the mating surfaces of one flange (101, 102) and the other contact surface (84, 86) of the airfoil portion 30 or the shroud portion 40.
- a welded portion 54a, 54d
- second welded portion 54b, 54c, 54e, 54f
- the second welded portion 54 can be easily formed, and a slit (gap 50) having a desired length can be obtained.
- the second welded portion 54 is formed by performing through-weld from the side by abutting the wall surface 43 of the opening 42 of the shroud portion 40 and the outer peripheral surface 33 of the end portion 32 of the airfoil portion 30. In some cases, part of the shroud portion 40 or the airfoil portion 30 may remain after welding depending on welding conditions. In FIG. 9, the remaining portions of the airfoil portion 30 and the shroud portion are shown as remaining portions (30 ', 40'). If such remaining portions (30 ′, 40 ′) remain, slits (gap) are formed on both sides across the portion joined by the weld 51, and the strength of the weld 51 decreases. End up. Therefore, when the remaining portions (30 ', 40') are formed by welding, the remaining portions (30 ', 40') may be removed by cutting or the like to prevent a decrease in strength.
- the manufacturing method of the turbine blade 100 further includes a casting step of casting the airfoil portion 30 and the shroud portion 40 (the outer shroud 40A and / or the inner shroud 40B), respectively.
- the turbine blade 100 is manufactured by implementing said insertion step and welding step using the airfoil part 30 and the shroud part 40 which were cast at the casting step.
- various casting methods can be employed without limitation, but a precision casting method suitable for producing a precise casting product may be employed.
- a precision casting method suitable for producing a precise casting product may be employed.
- the airfoil part 30 and the shroud part 40 having a complicated structure can be manufactured.
- relative or absolute arrangements such as “in a certain direction”, “along a certain direction”, “parallel”, “orthogonal”, “center”, “concentric”, or “coaxial” are used.
