WO2005068670A1 - Piece de moteur, piece de temperature elevee, procede de traitement surfacique, moteur a turbine a gaz, structure de prevention de grippage, et procede de production d'une telle structure - Google Patents

Piece de moteur, piece de temperature elevee, procede de traitement surfacique, moteur a turbine a gaz, structure de prevention de grippage, et procede de production d'une telle structure Download PDF

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Publication number
WO2005068670A1
WO2005068670A1 PCT/JP2005/000393 JP2005000393W WO2005068670A1 WO 2005068670 A1 WO2005068670 A1 WO 2005068670A1 JP 2005000393 W JP2005000393 W JP 2005000393W WO 2005068670 A1 WO2005068670 A1 WO 2005068670A1
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WO
WIPO (PCT)
Prior art keywords
sliding side
component
electrode
powder
discharge
Prior art date
Application number
PCT/JP2005/000393
Other languages
English (en)
Japanese (ja)
Inventor
Hiroyuki Ochiai
Mitsutoshi Watanabe
Takashi Furukawa
Yoshiyuki Saitou
Akihiro Goto
Masao Akiyoshi
Original Assignee
Ishikawajima-Harima Heavy Industries Co., Ltd.
Mitsubishi Denki Kabushiki Kaisha
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ishikawajima-Harima Heavy Industries Co., Ltd., Mitsubishi Denki Kabushiki Kaisha filed Critical Ishikawajima-Harima Heavy Industries Co., Ltd.
Publication of WO2005068670A1 publication Critical patent/WO2005068670A1/fr

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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
    • 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
    • C23C26/02—Coating not provided for in groups C23C2/00 - C23C24/00 applying molten material to the substrate
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
    • B22F2003/1051—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding by electric discharge
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy

