WO2017115643A1 - タービン翼の補修方法 - Google Patents
タービン翼の補修方法 Download PDFInfo
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- WO2017115643A1 WO2017115643A1 PCT/JP2016/087066 JP2016087066W WO2017115643A1 WO 2017115643 A1 WO2017115643 A1 WO 2017115643A1 JP 2016087066 W JP2016087066 W JP 2016087066W WO 2017115643 A1 WO2017115643 A1 WO 2017115643A1
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- turbine blade
- pressurized water
- cleaning
- blade
- cleaning process
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/002—Cleaning of turbomachines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/02—Cleaning by the force of jets or sprays
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
- B08B3/08—Cleaning involving contact with liquid the liquid having chemical or dissolving effect
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
- B08B3/10—Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration
- B08B3/12—Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration by sonic or ultrasonic vibrations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B9/00—Cleaning hollow articles by methods or apparatus specially adapted thereto
- B08B9/02—Cleaning pipes or tubes or systems of pipes or tubes
- B08B9/027—Cleaning the internal surfaces; Removal of blockages
- B08B9/032—Cleaning the internal surfaces; Removal of blockages by the mechanical action of a moving fluid, e.g. by flushing
- B08B9/0321—Cleaning the internal surfaces; Removal of blockages by the mechanical action of a moving fluid, e.g. by flushing using pressurised, pulsating or purging fluid
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
- B24C1/086—Descaling; Removing coating films
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C3/00—Abrasive blasting machines or devices; Plants
- B24C3/32—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
- B24C3/325—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks for internal surfaces, e.g. of tubes
- B24C3/327—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks for internal surfaces, e.g. of tubes by an axially-moving flow of abrasive particles without passing a blast gun, impeller or the like along the internal surface
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- 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
- F01D5/005—Repairing methods or devices
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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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01D5/187—Convection cooling
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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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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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
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B2209/00—Details of machines or methods for cleaning hollow articles
- B08B2209/005—Use of ultrasonics or cavitation, e.g. as primary or secondary action
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B2209/00—Details of machines or methods for cleaning hollow articles
- B08B2209/02—Details of apparatuses or methods for cleaning pipes or tubes
- B08B2209/027—Details of apparatuses or methods for cleaning pipes or tubes for cleaning the internal surfaces
- B08B2209/032—Details of apparatuses or methods for cleaning pipes or tubes for cleaning the internal surfaces by the mechanical action of a moving fluid
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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
- F05D2230/10—Manufacture by removing material
- F05D2230/11—Manufacture by removing material by electrochemical 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
- F05D2230/00—Manufacture
- F05D2230/40—Heat treatment
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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
- F05D2230/72—Maintenance
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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
- F05D2230/80—Repairing, retrofitting or upgrading 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
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
Definitions
- the present invention relates to a method of repairing a turbine blade having an internal cooling passage for circulating a refrigerant.
- Patent Document 1 discloses a technique of removing a ceramic bond coat by immersion in a stripping solution after removing the ceramic top coat by a known method such as an autoclave.
- the turbine blade is cleaned by grit blasting, and heat coloring is performed to check whether or not a metal bond coat remains. Tinto is done.
- the turbine blade is sent to repair processes such as repair of damage as needed and recoating of the coating.
- the above-mentioned grit blasting is performed as a pretreatment for heating and coloring inspection (heat tinting) for the purpose of cleaning the turbine blade by removing the residue of the reaction layer and the metal bond coat generated on the blade surface by the stripping solution. It will be. However, a part of the blast particles used for the blast treatment may be mixed into the internal cooling channel of the turbine blade and stuck to the inner wall surface by the stripping solution remaining in the internal cooling channel. Since blasting and heat coloring inspection (heat tinting) are the final treatments of a series of steps for removing the coating (protective layer) from the turbine blade, it is possible that the blast particles generated here remain in the blade. It may cause a defect in the repair work of the turbine blade and the graft work of the turbine blade after the completion of the repair.