- the expression to be expressed not only strictly represents such an arrangement, but also represents a state of relative displacement with tolerance or an angle or a distance that can obtain the same function.
- an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
- expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained.
- a shape including a part or the like is also expressed.
- the expression “comprising”, “including”, or “having” one constituent element is not an exclusive expression that excludes the presence of the other constituent elements.
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Abstract
Description
例えば、特許文献1には、鋳造された翼部及びシュラウド部を溶接で接合して得られるタービン静翼が開示されている。このタービン静翼では、シュラウドの熱変形の拘束を和らげるため、翼部とシュラウド部とがシュラウドの冷却面側からシュラウドの厚さ方向に部分的に溶接されており、翼部とシュラウドとの間においてシュラウドの高温流体面近傍に隙間(未溶着部)が残される構造となっている。
そこで、タービン翼における溶接部の温度上昇を抑制することが望まれる。
タービンの径方向に沿って設けられるタービン翼であって、
前記タービンの流体流路内に位置する翼型部と、
前記径方向における前記翼型部の内側又は外側に位置し、且つ、前記翼型部の端部が嵌合される開口を有するシュラウド部と、を備え、
前記シュラウド部の前記開口を形成する壁面と前記翼型部の前記端部の外周面との間には、間隙が形成されており、
前記シュラウド部の前記壁面と前記翼型部の前記外周面とは、前記間隙を挟んで前記流体流路とは反対側において、溶接部を介して互いに接合されており、
前記シュラウド部又は前記翼型部の少なくとも一方には、前記間隙に開口し且つ前記間隙に冷却流体を供給するように構成された冷却孔が設けられる。
前記シュラウド部は、前記径方向において前記翼型部の内側および外側にそれぞれ設けられ、且つ、前記開口をそれぞれ有する内側シュラウド及び外側シュラウドを含み、
前記内側シュラウド及び前記外側シュラウドの各々の前記壁面と前記翼型部の各々の端部の前記外周面との間には、前記間隙が形成されており、
前記内側シュラウド及び前記外側シュラウドの各々の前記壁面と前記翼型部の各々の端部の前記外周面とは、前記間隙を挟んで前記流体流路とは反対側において、前記溶接部を介して互いに接合されている。
上記(2)の構成では、内側シュラウドと翼型部との間、及び、外側シュラウドと翼型部との間のそれぞれに形成された間隙に冷却孔から冷却流体が供給されるので、より効果的に高温の流体が間隙に侵入するのを防止することができる。これにより、各々の間隙を挟んで流体流路側とは反対側に位置する各々の溶接部の温度上昇を抑制することができ、タービン翼の寿命をより向上させることができる。
前記翼型部は、前記冷却流体が流れるように構成された中空部を有し、
前記冷却孔は、前記翼型部の前記中空部と前記間隙とを連通させるように構成された第1冷却孔を含む。
上記(3)の構成によれば、翼型部の中空部と間隙とを連通させるように構成された第1冷却孔を介して、中空部を流れる冷却流体を間隙に供給することができ、高温の流体が間隙に侵入するのを防止することができる。
前記シュラウド部内に設けられ、前記冷却流体が流れるように構成された冷却通路を前記シュラウド部の内壁面とともに形成する遮蔽板をさらに備え、
前記冷却孔は、前記シュラウド部内の前記冷却通路と前記間隙とを連通させるように構成された第2冷却孔を含む。
上記(4)の構成によれば、シュラウド部の内壁面と遮蔽板とにより形成される冷却通路と間隙とを連通させるように構成された第2冷却孔を介して、冷却通路を流れる冷却流体を間隙に供給することができ、高温の流体が間隙に侵入するのを防止することができる。
(6)また、幾つかの実施形態では、上記(1)~(5)のいずれかの構成において、前記溶接部は、前記間隙の幅方向に沿った第2溶接部を含む。
上記(5)又は(6)の構成によれば、第1溶接部及び/又は第2溶接部により、翼型部とシュラウド部とを強固に接合することができる。
前記シュラウド部には、前記流体流路に開口するように前記間隙の周囲に設けられ、且つ、前記冷却流体を噴出するように構成された噴射孔が形成されており、
前記噴射孔は、前記流体流路側に向かうにつれて前記翼型部に近づくように前記径方向に対して傾斜している。
