WO2004113587A1 - 金属部品、タービン部品、ガスタービンエンジン、表面処理方法、及び蒸気タービンエンジン - Google Patents
金属部品、タービン部品、ガスタービンエンジン、表面処理方法、及び蒸気タービンエンジン Download PDFInfo
- Publication number
- WO2004113587A1 WO2004113587A1 PCT/JP2004/008130 JP2004008130W WO2004113587A1 WO 2004113587 A1 WO2004113587 A1 WO 2004113587A1 JP 2004008130 W JP2004008130 W JP 2004008130W WO 2004113587 A1 WO2004113587 A1 WO 2004113587A1
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- WO
- WIPO (PCT)
- Prior art keywords
- component
- electrode
- powder
- electrode material
- protective coat
- Prior art date
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
Definitions
- Metal parts, turbine parts, gas turbine engines, surface treatment methods, and steam turbine engines are Metal parts, turbine parts, gas turbine engines, surface treatment methods, and steam turbine engines
- the present invention relates to a metal component, a turbine component, a gas turbine engine, a surface treatment method, a metal component, and a steam turbine engine.
- Turbine blades used in gas turbine engines such as jet engines include a blade main body as a component main body.
- a surface treatment such as a wing surface of the wing in the wing main body is subjected to a surface treatment to ensure oxidation resistance.
- aluminizing treatment is performed on the to-be-processed portion of the wing body using a hydrogen furnace, so that aluminum is attached to the to-be-processed portion of the wing body. Further, the aluminum is diffused into the base material of the blade body by keeping the blade body and the attached aluminum at a high temperature by the hydrogen furnace or another heat treatment furnace. Thereby, an oxidation-resistant protective coat is formed on the processing target portion of the blade main body, so that the turbine blade can be finally manufactured.
- a first feature of the present invention is that a component main body; A protective coat having a chemical property, wherein the protective coat is any one of powders of aluminum powder, aluminum alloy powder, chromium powder, or chromium alloy powder, or two kinds thereof.
- the protective coat is any one of powders of aluminum powder, aluminum alloy powder, chromium powder, or chromium alloy powder, or two kinds thereof.
- the treated part of the component main body and the electrode are formed in an electrically insulating liquid or air.
- the discharge energy causes the electrode material of the electrode to adhere to the processed portion of the component main body, and further causes the processed portion of the component main body to adhere to the electrode portion.
- the electrode material thus formed is maintained at a high temperature to diffuse the adhered electrode material into the base material of the component main body, thereby forming the processed portion of the component main body.
- a second feature of the present invention is that the component body includes: a component main body; and a protection coat formed of SiC and formed of a SiC and having oxidation resistance.
- the protective coat uses an electrode composed of a solid body of Si, a molded body formed from Si powder, or a heat-treated molded body, and in an electrically insulating liquid containing alkane hydrocarbons, A pulse-like discharge is generated between the processing target portion of the component body and the electrode, and the discharge energy causes the electrode material of the electrode or a reactant of the electrode material to reach the processing target portion of the component body. It is formed by deposition, diffusion, and / or welding.
- FIG. 1 is a schematic view of a gas turbine engine according to an embodiment of the present invention.
- FIG. 2 (a) is a cross-sectional view taken along the line IIA-IIA in FIG. 2 (b), and FIG. 2 (b) is a side view of the turbine blade according to the first embodiment.
- FIG. 3 is a side view of the electric discharge machine according to the embodiment.
- FIG. 4 (a) and FIG. 4 (b) are diagrams for explaining a surface treatment method according to the first embodiment.
- FIG. 5 (a) and FIG. 5 (b) are diagrams illustrating a surface treatment method according to the first embodiment.
- FIG. 6 is a schematic diagram of a steam engine according to a second embodiment.
- FIG. 7 is a side view of a turbine blade according to a second embodiment.
- FIG. 8 is a view of FIG. 8 (b) as viewed from above, and FIG. 8 (b) is a diagram illustrating a surface treatment method according to the second embodiment.