- heating and coloring inspection heat tinting
- the present invention has been made in view of the above, and in the repair process of a turbine blade having an internal cooling flow passage for circulating the refrigerant, the time until a series of processes for removing the protective layer from the turbine blade is completed.
- the main purpose is to remove blast particles better from inside the turbine blade.
- the present invention provides a method of repairing a turbine blade having a first coating layer as a protective layer applied to the outer surface and an internal cooling channel for circulating a refrigerant.
- Ultrasonic cleaning treatment for immersing the turbine blade in a water tank and conducting ultrasonic waves in the water tank to clean the turbine blade after the cleaning step; and the internal cooling flow after the ultrasonic cleaning treatment It is characterized by having a blast grain washing process which performs pressurization water washing processing which sprays pressurization water into a channel at least once.
- the turbine blade is formed into a water tank after the first coating layer removing step of removing the first coated layer by chemical treatment and the cleaning step of cleaning the turbine blade by blasting.
- An ultrasonic cleaning process that conducts ultrasonic waves in the water tank to conduct ultrasonic waves in the water tank and cleans the turbine blades, and a blast particle that performs at least one pressurized water cleaning process that sprays pressurized water into the internal cooling flow path after the ultrasonic cleaning process.
- a washing step is performed.
- the blast particles used in the blasting process of the cleaning process are mixed into the internal cooling channel of the turbine blade and stick to the inner wall surface, the ultrasonic cleaning process is performed from the inner wall surface of the internal cooling channel
- the grains can be exfoliated well.
- grains which remained in the internal cooling flow path can be removed more reliably by a pressurized water washing process. Therefore, according to the present invention, in the repair process of the turbine blade having the internal cooling flow passage for circulating the coolant, the blast particles are internally blasted from the inside of the turbine blade until the series of processes for removing the protective layer from the turbine blade is completed. Can be removed better.
- the method of repairing a turbine blade according to the present invention further includes a heat tinting step of performing a heat treatment to inspect whether or not the first coating layer remains on the turbine blade after the blast particle cleaning step.
- the turbine blade may be a moving blade, and the internal cooling passage may be opened at a blade top and a blade root of the turbine blade, and the pressurized water cleaning In the treatment, pressurized water may be injected into the internal cooling channel from any one of the opening of the tip and the opening of the blade root.
- pressurized water may be injected into the internal cooling channel from any one of the opening of the tip and the opening of the blade root.
- the pressurized water cleaning process is performed with the turbine blade supported so that the longitudinal direction is along the vertical direction, and the vertical direction upper side of the opening of the blade top and the opening of the blade root
- the pressurized water may be jetted from one side of the As a result, blast particles adhering to the inside of the internal cooling flow passage can be washed out from the upper side in the vertical direction by the injection of pressurized water and can be removed well.
- the blast particle cleaning step switches the supporting direction so that the vertical direction of the turbine blade is opposite to that in the previous pressurized water cleaning process, and then the next time
- the pressurized water cleaning process of As a result, when the pressurized water cleaning process is performed multiple times, the flow direction of the pressurized water supplied into the internal cooling channel can be switched, so that the blast particles adhering to the internal cooling channel can be removed extremely well. It is possible to
- the pressurized water cleaning process may be performed for the first time in a state where the turbine blade is supported such that the blade top is vertically upward.
- the method may further include a scale cleaning step of performing at least once the ultrasonic cleaning process and the pressurized water cleaning process performed after the ultrasonic cleaning process.
- a residual stress removing step is performed in which heat treatment is performed to remove the stress remaining on the turbine blade. Thereby, it is possible to well suppress the occurrence of stress corrosion cracking in the turbine blade in the first coating layer removing step.
- a scale cleaning process is performed which performs at least one ultrasonic cleaning process and the pressurized water cleaning process performed after the ultrasonic cleaning process. As a result, the water-soluble scale attached to the outer peripheral surface of the turbine blade and the inner wall surface of the internal cooling channel by ultrasonic cleaning can be favorably peeled off.