上記(7)の構成によれば、間隙の周囲においてシュラウド部に設けられた噴射孔から翼型部に向けて冷却流体が噴射されるので、流体流路内の高温流体の間隙への侵入を抑制できる。よって、間隙への高温流体の流入が阻害され、溶接部の温度上昇を抑制するとともに、翼型部の温度上昇を抑制することができる。これにより、タービン翼の寿命をより向上させることができる。
上記(8)の構成によれば、タービン翼の組み立て時において翼型部の端部をシュラウド部の開口に嵌入する際、シュラウド部の開口の縁と翼型部とが接触してしまっても、シュラウド部の開口の縁が湾曲状の滑らかな断面形状を有するので、翼型部の表面に損傷が生じ難い。これにより、タービン翼の寿命をより向上させることができる。
タービンの流体流路内に設けられる翼型部と、前記翼型部の端部が嵌合される開口を有するシュラウド部と、を含むタービン翼の製造方法であって、
前記シュラウド部又は前記翼型部の少なくとも一方に形成された冷却孔が、前記シュラウド部の前記開口を形成する壁面と前記翼型部の前記端部の外周面との間に形成される間隙に開口するように、前記シュラウド部の前記開口に前記翼型部の前記端部を嵌入するステップと、
前記冷却孔を挟んで前記流体流路とは反対側において、前記シュラウド部の前記壁面と前記翼型部の前記外周面とを溶接するステップと、を備え、
前記溶接するステップでは、少なくとも前記冷却孔の開口位置と該開口位置よりも前記流体流路側において前記間隙が残るように、前記冷却孔からみて前記流体流路とは反対側においてのみ前記間隙に溶接部を形成する。
上記(11)の方法によれば、翼型部及びシュラウド部をそれぞれ鋳造により作製するので、翼型部及びシュラウド部を一体的に鋳造する場合に比べて、鋳造品の構造が比較的簡素になる。このため、鋳造時の欠陥を低減し、歩留まりを向上させることができる。
前記シュラウド部は、前記翼型部の一端側及び他端側にそれぞれ設けられ、且つ、前記開口をそれぞれ有する内側シュラウド及び外側シュラウドを含み、
前記嵌入するステップでは、前記内側シュラウド及び前記外側シュラウドの各々の前記開口を形成する前記壁面と前記翼型部の各々の端部の前記外周面との間に形成される前記間隙に前記冷却孔が開口するように、前記内側シュラウド及び前記外側シュラウドの各々の前記開口に前記翼型部の各々の端部を嵌入し、
前記溶接するステップでは、前記冷却孔を挟んで前記流体流路とは反対側において、前記内側シュラウド及び前記外側シュラウドの前記壁面と前記翼型部の各々の端部の前記外周面とを溶接する。
上記(12)の方法で得られるタービン翼によれば、内側シュラウドと翼型部との間、及び、外側シュラウドと翼型部との間のそれぞれに形成された間隙に冷却孔から冷却流体が供給されるので、より効果的に高温の流体が間隙に侵入するのを防止することができる。これにより、各々の間隙を挟んで流体流路側とは反対側に位置する各々の溶接部の温度上昇を抑制することができ、タービン翼の寿命をより向上させることができる。
圧縮機2は、圧縮機車室10と、圧縮機車室10の入口側に設けられ、空気を取り込むための空気取入口12と、圧縮機車室10及び後述するタービン車室22を共に貫通するように設けられたロータ8と、圧縮機車室10内に配置された各種の翼と、を備える。各種の翼は、空気取入口12側に設けられた入口案内翼14と、圧縮機車室10側に固定された複数の静翼16と、静翼16に対して交互に配列されるようにロータ8に植設された複数の動翼18と、を含む。なお、圧縮機2は、不図示の抽気室等の他の構成要素を備えていてもよい。このような圧縮機2において、空気取入口12から取り込まれた空気は、複数の静翼16及び複数の動翼18を通過して圧縮されることで高温高圧の圧縮空気となる。そして、高温高圧の圧縮空気は圧縮機2から後段の燃焼器4に送られる。
また、タービン6には、圧縮機2内部の空気が圧縮機2から燃焼器4を迂回(バイパス)して供給される図示しないバイパス流路が設けられている。このバイパス流路を通してタービン6に供給された空気は、冷却流体G2(図3参照)としてタービン静翼本体及びタービン動翼本体それぞれの内部を流通するようになっている。
タービン車室22の下流側には、排気車室28を介して排気室29が連結されている。タービン6を駆動した後の燃焼ガスは、排気車室28及び排気室29を介して外部へ排出される。
各単位構造Uの各シュラウド部40(40A,40B)は連結部40aを有しており、当該連結部40aにおいて、隣接する単位構造Uの連結部40aを介して連結可能になっていてもよい。
燃焼ガスG1が流れる流体流路72は、外側シュラウド40A及び内側シュラウド40Bを隔壁として翼型部30が配列した範囲に形成される。
また、翼型部30は、タービン6の径方向に沿って貫通するように設けられた中空部74を有する。この中空部74には、圧縮機2からの冷却流体G2が流れるようになっており、冷却流体G2によって翼型部30を冷却することで、流体流路72を流れる高温流体(燃焼ガスG1)の熱による損傷から翼型部30を保護するようになっている。翼型部30には、中空部74と流体流路72を連通する図示されない孔が複数設けられており、中空部74からの冷却流体G2がこの孔を通過して、翼型部30をより効果的に冷却するようになっていてもよい。