- FIG. 9 (a) is a diagram of FIG. 9 (b) as viewed from above, and FIG. 9 (b) is a diagram illustrating a surface treatment method according to the second embodiment.
- FIG. 10 is a side view of a turbine blade according to a modification of the fifth embodiment.
- FF forward direction
- FR backward direction
- X-axis direction front-back direction
- lateral direction lateral direction
- vertical direction vertical direction
- a turbine blade 1 is one of turbine components used for a gas turbine engine 3 such as a jet engine, and has three shafts of a gas turbine engine. It is rotatable around the heart 3c.
- the turbine blade 1 includes a blade body 5 as a component body, and the blade body 5 includes a blade 7 and a blade 7 And a dovetail 11 formed on the platform 9.
- the platform 9 has a flow path surface 9f for the combustion gas, and the dovetail 11 can be fitted into a dovetail groove (not shown) of a turbine disk (not shown).
- the portion of the wing 7 extending from the leading edge 7a to the abdominal surface 7b, the back surface 7c, the tip surface 7t, and the flow path surface 9f of the platform 9 are portions to be processed of the wing body 5.
- a surface treatment is performed to ensure oxidation resistance.
- a protective coat 13 having a new configuration having oxidation resistance is formed, and the front side of the protective coat 13 is subjected to a peung treatment.
- FIG. 3 Before describing the novel surface treatment method according to the first embodiment, referring to FIG. 3, the surface of a part to be processed of the component body of the turbine component, such as the part to be processed of blade body 5, The discharge power dispenser 15 used for performing the treatment will be described.
- the electric discharge machine 15 includes a bed 17 extending in the X-axis direction and the Y-axis direction.
- the bed 17 is provided with a table 19, which can be moved in the X-axis direction by driving an X-axis servo motor (not shown), and is provided with a Y-axis servo motor (not shown). It can be moved in the Y-axis direction by driving.
- the table 19 is provided with a processing tank 21 for storing an electrically insulating liquid S containing an alkane hydrocarbon such as oil, and a support plate 23 is provided in the processing tank 21. ing.
- the support plate 23 is provided with a jig 25 such as the wing main body 5 on which the component main bodies can be set.
- the jig 25 is electrically connected to a power supply 27. Note that the attitude of the component main body with respect to the jig 25 can be changed, and FIG. 3 shows a state in which the wing main body 5 is set so that the tip surface 7t of the wing 7 faces upward.
- a processing head 29 is provided via a column (not shown).
- the processing head 29 can be moved in the Z-axis direction by driving a Z-axis servomotor (not shown). It is.
- the processing head 29 is provided with a holding member 37 for holding electrodes 31. 33. 35 and the like described later, and the holding member 37 is electrically connected to the power supply 27.
- the surface treatment method according to the first embodiment includes an adhesion step, a diffusion step, and a peening step as follows.
- the wing body 5 is set on the jig 25 so that the holding member 37 holds the electrode 31 and the abdominal surface 7b of the wing 7 faces upward.
- the electrode 31 and the portion extending from the leading edge 7a to the abdominal surface 7b of the wing 7 are formed.
- Position the wing body 5 so that it faces each other. Move table 19 in either the X-axis direction or the Y-axis direction. In some cases, just moving them is enough.
- the electrode 31 is located between the electrode 31 and the portion extending from 7a to the ventral surface 7b, and between the ventral part of the flow surface 9f of the platform 9 (the platform 9 is omitted in FIG. 4 (a)). A nores-like discharge is generated. Thereby, the electrode material M of the electrode 31 can be adhered to the leading edge 7a of the blade 7 and the portion extending over the ventral surface 7b and the ventral portion of the flow path surface 9f of the platform 9 by the discharge energy.
- the electrode 31 is formed of a compact formed by compression from a powder of aluminum or aluminum alloy by pressing, or a compact formed by heat treatment in a vacuum furnace or the like.
- the electrode 31 may be formed by plasma, MIM (Metal Injection Molding), thermal spraying or the like instead of being formed by compression.
- the tip of the electrode 31 has a shape approximating a portion extending from the leading edge 7a of the blade 7 to the abdominal surface 7b.