- the water-soluble scale which remained in the internal cooling flow path can be removed more reliably by a pressurized water washing process. Therefore, according to the present invention, it is possible to favorably remove the water-soluble scale attached to the turbine blade by a simpler method before heat-treating the turbine blade.
- the turbine blade may have a second coating layer applied to the outside of the first coating layer, and the second stress layer removing step may be performed before the residual stress removing step.
- the method may further include a second coating layer removing step of removing the coating layer by blasting.
- the water-soluble scale attached to the second coated layer is favorably performed together with the second coated layer by blasting to remove the second coated layer before the heat treatment for residual stress removal is applied to the turbine blade. It is removed.
- the water-soluble scale attached to the outer peripheral surface of the turbine blade other than the second coating layer that can not be removed by the blasting process or in the internal cooling flow path is subjected to heat treatment for residual stress removal before the turbine blade is treated.
- the method for repairing a turbine blade according to the present invention is suitable for application to a turbine blade having a second coated layer.
- the 2nd film layer removal process and the scale washing process are before a residual stress removal process, either may be performed first.
- the turbine in the repairing process of a turbine blade having an internal cooling flow passage for circulating the refrigerant, the turbine is completed until a series of processes of removing the protective layer from the turbine blade is completed. It is possible to better remove blast particles from the inside of the wing.
- FIG. 1 is a cross-sectional view showing an example of a gas turbine blade to be a target of the method of repairing a turbine blade according to the embodiment of the present invention.
- FIG. 2 is a schematic view showing a protective layer removing system for performing a protective layer removing step as a method of repairing a turbine blade according to an embodiment of the present invention.
- FIG. 3 is a flow chart showing an example of the protective layer removing step.
- FIG. 4 is a flowchart showing an example of the deposit cleaning step included in the protective layer removing step.
- FIG. 1 is a cross-sectional view showing a turbine blade 1 as a target of the method of repairing a turbine blade according to an embodiment of the present invention.
- the turbine blade 1 is a moving blade used for the front stage (for example, the first and second stages) of a known gas turbine, and is disposed in a turbine cabin (not shown).
- the object of the method of repairing a turbine blade according to the present invention is not limited to the turbine blade 1.
- the object of the method of repairing a turbine blade according to the present invention may be a turbine blade mounted on the rear stage of a gas turbine, a gas turbine stator blade, or a motion used in a steam turbine It may be a wing or a vane.
- the turbine blade 1 includes a blade 2 forming a profile, a platform 3 joined to the blade 2, and a shank 4 extending from the platform 3 to the opposite side of the blade 2.
- a blade root (not shown) attached to the disk of the gas turbine rotor.
- a plurality of internal cooling channels 5 extending from a blade root (not shown) to a blade tip 2 T which is a tip of the blade portion 2.
- the plurality of internal cooling channels 5 are configured as serpentine channels formed such that a portion thereof meanders inside the wing portion 2.
- the plurality of internal cooling channels 5 are respectively opened at the blade root and the blade tip 2T, and cooling air is supplied into the internal cooling channel 5 from the rotor (not shown) through the openings of the blade roots. .
- the cooling air supplied into the internal cooling flow passage 5 is formed at the opening of the wing tip 2T and at the leading edge and trailing edge of the wing portion 2 after passing through the inside of the shank 4, the platform 3 and the wing portion 2.
- the gas is discharged to the outside of the turbine blade 1 from a plurality of outflow holes (none of which are shown). Thereby, it is possible to effectively cool the front stage turbine blade 1 exposed to a high temperature environment for a long time.
- the opening of the wing root which is not shown in figure may be opened downward of FIG. 1, and may be opened facing either the left or right of FIG.
- the turbine blade 1 configured in this manner includes a bond coat layer (first coat layer) coated on the outer peripheral surface of the wing portion 2 and a top coat layer (second coat layer) coated on the outside of the bond coat layer.