Definitions

  • the present invention relates to an engine component, a high-temperature component, a surface treatment method, a gas turbine engine, a galling preventing structure, and a method for manufacturing an galling preventing structure.
  • Turbine blades used in a gas turbine engine such as a jet engine have a frictional relationship with an adjacent counterpart turbine blade, and a friction between the counterpart turbine blade in the blade body of the turbine blade.
  • a wear-resistant protective coat is formed on the moving side.
  • the protective coating is formed by spraying a powder of a Co-Cr (cobalt 'chromium) alloy as a thermal spray material on the rubbing side of the rotor blade body. Thereby, abrasion on the rubbing side of the blade body can be suppressed.
  • the gas turbine engine has, for example, a wrinkle prevention structure for preventing wrinkles between a dovetail of a compression moving blade and a fitting groove of a compressor disk in a sliding relationship.
  • a porous protective coat is formed on a side of the dovetail that rubs against the fitting groove of the compression disk.
  • the protective coat Ni-Cu-I n alloy, Cu- Ni alloy, Cu- A1- using soft alloy such as F e alloy as spray material, those formed by spraying the soft quality alloy It is.
  • the microporous portion of the protective coat is filled with a solid lubricant containing MoS2 as a main component by brush coating or the like.
  • the protective coat of the turbine rotor blade and the protection coat of the galling prevention structure are formed by thermal spraying, in the manufacture of the turbine rotor blade and the galling prevention structure, blasting is performed. Processing, pasting of masking tape, etc.
  • a post-treatment for forming the protective coat such as a pre-treatment for forming the protective coat and a masking tape removing treatment, is required. Therefore, the number of steps required for manufacturing the turbine rotor blades increases, and the manufacturing operation of the turbine rotor blades becomes complicated. In addition, the number of steps required for manufacturing the anti-galling structure increases, and the force There is a problem that the manufacturing work of the prevention structure becomes complicated.
  • a first feature of the present invention is an engine component used for a gas turbine engine, which comprises: a component main body; and a mating engine component in the component main body.
  • the electrode is placed between the sliding side or sliding side of the component body and the electrode. A loose discharge is generated, and the discharge energy is used to cause the material of the electrode or a reactant of the material to be deposited on the sliding side or the sliding side of the component body. is there.
  • a second feature of the present invention is a high-temperature component having mechanical strength in a high-temperature environment, and includes a component main body and a sliding side or sliding side of the component main body with a mating high-temperature component. And a wear-resistant protective coat; wherein the protective coat is formed from a powder mainly composed of a Ti (titanium) -based material or formed by heating.
  • a pulsed discharge is generated between the sliding side or sliding side of the component body and the electrode in an electrically insulating liquid or air, using the electrode composed of It is formed by welding the material of the electrode or a reactant of the material to the sliding side or the sliding side of the component body by energy.
  • a third feature of the present invention is a surface treatment method for securing abrasion resistance on a sliding side or a sliding side of an engine component used in a gas turbine engine with a mating engine component.
  • a pulse-like discharge is generated between the sliding side or the sliding side of the component main body and the electrode, and the discharge energy is used to generate the pulse-like discharge.
  • a wear-resistant protective coat is formed on the sliding side or sliding side of the component body. That is.
  • a fourth feature of the present invention is that a wear resistance is ensured on a sliding side or sliding side of a component body of a high-temperature component having mechanical strength in a high-temperature environment with a mating engine component.
  • Surface treatment method using a molded body molded from a powder mainly composed of Ti (titanium) -based material or an electrode constituted by the heat-treated molded body, and using an electrode having electrical insulation properties.
  • a noisy discharge is generated between the sliding or sliding side of the component body and the electrode, and the discharge energy causes the sliding side or the sliding of the component body.
  • the material of the electrode or the reactant of the material is welded to the moving side to form a wear-resistant protective coat on the sliding side or sliding side of the component body.
  • a fifth feature of the present invention is a squeezing prevention structure for preventing squeezing between a pair of metal components in a sliding relationship or a sliding relationship, wherein And a porous protective coat formed on the rubbing side or the rubbing side of at least one of the metal parts; and a lubricant filled in micropores in the protective coat.
  • a molded body molded from a metal powder or an electrode formed of the molded body subjected to heat treatment the sliding side or sliding of the one metal part is performed in an electrically insulating liquid or air.
  • a pulsed discharge is generated between the electrode and the electrode, and the discharge energy causes the material of the electrode or a reactant of the material to be welded to the sliding side or the sliding side of the one metal part. Formed by It is a
  • FIG. 1 is a schematic diagram of a gas turbine engine according to an embodiment.
  • FIG. 2 is a perspective view of a turbine rotor blade according to the first embodiment.
  • FIGS. 3 (a) and 3 (b) are schematic diagrams illustrating a process of forming a protective coat according to the first embodiment
  • FIG. 3 (c) is a diagram illustrating the process of the first embodiment
  • FIG. 2 is a schematic diagram illustrating a configuration of a protective coat according to the present invention