- the electrode 31 is detached from the holding member 37, the electrode 33 is held by the holding member 37, and the wing body is positioned so that the back surface 7c of the wing 7 faces upward.
- the table 19 is moved in the X-axis direction and the Y-axis direction by the drive of the X-axis servo motor and the Y-axis servo motor, so that the back surface 7c of the blade 7 and the electrode 33 face each other. Perform 5 positioning. In some cases, it is sufficient to simply move the table 19 in one of the X-axis direction and the Y-axis direction.
- the space between the back surface 7c of the wing 7 and the electrode 33 and the back side of the flow path surface 9f of the platform 9 (the platform 9 is omitted in FIG. 4 (b)).
- the electrode 33 to generate a pulsed discharge.
- the electrode material M of the electrode 33 can be attached to the back surface 7c of the wing 7 and the back side of the flow path surface 9f of the platform 9 by the discharge energy.
- the electrode 33 is formed by molding a powder of aluminum or aluminum alloy by compression by pressing, or the above-mentioned heat-treated by a vacuum furnace or the like. It is constituted by a molded body.
- the electrode 33 is not formed by compression, but is formed by slurry, MIM (Metal Injection Molding), thermal spraying, etc. No problem.
- the tip of the electrode 33 has a shape similar to the back surface 7c of the wing 7.
- the electrode 33 After the electrode material M of the electrode 33 is attached, the electrode 33 is detached from the holding member 37, the electrode 35 is held by the holding member 37, and the wing 7 is turned so that the tip end surface 7t faces upward.
- the table 19 is moved in the X-axis direction and the Y-axis direction by driving the X-axis servo motor and the Y-axis servo motor, so that the tip surface 7t of the blade 7 and the electrode 35 face each other. Position the main unit 5. In some cases, it is sufficient to move the table 19 in any one of the X-axis direction and the Y-axis direction.
- a pulse-like discharge is generated between the tip surface 7t of the blade 7 and the electrode 35.
- the electrode material M of the electrode 35 can be attached to the tip end surface 7t of the blade 7 by the discharge energy.
- the electrode 35 is formed from a powder of aluminum or aluminum alloy by pressing with a press, or the former is heat-treated with a vacuum furnace or the like. It is composed of the body.
- the electrode 35 may be formed by slurry, MIM (Metal Injection Molding), thermal spraying, or the like instead of being formed by compression.
- the tip of the electrode 35 has a shape similar to the shape of the tip surface 7t of the blade 7.
- the electrodes 31.33.35 are reciprocated in the Z-axis direction by a small amount by the driving of the Z-axis servomotor integrally with the machining head 29.
- a pulsed discharge may be generated in the electrically insulating air.
- the wing body 5 is removed from the jig 25 and set at a predetermined position of the heat treatment furnace 39 as shown in FIG. Then, the wing body 5 and the attached electrode material M are maintained at a high temperature of 950 ° C. and 1100 ° C. by the heat treatment furnace 39. As a result, the adhered electrode material M is diffused into the base material of the wing main body 5, and the protective coat 13 made of nickel metal intermetallic compound can be formed. (III) Peening step
- the wing body 5 is removed from the jig 25 and set at a predetermined position of a peening device (not shown). Then, a peening process is performed on the front side of the protection coat 13 by the peunging apparatus.
- the specific aspect of the pe-jung processing is shot pe-jung processing using shots (for example, see JP-A-2001-170866, JP-A-2001-260027, JP-A-2000-225567, etc.), laser There is a laser jungling process using light (for example, see JP-A-2002-236112, JP-A-2002-239759, etc.).
- the electrode material M can be attached to the front surface 7b, the back surface 7c, the tip surface 7t, and the flow path surface 9f of the platform 9 from the leading edge 7a of the wing 7 by the discharge energy.
- the range can be limited to the range in which discharge occurs, and masking processing and processing accompanying the masking processing can be omitted. Note that the processing accompanying the masking processing includes blast processing, mask removal processing, and the like.