- a protective layer composed of The bond coat layer is formed of, for example, an MCrAlY alloy (where M is Co, Ni, or a combination of these elements), and functions as a metal bonding layer that enhances the adhesion between the wing 2 and the top coat layer.
- the top coat layer is a film made of zirconia (ZrO 2 ) -based ceramic and functions as a thermal barrier coating (TBC) film having a thermal barrier property. Thereby, the heat resistance of the turbine blade 1 can be improved.
- FIG. 2 is a schematic view showing a protective layer removal system 10 for performing a protective layer removal process as a method of repairing a turbine blade according to an embodiment of the present invention.
- the protective layer removing system 10 comprises a blasting device 11 for blasting the turbine blade 1 to remove the top coat layer, an ultrasonic cleaning device 12 for performing ultrasonic cleaning treatment on the turbine blade 1, and pressurized water on the turbine blade 1 Pressurized water cleaning device 13 which performs cleaning, heat treatment device 14 which performs heat treatment for removing residual stress to turbine blade 1, blast device 15 which performs blasting for removing oxide film on turbine blade 1, and bond coat A cleaning device 16 for performing pickling treatment for removing layers, etc.
- blasting device 17 for performing blasting treatment for cleaning the turbine blade 1, and a turbine blade for heat treatment for performing heating coloring inspection 1 and a heat treatment apparatus 18 to be applied.
- the blasting devices 11, 15 and 17 may be used as any of the devices.
- FIG. 3 is a flow chart showing an example of the protective layer removing step.
- the protective layer removing step first, the turbine blade 1 is subjected to a blasting process using the blasting device 11 to remove the top coat layer coated on the outer peripheral surface (second coated layer removing step) Is executed (step S11).
- blasting is performed using an alumina-based projectile.
- the top coat layer which is a film made of ceramics can be removed satisfactorily.
- the projection material used for a blast process is not restricted to an alumina type.
- the water-soluble scale attached to the outer surface of the top coat layer of the turbine blade 1 can be removed together with the top coat layer during operation of the gas turbine.
- the water-soluble scale attached to the inner wall surface of the plurality of internal cooling channels 5, the platform 3 and the shank 4 can not be removed in the top coat layer removing step.
- a heat treatment (step S13) for removing residual stress, which will be described later, is performed on the turbine blade 1 in this state, high temperature corrosion may occur at the location where the water-soluble scale adheres.
- the adhered substance cleaning step shown in FIG. 4 is executed using the ultrasonic cleaning device 12 and the pressurized water cleaning device 13 (step S12).
- the deposit cleaning step will be described in detail later, by performing the step, the water-soluble scale attached to the turbine blade 1 can be removed well.
- a residual stress removing process is performed which applies a heat treatment for removing the residual stress using the heat treatment apparatus 14 to the turbine blade 1 (step S13).
- residual stress is removed from the turbine blade 1 by heat treating the turbine blade 1 using a vacuum heat treatment apparatus 14.
- an oxide film removing step is performed to remove the oxide film generated on the turbine blade 1 by the heat treatment in the residual stress removing step by the blast processing of the blast device 15 (step S14). Thereby, it becomes possible to improve the effect of the pickling treatment in the bonding coat layer removing step (step S15) described later.
- a pickling process is performed on the turbine blade 1 using the cleaning device 16 to perform a bonding coat layer removing step (first film layer removing step) of removing the bonding coat layer from the wing portion 2 (step S15).
- the turbine blade 1 is immersed in a liquid bath (not shown) filled with a strongly acidic cleaning solution (for example, hydrochloric acid etc.) contained in the cleaning device 16 to form a bonding coating layer from the turbine blade 1
- a strongly acidic cleaning solution for example, hydrochloric acid etc.
- the turbine blade 1 is subjected to a blasting process using the blast device 17 to perform a cleaning process for cleaning the turbine blade 1 (step S16).