シュラウド部40と翼型部30との間に形成された間隙50によって、翼型部30及びシュラウド部40の僅かな変形が許容されるので、タービン6の運転中における溶接部51への応力集中を抑制できる。
また、図9~図11に示す実施形態に係るタービン翼100では、溶接部51は、間隙50の幅方向に沿った第2溶接部54(54a~54c)を含む。
このようにタービン翼100は、第1溶接部52又は第2溶接部54(54a~54c)により、翼型部30とシュラウド部40とを強固に接合することができる。また、図10に示すように、間隙50の延在方向に沿った第1溶接部52及び間隙50の幅方向に沿った第2溶接部54(54a~54c)の両方を設けることにより、翼型部30とシュラウド部40とをより強固に接合することができる。
この冷却孔(34,44)から、シュラウド部40と翼型部30との間に形成された間隙50に冷却流体G2が供給されるので、流体流路72を流れる高温の流体(燃焼ガスG1)が間隙50に侵入するのを防止することができる。これにより、間隙50を挟んで流体流路72とは反対側に位置する溶接部51(52,54)の温度上昇を抑制することができ、タービン翼100の寿命を向上させることができる。
このような第1冷却孔34は、翼型部30において、周状に複数設けられていてもよく、タービン6の径方向において複数設けられていてもよい。第1冷却孔34を複数設けることで、流体流路72を流れる高温流体(燃焼ガスG1)が間隙50に侵入するのをより効果的に防止することができる。
このような第2冷却孔44は、シュラウド部40において、周状に複数設けられていてもよく、タービン6の径方向において複数設けられていてもよい。第2冷却孔44を複数設けることで、流体流路72を流れる高温流体(燃焼ガスG1)が間隙50に侵入するのをより効果的に防止することができる。
このタービン翼100では、シュラウド部40に設けられた噴射孔46から翼型部30に向けて冷却流体が噴射されるので、流体流路72内の高温流体の間隙50への侵入をさらに抑制することができる。
シュラウド部40の縁41が上述のような湾曲形状であることにより、タービン翼100の組み立て時において翼型部30の端部32をシュラウド部40の開口42に嵌入する際、シュラウド部40の開口42の縁41と翼型部30とが接触してしまっても、翼型部30の表面に損傷が生じ難い。これにより、タービン翼100の寿命をより向上させることができる。
一実施形態に係るタービン翼100の製造方法は、以下に説明する嵌入ステップ及び溶接ステップを備える。
まず、シュラウド部40の開口42に翼型部30の端部32を嵌入する。この際、シュラウド部40の開口42を形成する壁面43と翼型部30の端部32の外周面33との間に間隙50が形成されるようにするとともに、シュラウド部40又は翼型部30の少なくとも一方に形成された冷却孔(第1冷却孔34又は第2冷却孔44)が、間隙50に開口するようにする(嵌入ステップ)。
次に、冷却孔(第1冷却孔34又は第2冷却孔44)を挟んで流体流路72とは反対側において、シュラウド部40の壁面43と翼型部30の外周面33とを溶接する(溶接ステップ)。溶接ステップでは、冷却孔(第1冷却孔34又は第2冷却孔44)の開口位置と、該開口位置よりも流体流路72側において間隙50が残るように、冷却孔(第1冷却孔34又は第2冷却孔44)からみて流体流路72とは反対側においてのみ間隙50に溶接部51を形成する。
溶接方法としては、例えば、レーザ溶接、電子ビーム溶接、プラズマ溶接、TIG溶接等、各種の溶接方法を用いることができる。
なお、形成されるスリットの深さ(間隙50の延在方向における長さ)は、溶接時の溶け込み深さによって決まるが、溶接時の溶け込み深さは、溶接条件で制御することができる。
このように側方から溶接を行う場合、溶接の層を増やすことで溶け込み深さを増加させることができるため、所望の溶け込み深さとすることが比較的容易である。よって、シュラウド部40の開口42の壁面43と、翼型部30の端部32の外周面33との間にスリット(間隙50)が比較的容易に形成される。なお、図9~図11では、第2溶接部54は、54a~54cで示される3つの層によって形成されている。
溶接の手段としては、例えば、レーザ溶接、電子ビーム溶接等、各種の溶接方法を用いることができる。
このように、翼型部30又はシュラウド部40のうち一方のフランジ(101,102)と他方の当接面(84,86)を合わせることで、溶接の際に、タービン6の径方向における位置合わせが容易となる。
この場合、まず、翼型部30又はシュラウド部40のうち一方のフランジ(101,102)と他方の当接面(84,86)との合わせ面を接合するように溶接を行うことで第2溶接部(54a,54d)を形成し、次いで、溶接部所望の深さになるように溶接の層(第2溶接部(54b,54c,54e,54f))を形成することで、所望の長さの第2溶接部54を容易に形成することができ、所望の長さのスリット(間隙50)を得ることができる。