- the range of adhesion of the electrode material M can be limited to the range in which electric discharge occurs, so that the number of steps required for manufacturing the turbine blade 3 can be reduced.
- the attached electrode material M is added to the base material of the wing body 5 in the diffusion step ( ⁇ ). It can be spread early. Therefore, the production time of the turbine blade 1 can be shortened, and the productivity of the turbine blade 1 can be easily improved.
- the present invention is not limited to the description of the embodiment of the first embodiment. As described above, the present invention can be implemented in various modes.
- a compact formed by pressing a chromium powder or a chromium alloy powder by pressing instead of using an electrode 31. 33. 35 made of a compact or the like obtained by compression-molding an aluminum powder or an aluminum alloy powder, a compact formed by pressing a chromium powder or a chromium alloy powder by pressing.
- Another oxidation-resistant protective coat may be formed by using another electrode composed of the body or the molded body that has been heat-treated by a vacuum furnace or the like. In this case, the other protective coat is particularly resistant to corrosion due to collision of foreign matter or the like, in other words, the erosion resistance is particularly improved.
- the present invention is not limited to turbine components such as the turbine blade 1, and can be applied to various metal components.
- a turbine blade 41 according to the second embodiment is one of the blade components used in the gas turbine engine 3 or the steam turbine engine 43, and is a gas turbine engine. It is rotatable around the axis 3c of 3 or the axis 43c of the steam turbine engine 43.
- a turbine blade 41 according to the second embodiment has a blade body 45 as a component body, and the blade body 45 is a turbine blade according to the first embodiment.
- the wing 7 includes a wing 7, a platform 9, and a dovetail 11. The portion extending from the leading edge 7a of the wing 7 to the abdominal surface 7b, the back surface 7c of the wing 7, and the flow surface 9f of the platform 9 are portions to be processed of the wing body 45.
- the portion extending across the abdominal surface 7 b, the back surface 7 c of the wing 7, and the flow surface 9 f of the platform 9 are provided with an oxidation-resistant hard protective coating 47 of a new configuration. Are formed by the discharge energy, and the front side of the protective coat 47 is subjected to a peyung treatment. Note that the protective coat 47 is made of SiC.
- the protective coat 47 uses the electric discharge machine 15 according to the embodiment shown in FIG. 3 and the electrode 49 shown in FIGS. 8A and 8B and contains an alkane hydrocarbon.
- the electrically insulating liquid S there is no contact between the electrode 49 and the portion from the leading edge 7a to the ventral surface 7b of the wing 7 and the ventral portion of the flow surface 9f of the platform 9 and the electrode 49.
- a discharge in the form of a pulse is generated, and the discharge energy causes the electrode material of the electrode 49 or the reactant of the electrode material to flow between the front edge 7a of the blade 7 and the abdominal surface 7b and the channel surface 9f of the platform 9. It is formed by depositing, diffusing, and Z or welding on the ventral part.
- the electrode 49 is formed of a solid body of Si, a compact formed by compressing a Si powder by pressing, or a compact formed by heat treatment in a vacuum furnace or the like.
- the electrode 49 may be formed by slurry, MIM (Metal Injection Molding), thermal spraying or the like instead of being formed by compression.
- the tip of the electrode 49 has a shape similar to the shape of a portion extending from the leading edge 7a of the blade 7 to the abdominal surface 7b.
- deposition, diffusion, and / or welding refers to “deposition,” “diffusion,” “welding,” “a mixed phenomenon of deposition and diffusion,” and “a mixed phenomenon of deposition and welding. ",” A mixed phenomenon of diffusion and welding ", and” a mixed phenomenon of deposition, diffusion and welding ".
- the remaining portion of the protective coat 47 uses the electric discharge machine 15 according to the embodiment shown in Fig. 3 and the electrode 51 shown in Figs. 9 (a) and 9 (b).
- a pulse-like discharge is generated between the back surface 7c of the blade 7 and the electrode 49, and between the back side of the flow surface 9f of the platform 9 and the electrode 49, respectively.