- the cleaning step the residue of the reaction layer generated on the outer surface of the turbine blade 1 by the pickling process in the bonding coat layer removing step of step S15 or the bonding coat layer that could not be removed by the acid cleaning process is removed. Done for the purpose.
- the outer surface of the turbine blade 1 can be cleaned, and the heating and coloring inspection (heat tint) described later can be more appropriately performed.
- the protective layer removing step of the present embodiment after the execution of the cleaning step (step S16), the ultrasonic cleaning device 12 and the pressurized water cleaning device 13 are used to remove the blast particles attached in the internal cooling flow passage 5.
- the deposit cleaning step shown in FIG. 4 is executed again using step S17.
- the heat treatment apparatus 18 is used to perform a heat coloring process (heat tinting) to check whether the protective layer (bond coat layer) remains on the turbine blade 1 or not. 1 (step S18), and it is determined whether removal of the protective layer (bonding coat layer) is completed (step S19).
- step S19 the presence of a protective layer (bonding coat layer) is inspected by visually inspecting the colored state of the outer surface of the turbine blade 1 after heating. Then, if it is determined that the removal of the protective layer (bonding coat layer) is not completed in the inspection, the processing after step S15 is repeated again.
- the protective layer using a polishing tool such as a grinder instead of repeating the process after step S15 (bonding The coating layer) may be removed.
- the protective layer removing step is ended. Thereafter, the turbine blade 1 is subjected to a repair operation for damage as needed and a recoating operation for the protective layer, and when the repair is completed, the turbine blade 1 is transplanted to the gas turbine again.
- adhered substance cleaning process performed in steps S12 and S17 will be described in detail.
- adhered matter refers to the water-soluble scale adhering to the turbine blade 1 during operation of the gas turbine in the adhered matter cleaning step performed in step S12, and in step S17 In the attached substance washing process to be performed, it shows the thing of the blast particle used at the cleaning process of step S16.
- the turbine blade 1 is supported so that the longitudinal direction (vertical direction in FIG. 1) is along the vertical direction (step S21). At this time, the tip 2T of the turbine blade 1 is set to be vertically above.
- “as the longitudinal direction follows the vertical direction” is not only when the longitudinal direction coincides with the vertical direction, but when the longitudinal direction has a slight angle with the vertical direction, that is, the turbine blade 1 The case of being inclined at a slight angle shall also be included.
- the ultrasonic cleaning device 12 has a water tank provided with a transmitter and a vibrator (none of which is shown). And ultrasonic cleaning processing immerses the turbine blade 1 in the water tank in which the said transmitter and vibrator were installed, and generates and conducts an ultrasonic wave in a water tank by a transmitter and vibrator, Peel off the deposits attached to the surface of Thereby, the deposit
- step S12 in the deposit cleaning process (scale cleaning process) in step S12, it is possible to exfoliate the water-soluble scale adhering to the outer surface of the turbine blade 1 to which the top coat layer is not applied such as the platform 3 and the shank 4 This process works effectively. Then, after the ultrasonic cleaning process is performed, the turbine blade 1 pulled up from the water tank is sent to the next step with the posture supported in step S21. Thus, by performing the ultrasonic cleaning process while supporting the turbine blade 1 so that the longitudinal direction is along the vertical direction, it is possible to more easily immerse the turbine blade 1 in the water tank and withdraw it from the water tank. Is possible.
- a pressurized water cleaning process is performed in which pressurized water is jetted and washed into the plurality of internal cooling flow paths 5 of the turbine blade 1 using the pressurized water cleaning device 13 (step S23).
- pressurized water is supplied to each of the openings 2T of the plurality of internal cooling channels 5.
- the injection nozzle is inserted, and pressurized water is directly injected into the internal cooling flow passage 5.
- the deposits remaining in the internal cooling channel 5 including the deposits that could not be peeled off by the ultrasonic cleaning treatment are thoroughly washed away with pressurized water from the blade top 2T to the blade root (inner wall surface ) And discharged to the outside of the turbine blade 1 (internal cooling passage 5) through the opening of the blade root.