このように、翼型部30及びシュラウド部40をそれぞれ鋳造により作製することで、翼型部30及びシュラウド部40を一体的に鋳造する場合に比べて、鋳造品の構造が比較的簡素になる。このため、鋳造時の欠陥を低減し、歩留まりを向上させることができる。
例えば、「同一」、「等しい」及び「均質」等の物事が等しい状態であることを表す表現は、厳密に等しい状態を表すのみならず、公差、若しくは、同じ機能が得られる程度の差が存在している状態も表すものとする。
例えば、四角形状や円筒形状等の形状を表す表現は、幾何学的に厳密な意味での四角形状や円筒形状等の形状を表すのみならず、同じ効果が得られる範囲で、凹凸部や面取り部等を含む形状も表すものとする。
一方、一の構成要素を「備える」、「含む」、又は、「有する」という表現は、他の構成要素の存在を除外する排他的な表現ではない。
2 圧縮機
4 燃焼器
5 静翼
6 タービン
8 ロータ
10 圧縮機車室
12 空気取入口
14 入口案内翼
16 静翼
18 動翼
20 ケーシング
22 タービン車室
24 静翼
26 動翼
28 排気車室
29 排気室
30 翼型部
32 端部
33 外周面
34 第1冷却孔
40 シュラウド部
40A 外側シュラウド
40B 内側シュラウド
40a 連結部
41 縁
42 開口
43 壁面
44 第2冷却孔
45 内壁面
46 噴射孔
47 フランジ
48 遮蔽板
49 冷却通路
50 間隙
51 溶接部
52 第1溶接部
54 第2溶接部
72 流体流路
74 中空部
76 壁面
84 当接面
86 当接面
100 タービン翼
101 フランジ
102 フランジ
U 単位構造
Claims (12)
- タービンの径方向に沿って設けられるタービン翼であって、
前記タービンの流体流路内に位置する翼型部と、
前記径方向における前記翼型部の内側又は外側に位置し、且つ、前記翼型部の端部が嵌合される開口を有するシュラウド部と、を備え、
前記シュラウド部の前記開口を形成する壁面と前記翼型部の前記端部の外周面との間には、間隙が形成されており、
前記シュラウド部の前記壁面と前記翼型部の前記外周面とは、前記間隙を挟んで前記流体流路とは反対側において、溶接部を介して互いに接合されており、
前記シュラウド部又は前記翼型部の少なくとも一方には、前記間隙に開口し且つ前記間隙に冷却流体を供給するように構成された冷却孔が設けられたことを特徴とするタービン翼。 - 前記シュラウド部は、前記径方向において前記翼型部の内側および外側にそれぞれ設けられ、且つ、前記開口をそれぞれ有する内側シュラウド及び外側シュラウドを含み、
前記内側シュラウド及び前記外側シュラウドの各々の前記壁面と前記翼型部の各々の端部の前記外周面との間には、前記間隙が形成されており、
前記内側シュラウド及び前記外側シュラウドの各々の前記壁面と前記翼型部の各々の端部の前記外周面とは、前記間隙を挟んで前記流体流路とは反対側において、前記溶接部を介して互いに接合されていることを特徴とする請求項1に記載のタービン翼。 - 前記翼型部は、前記冷却流体が流れるように構成された中空部を有し、
前記冷却孔は、前記翼型部の前記中空部と前記間隙とを連通させるように構成された第1冷却孔を含むことを特徴とする請求項1又は2に記載のタービン翼。 - 前記シュラウド部内に設けられ、前記冷却流体が流れるように構成された冷却通路を前記シュラウド部の内壁面とともに形成する遮蔽板をさらに備え、
前記冷却孔は、前記シュラウド部内の前記冷却通路と前記間隙とを連通させるように構成された第2冷却孔を含むことを特徴とする請求項1乃至3の何れか一項に記載のタービン翼。 - 前記溶接部は、前記間隙の延在方向に沿った第1溶接部を含むことを特徴とする請求項1乃至4の何れか一項に記載のタービン翼。
- 前記溶接部は、前記間隙の幅方向に沿った第2溶接部を含むことを特徴とする請求項1乃至5の何れか一項に記載のタービン翼。
- 前記シュラウド部には、前記流体流路に開口するように前記間隙の周囲に設けられ、且つ、前記冷却流体を噴出するように構成された噴射孔が形成されており、
前記噴射孔は、前記流体流路側に向かうにつれて前記翼型部に近づくように前記径方向に対して傾斜していることを特徴とする請求項1乃至6の何れか一項に記載のタービン翼。 - 前記シュラウド部のうち、前記流体流路に面する前記開口の縁は、前記翼型部の延在方向に沿った断面形状が湾曲形状であることを特徴とする請求項1乃至7の何れか一項に記載のタービン翼。
- 請求項1乃至8の何れか一項に記載のタービン翼を含むロータを備えることを特徴とするタービン。
- タービンの流体流路内に設けられる翼型部と、前記翼型部の端部が嵌合される開口を有するシュラウド部と、を含むタービン翼の製造方法であって、