- the electrode material of the electrode 51 or a reactant of the electrode material is deposited, diffused, and / or deposited on the back surface 7c of the wing 7 and the back surface of the flow path surface 9f of the platform 9 by the discharger energy. Is formed by
- the electrode 51 is formed of a solid body of Si, a molded body formed by compressing a Si powder by pressing, or the above-mentioned molded body that has been heat-treated in a vacuum furnace or the like.
- the electrode 51 may be formed by slurry, MIM (Metal Injection Molding), thermal spraying or the like instead of being formed by compression.
- the tip of the electrode 51 has a shape similar to the back surface 7c of the wing 7.
- the front side of the protective coat 47 may It has been subjected.
- the peening process include a shot peening process using a shot and a laser peening process using a laser beam.
- the range of the protective coat 47 can be limited to a range in which a discharge occurs, and a masking process and a process accompanying the masking process can be omitted. .
- the boundary portion B between the protective coat 47 formed by the discharge energy and the base material of the wing body 45 has a structure in which the composition ratio is inclined. 45 base materials can be firmly bonded.
- the range of the protective coat 47 can be limited to the range in which electric discharge occurs, and the masking process and the processes accompanying the masking process can be omitted.
- the number of steps required for manufacturing the wing 41 can be reduced. Therefore, the production time of the turbine blade 41 can be shortened, and the productivity of the turbine blade 41 can be easily improved.
- the protective coat 47 and the base material of the wing body 45 can be firmly bonded, the protective coat 47 does not easily separate from the base material of the wing body 45, and the quality of the turbine blade 41 is stabilized.
- the present invention is not limited to the description of the second embodiment described above.
- Appropriate changes can be made, for example, by performing a surface treatment based on the new surface treatment method according to the second embodiment on the portion to be treated.
- a turbine blade 53 according to a modification of the second embodiment is used for a gas turbine engine 3 or a steam turbine engine 43, like the turbine blade 41. It is one of the blade components, and is rotatable around the axis 3c of the gas turbine engine 3 or the axis 41c of the steam turbine engine 43.
- a turbine blade 53 includes a blade main body 55 as a component main body. It consists of a platform 9, a dovetail 11, and a shroud 57 formed at the tip of the wing 7.
- the shroud 57 has a flow path surface 57f for the combustion gas.
- the portion extending from the leading edge 7a of the wing 7 to the abdominal surface 7b, the back surface 7c of the wing 7, the flow surface 9f of the platform 9, and the flow surface 57f of the shroud 57 are processed portions of the wing body 57. .
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/560,360 US20070104585A1 (en) | 2003-06-10 | 2004-06-10 | Metal component, turbine component, gas turbine engine, surface processing method, and steam turbine engine |
JP2005507203A JP4505415B2 (ja) | 2003-06-10 | 2004-06-10 | 金属部品、タービン部品、ガスタービンエンジン、表面処理方法、及び蒸気タービンエンジン |
US12/904,327 US20110027099A1 (en) | 2003-06-10 | 2010-10-14 | Metal component, turbine component, gas turbine engine, surface processing method, and steam turbine engine |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2003165403 | 2003-06-10 | ||
JP2003-165403 | 2003-06-10 | ||
JP2004029970 | 2004-02-05 | ||