- the present process is particularly suitable for removing deposits from a blade having a complicated internal cooling flow passage 5 such as the serpentine flow passage of the turbine blade 1 of the present embodiment.
- the injection nozzle of pressurized water may not necessarily be inserted in the opening of the internal cooling flow path 5 (may be jetted from a distant place). Further, in the present process, pressurized water may be injected not only toward the internal cooling flow passage 5 but also toward the outer peripheral surface of the turbine blade 1.
- pressurized water is introduced into the internal cooling flow path 5 from the opening of the wing top 2T positioned on the upper side in the vertical direction. Inject. Thereby, the extraneous matter in the internal cooling flow passage 5 can be washed away from the upper side in the vertical direction from the upper side to the lower side, and can be removed more favorably.
- the turbine blade 1 in which a large amount of deposits remain in the internal cooling flow passage 5, the turbine blade 1 so that the blade top 2T is on the upper side in the vertical direction.
- step S24 ultrasonic cleaning processing and pressurized water cleaning processing are executed again (steps S25, S26), and finally, the turbine A hot water and air blow are applied to the wing 1 (step S27), and the deposit cleaning process is completed.
- the deposits can be more favorably removed from the turbine blade 1.
- the second ultrasonic cleaning process and the pressurized water cleaning process are performed.
- step S23 the pressurized water is injected from the opening of the wing tip 2T into the internal cooling channel 5, whereas in the pressurized water cleaning process in step S26, the internal cooling channel from the blade root opening Spray pressurized water into 5.
- step S26 the internal cooling channel from the blade root opening Spray pressurized water into 5.
- the adhesion cleaning step (scale cleaning step) is performed in step S12 to perform heat treatment on the turbine blade 1 in the residual stress removing step of step S13.
- the water-soluble scale attached to the place where the top coat layer is not provided centering on the inside of the internal cooling flow passage 5 is favorably performed by a simpler method without using complicated and various chemical treatment and water washing treatment. It can be removed. Further, as described above, the water-soluble scale attached to the place where the top coat layer is applied is removed together with the top coat layer in the top coat layer removing step. Therefore, in the heat treatment for removing the residual stress, it is possible to well suppress the occurrence of high temperature corrosion in the turbine blade 1.
- step S17 by executing the deposit cleaning step (blast particle cleaning step) in step S17, the process until the end of the series of steps of removing the protective layer from the turbine blade 1 is completed.
- the blast particles used in the cleaning step of step S16 can be satisfactorily removed from the internal cooling flow path 5 of the turbine blade 1.
- step S16 the cleaning step of cleaning the turbine blade 1 by blasting (step S16)
- the turbine blade 1 is immersed in the water tank and the ultrasonic wave is conducted in the water tank to clean the turbine blade 1.
- step S22 and S25 and attached substance cleaning process (blast particle cleaning process) which performs pressurized water cleaning process (steps S23 and S26) for injecting pressurized water into the internal cooling flow path after ultrasonic cleaning process at least once Is performed (step S17), and then the heat tinting process (steps S18 and S19) is performed.
- blast particle cleaning process which performs pressurized water cleaning process for injecting pressurized water into the internal cooling flow path after ultrasonic cleaning process at least once Is performed (step S17), and then the heat tinting process (steps S18 and S19) is performed.
- the blast particles are removed from the inside of the turbine blade 1 until the series of processes for removing the protective layer from the turbine blade 1 is completed. It is possible to remove better.
- the processing in steps S24 to S26 may be omitted to perform ultrasonic cleaning and pressurized water cleaning only once, or ultrasonic cleaning and pressurized water cleaning may be performed. May be performed three or more times.
- the pressurized water cleaning process may be performed in the water tank after the water is discharged from the water tank after the ultrasonic cleaning process is performed.
- the turbine blade 1 is a blade
- the internal cooling flow passage 5 is opened at the blade tip 2T and blade root of the turbine blade 1
- the pressurized water cleaning process is performed at the blade tip 2T
- pressurized water is injected into the internal cooling channel 5 from any one of the openings of the blade root and the blade root.