前記シュラウド部又は前記翼型部の少なくとも一方に形成された冷却孔が、前記シュラウド部の前記開口を形成する壁面と前記翼型部の前記端部の外周面との間に形成される間隙に開口するように、前記シュラウド部の前記開口に前記翼型部の前記端部を嵌入するステップと、
前記冷却孔を挟んで前記流体流路とは反対側において、前記シュラウド部の前記壁面と前記翼型部の前記外周面とを溶接するステップと、を備え、
前記溶接するステップでは、少なくとも前記冷却孔の開口位置と該開口位置よりも前記流体流路側において前記間隙が残るように、前記冷却孔からみて前記流体流路とは反対側においてのみ前記間隙に溶接部を形成することを特徴とするタービン翼の製造方法。 - 前記翼型部及び前記シュラウド部をそれぞれ鋳造する鋳造ステップをさらに備えることを特徴とする請求項10に記載のタービン翼の製造方法。
- 前記シュラウド部は、前記翼型部の一端側及び他端側にそれぞれ設けられ、且つ、前記開口をそれぞれ有する内側シュラウド及び外側シュラウドを含み、
前記嵌入するステップでは、前記内側シュラウド及び前記外側シュラウドの各々の前記開口を形成する前記壁面と前記翼型部の各々の端部の前記外周面との間に形成される前記間隙に前記冷却孔が開口するように、前記内側シュラウド及び前記外側シュラウドの各々の前記開口に前記翼型部の各々の端部を嵌入し、
前記溶接するステップでは、前記冷却孔を挟んで前記流体流路とは反対側において、前記内側シュラウド及び前記外側シュラウドの前記壁面と前記翼型部の各々の端部の前記外周面とを溶接することを特徴とする請求項10又は11に記載のタービン翼の製造方法。
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- 2015-01-27 JP JP2015013140A patent/JP6677969B2/ja active Active
- 2015-09-25 DE DE112015006056.1T patent/DE112015006056B4/de not_active Expired - Fee Related
- 2015-09-25 KR KR1020177020032A patent/KR101939519B1/ko active IP Right Grant
- 2015-09-25 CN CN201580070366.9A patent/CN107109952B/zh not_active Expired - Fee Related
- 2015-09-25 WO PCT/JP2015/077152 patent/WO2016121163A1/ja active Application Filing
- 2015-09-25 US US15/543,046 patent/US20180010460A1/en not_active Abandoned
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3293354A1 (en) * | 2016-09-07 | 2018-03-14 | Ansaldo Energia IP UK Limited | Turboengine blading member and a method for assembling such a member |
EP3306039A1 (en) * | 2016-10-06 | 2018-04-11 | Rolls-Royce plc | Stator assembly for a gas turbine engine |
US10337342B2 (en) | 2016-10-06 | 2019-07-02 | Rolls-Royce Plc | Stator assembly for a gas turbine engine |
EP3495622A1 (en) * | 2017-12-06 | 2019-06-12 | Rolls-Royce plc | Aerofoil, corresponding assembly and methods of manufacturing |
Also Published As
Publication number | Publication date |
---|---|
DE112015006056T5 (de) | 2017-10-12 |
DE112015006056B4 (de) | 2021-08-26 |
KR101939519B1 (ko) | 2019-04-11 |
JP6677969B2 (ja) | 2020-04-08 |
CN107109952A (zh) | 2017-08-29 |
JP2016138485A (ja) | 2016-08-04 |
US20180010460A1 (en) | 2018-01-11 |
CN107109952B (zh) | 2020-05-15 |
KR20170097157A (ko) | 2017-08-25 |
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