JP2004-029970 | 2004-02-05 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/904,327 Division US20110027099A1 (en) | 2003-06-10 | 2010-10-14 | Metal component, turbine component, gas turbine engine, surface processing method, and steam turbine engine |
Publications (2)
Publication Number | Publication Date |
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WO2004113587A1 true WO2004113587A1 (ja) | 2004-12-29 |
WO2004113587A9 WO2004113587A9 (ja) | 2005-07-14 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/JP2004/008130 WO2004113587A1 (ja) | 2003-06-10 | 2004-06-10 | 金属部品、タービン部品、ガスタービンエンジン、表面処理方法、及び蒸気タービンエンジン |
Country Status (4)
Country | Link |
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US (2) | US20070104585A1 (ja) |
JP (1) | JP4505415B2 (ja) |
TW (1) | TWI270427B (ja) |
WO (1) | WO2004113587A1 (ja) |
Cited By (3)
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JP2007051635A (ja) * | 2005-06-30 | 2007-03-01 | General Electric Co <Ge> | ニオブシリサイド基タービン構成部品および関連するレーザ付着方法 |
WO2008120648A1 (ja) | 2007-03-30 | 2008-10-09 | Ihi Corporation | 放電表面処理方法及び修理方法 |
JP2011102562A (ja) * | 2009-11-11 | 2011-05-26 | Mitsubishi Electric Corp | 機械部品の補修方法 |
Families Citing this family (9)
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WO2004029329A1 (ja) | 2002-09-24 | 2004-04-08 | Ishikawajima-Harima Heavy Industries Co., Ltd. | 高温部材の擦動面のコーティング方法および高温部材と放電表面処理用電極 |
US9284647B2 (en) * | 2002-09-24 | 2016-03-15 | Mitsubishi Denki Kabushiki Kaisha | Method for coating sliding surface of high-temperature member, high-temperature member and electrode for electro-discharge surface treatment |
WO2004033755A1 (ja) * | 2002-10-09 | 2004-04-22 | Ishikawajima-Harima Heavy Industries Co., Ltd. | 回転体及びそのコーティング方法 |
EP1873276B1 (en) * | 2005-03-09 | 2016-12-21 | IHI Corporation | Surface treatment method and repair method |
US7237730B2 (en) * | 2005-03-17 | 2007-07-03 | Pratt & Whitney Canada Corp. | Modular fuel nozzle and method of making |
US20100119864A1 (en) * | 2007-03-26 | 2010-05-13 | Ihi Corporation | Heat-resistant component |
US8316541B2 (en) * | 2007-06-29 | 2012-11-27 | Pratt & Whitney Canada Corp. | Combustor heat shield with integrated louver and method of manufacturing the same |
DE112009005100T5 (de) | 2009-07-28 | 2012-09-13 | Mitsubishi Electric Corporation | Erosionsresistente Maschinenkomponente, Verfahren zur Bildungeiner Oberflächenschicht einer Maschinenkomponente und Verfahrenzur Herstellung einer Dampfturbine |
JP5555727B2 (ja) | 2012-01-23 | 2014-07-23 | 川崎重工業株式会社 | 軸流圧縮機翼の製造方法 |
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2004
- 2004-06-10 US US10/560,360 patent/US20070104585A1/en not_active Abandoned
- 2004-06-10 TW TW093116853A patent/TWI270427B/zh not_active IP Right Cessation
- 2004-06-10 WO PCT/JP2004/008130 patent/WO2004113587A1/ja active Application Filing
- 2004-06-10 JP JP2005507203A patent/JP4505415B2/ja not_active Expired - Fee Related
-
2010
- 2010-10-14 US US12/904,327 patent/US20110027099A1/en not_active Abandoned
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JPS62177179A (ja) * | 1986-01-31 | 1987-08-04 | Toshiba Corp | 蒸気タ−ビン動翼 |
JPH05148615A (ja) * | 1991-11-18 | 1993-06-15 | Res Dev Corp Of Japan | 金属材料の表面処理方法 |
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007051635A (ja) * | 2005-06-30 | 2007-03-01 | General Electric Co <Ge> | ニオブシリサイド基タービン構成部品および関連するレーザ付着方法 |
WO2008120648A1 (ja) | 2007-03-30 | 2008-10-09 | Ihi Corporation | 放電表面処理方法及び修理方法 |
JP2011102562A (ja) * | 2009-11-11 | 2011-05-26 | Mitsubishi Electric Corp | 機械部品の補修方法 |
Also Published As
Publication number | Publication date |
---|---|
TWI270427B (en) | 2007-01-11 |
JP4505415B2 (ja) | 2010-07-21 |
TW200510100A (en) | 2005-03-16 |
JPWO2004113587A1 (ja) | 2006-08-03 |
US20110027099A1 (en) | 2011-02-03 |
US20070104585A1 (en) | 2007-05-10 |
WO2004113587A9 (ja) | 2005-07-14 |
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