- pressurized water may be supplied from an opening capable of supplying pressurized water to the internal cooling passage.
- the pressurized water cleaning process is located vertically above the opening of the blade top 2T and the opening of the blade root while supporting the turbine blade 1 so that the longitudinal direction is along the vertical direction.
- Spray pressurized water from As a result, the blast particles adhering to the inside of the internal cooling flow passage 5 can be washed out from the upper side in the vertical direction by the injection of pressurized water and can be removed well.
- the ultrasonic cleaning process and the pressurized water cleaning process are performed in a state in which the turbine blade 1 is supported so that the longitudinal direction is along the vertical direction.
- the turbine is such that the longitudinal direction is along the horizontal direction With the wing 1 supported, both ultrasonic cleaning and / or pressurized water cleaning may be performed.
- the attached matter cleaning step (blast particle cleaning step) has a supporting direction such that the vertical direction of the turbine blade 1 is opposite to that of the previous pressurized water cleaning process (step S23).
- step S24 the next pressurized water cleaning process (step S26) is performed.
- the support direction of the turbine blade 1 is switched before the second ultrasonic cleaning process (step S25), but the process of step S24 is at least the first pressurized water cleaning process (step S23). ) And the second pressurized water cleaning process (step S26).
- the process of step S24 may be omitted at all times, may be performed every time between each pressurized water cleaning, or may be performed only optionally. May be Furthermore, after the pressurized water cleaning process is performed once, the pressurized water cleaning process may be performed continuously after the process of step S24, that is, the support direction of the turbine blade 1 is switched.
- the attached substance cleaning step is a first pressurized water cleaning process (step S23) in a state where the turbine blade 1 is supported such that the tip 2T is vertically upward. I do.
- the first pressurized water cleaning process (step S23) or the ultrasonic cleaning process (step S22) may be performed in a state in which the turbine blade 1 is supported so that the blade root side is at the upper side in the vertical direction.
- the residual stress removing step is carried out so as to remove the stress remaining on the turbine blade 1 before the bonding coat layer (first coating layer) removing step (step S15) S13), before the residual stress removing step, adherent cleaning performed at least once with ultrasonic cleaning processing (steps S22, S25) and pressurized water cleaning processing (steps S23, S26) performed after the ultrasonic cleaning processing And step (scale cleaning step) (step S12).
- a residual stress removing step of performing heat treatment so as to remove the stress remaining on the turbine blade 1 is performed before the bonding coat layer removing step (step S13).
- the occurrence of stress corrosion cracking in the turbine blade 1 in the bonding coat layer removing step can be favorably suppressed.
- the above-mentioned ultrasonic cleaning process and the above-mentioned pressurized water cleaning process performed after the ultrasonic cleaning process are performed at least once.
- a process is performed (step S12).
- the water-soluble scale attached to the outer peripheral surface of the turbine blade 1 and the inner wall surface of the internal cooling flow passage 5 by ultrasonic cleaning can be favorably peeled off.
- the water-soluble scale which remained in the internal cooling flow path 5 can be removed more reliably by a pressurized water washing process. Therefore, it is possible to favorably remove the water-soluble scale attached to the turbine blade 1 by a simpler method before the turbine blade 1 is subjected to the heat treatment.
- the water-soluble scale may be removed from the turbine blade 1 using another method by chemical treatment and water washing treatment.
- the turbine blade 1 has a top coat layer (second coated layer) applied to the outside of the bond coat layer, and the top coat is performed before the residual stress removing step (step S13). It further has a top coat layer (second film layer) removing step (step S11) of removing the layer by blasting.
- a top coat layer (second film layer) removing step (step S11) of removing the layer by blasting removing the layer by blasting.
- the method for repairing a turbine blade according to an embodiment of the present invention is suitable for application to a turbine blade 1 having a top coat layer.
- any of the top coat layer removing step (step S11) and the deposit cleaning step (step S12) may be performed first as long as it is before the residual stress removing step (step S13).
- the repair method of the turbine blade of the present invention may be applied to a turbine blade having no top coat layer.
- the top coat layer removal process of step S11 from the protective layer removal process is omitted, the outer peripheral surface of the turbine blade can also be cleaned by the ultrasonic cleaning process in the deposit cleaning process of step S12. Therefore, if the deposit cleaning step is performed, it is possible to satisfactorily remove the water-soluble scale attached to the turbine blade having no top coat layer, including the wing portion.
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Abstract
Description
2 翼部
2T 翼頂
3 プラットフォーム
4 シャンク
5 内部冷却流路
10 保護層除去システム
11 ブラスト装置
12 超音波洗浄装置
13 加圧水洗浄装置
14 熱処理装置
15 ブラスト装置
16 洗浄装置
17 ブラスト装置
18 熱処理装置
Claims (8)
- 外表面に施された保護層としての第1被膜層と、冷媒を流通させる内部冷却流路とを有するタービン翼の補修方法であって、
前記第1被膜層を化学処理により除去する第1被膜層除去工程と、
前記第1被膜層除去工程の後に、前記タービン翼を清浄化するためのブラスト処理を行う清浄化工程と、
前記清浄化工程の後に、前記タービン翼を水槽に浸漬すると共に該水槽内に超音波を伝導させて該タービン翼を洗浄する超音波洗浄処理と、該超音波洗浄処理の後に前記内部冷却流路内に加圧水を噴射する加圧水洗浄処理と、を少なくとも一回行うブラスト粒洗浄工程と、を有することを特徴とするタービン翼の補修方法。 - 前記ブラスト粒洗浄工程の後に、前記タービン翼に前記第1被膜層が残留しているか否かを検査するための熱処理を行うヒートティント工程をさらに有することを特徴とする請求項1に記載のタービン翼の補修方法。
- 前記タービン翼は、動翼であり、
前記内部冷却流路は、前記タービン翼の翼頂および翼根で開口し、
前記加圧水洗浄処理は、前記翼頂の開口および前記翼根の開口の何れか一方から該内部冷却流路内に加圧水を噴射することを特徴とする請求項1または2に記載のタービン翼の補修方法。 - 前記加圧水洗浄処理は、長手方向が鉛直方向に沿うように前記タービン翼を支持した状態で、前記翼頂の開口および前記翼根の開口の鉛直方向上側に位置する一方から加圧水を噴射することを特徴とする請求項3に記載のタービン翼の補修方法。
- 前記ブラスト粒洗浄工程は、前回の前記加圧水洗浄処理に対して、前記タービン翼の鉛直方向上下が反対となるように支持方向を切り替えた上で、次回の前記加圧水洗浄処理を行うことを特徴とする請求項4に記載のタービン翼の補修方法。
- 前記ブラスト粒洗浄工程は、前記翼頂が鉛直方向上側になるように前記タービン翼を支持した状態で一回目の前記加圧水洗浄処理を行うことを特徴とする請求項4または5に記載のタービン翼の補修方法。
- 前記第1被膜層除去工程の前に、前記タービン翼に残留する応力が除去されるように熱処理を行う残留応力除去工程と、
前記残留応力除去工程の前に、前記超音波洗浄処理と、該超音波洗浄処理の後に行われる前記加圧水洗浄処理とを少なくとも一回行うスケール洗浄工程と、をさらに有することを特徴とする請求項1から6の何れか一項に記載のタービン翼の補修方法。 - 前記タービン翼は、前記第1被膜層の外側に施された第2被膜層を有し、
前記残留応力除去工程の前に、前記第2被膜層をブラスト処理により除去する第2被膜層除去工程をさらに有することを特徴とする請求項7に記載のタービン翼の補修方法。
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EP16881622.1A EP3315745B1 (en) | 2015-12-28 | 2016-12-13 | Turbine blade maintenance method |
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