  • FIG. 4 is a diagram showing a relationship between the thickness of a fusion portion and the adhesion strength of a coat when a coat is formed on a metal base material by discharge energy.
  • FIG. 5 is a diagram showing a relationship between the thickness of a fusion portion and deformation of a base material when a coat is formed on a metal base material by discharge energy.
  • FIG. 6 is a schematic front view of the electric discharge machine according to the embodiment.
  • FIG. 7 is a graph showing a wear test result of the protective coat according to the first embodiment.
  • FIG. 8 is a perspective view of a turbine bucket according to a second embodiment.
  • FIGS. 9 (a) and 9 (b) are schematic diagrams illustrating a process of forming a protective coat according to a second embodiment.
  • FIG. 10 is a graph showing a wear test result of a protective coat according to the second embodiment.
  • FIG. 11 is a schematic view of a squeezing prevention structure according to a third embodiment.
  • FIG. 12 is a diagram illustrating a process of forming a protective coat according to a third embodiment by using an electric discharge machine.
  • FIG. 13 (a) is a view showing a state in which a protective coat according to a third embodiment is formed
  • FIG. 13 (b) is a diagram showing a fine structure of the protective coat according to the third embodiment
  • FIG. 4 is a view showing a state in which a high-temperature lubricant is filled in a hole portion.
  • FF forward direction
  • FR backward direction
  • front-back direction is appropriately referred to as an X-axis direction
  • lateral direction is referred to as a Y-axis direction
  • up-down direction is referred to as a Z-axis direction.
  • FIG. 1 A turbine blade 1 according to the first embodiment will be described with reference to FIGS. 1, 2, and 3.
  • FIG. 1 A turbine blade 1 according to the first embodiment will be described with reference to FIGS. 1, 2, and 3.
  • a turbine bucket 1 is one of engine parts used for a gas turbine engine 3 such as a jet engine, and It is rotatable about the axis of the turbine engine.
  • the turbine rotor blade 1 includes a rotor blade body 5 as a component body, and the rotor blade body 5 includes Ni (nickel) containing Cr (chromium). It is composed of an alloy or a Co (cobalt) alloy.
  • the rotor blade body 5 includes a blade 7, a platform 9 integrally formed on the base end side of the blade 7, and a fitting groove (not shown) formed integrally with the platform 9 and formed on the turbine disk. It has a dovetail 11 that can be fitted and a shroud 13 integrally formed on the tip side of the wing 7.
  • the platform 9 has an inner single flow path surface 9p that defines a part of the flow path of the combustion gas
  • the shroud 13 similarly has an outer surface that defines a part of the flow path of the combustion gas. It has a channel surface 13p.
  • the shroud 13 has a seal fin 15 that allows contact with a stationary cam component (not shown), which is one of the engine components.
  • the shroud 13 of the turbine rotor blade 1 has a frictional relationship with the shroud 13 of the partner turbine rotor blade 1 'as a partner engine part, and the shroud 13 has a frictional relationship with the partner turbine rotor blade 1'.
  • a wear-resistant protective coat 17 is formed on the side 13s.
  • the protective coat 17 uses an electrode 19 as shown in FIGS. 3 (a) and 3 (b).
  • the sliding side 13s of the shroud 13 and the electrode 19 are connected. It is formed by generating a pulse-like discharge between the electrodes and welding the material of the electrode 19 or a reactant of the material to the sliding side 13s of the shroud 13 by the discharge energy.
  • the thickness of the protective coat 17 is not less than 0.01 mm and not more than 0.02 mm.
  • the electrode 19 is formed of a compact formed by pressing a powder containing a Ti (titanium) -based material as a main component by pressing, or a compact formed by heat treatment, and is formed of a shroud. 13 has a shape similar to the sliding side 13s.
  • the Ti-based materials include, in addition to TiC (titanium carbide), materials such as Ti (titanium) and TiH2 (titanium hydride) that are carbonized by discharge to become TiC.
  • welding includes welding together with diffusion, welding together with deposition, and welding together with deposition and diffusion.
  • the electrode 19 may be formed by slurry, MIM (Metal Injection Molding), thermal spraying or the like instead of being formed by compression.
  • MIM Metal Injection Molding
  • FIG. 3 (c) when the protective coat 17 is placed in an oxidizing atmosphere A at a temperature of 600 ° C. or more by the operation of the gas turbine engine 3, the protective coat 17 While leaving the hard layer 21 made of TiC (titanium carbide) on the side 13s, the surface of the hard layer 21 is oxidized from TiC in the hard layer 21 and Cr in the shroud 13 to Ti02 (titanium oxide), respectively. An extremely thin lubricating layer 23 containing Cr203 (oxidized chromium) is formed.
  • a fusion portion (fusion layer) B1 whose composition ratio changes in a gradient direction in the thickness direction is generated.
  • the fusion portion B1 is configured to have a thickness of 3 ⁇ m or more and 20 m or less.
  • the appropriate discharge conditions are a peak current of 30 A or less and a pulse width of 200 s or less, preferably, a peak current of 20 A or less and a pulse width of 20 ⁇ s or less.
  • the reason why the thickness of the fusion portion B1 is set to 3 m or more and 20 m or less is based on the test results shown in FIGS. 4 and 5.
  • the thickness of the fused portion generated at the boundary between the base material and the core and the adhesion of the coat was as shown in FIG. 5, and it was possible to obtain a new first finding that, when the thickness of the fused portion was 3 m or more, the adhesion strength of the coat was increased. Further, the relationship between the thickness of the fusion zone and the deformation of the base material is as shown in FIG. 6, and it is said that if the thickness of the fusion zone is 20 m or less, the deformation of the base material can be suppressed. Thus, a new second finding was obtained.
  • the thickness of the fusion portion B1 is set to 3 ⁇ m so that the deformation of the base material of the rotor blade body 5 can be suppressed and the adhesion strength of the protective coat 17 can be increased. It was set to be not less than 20 ⁇ m.
  • the horizontal axis in FIGS. 4 and 5 shows the thickness of the fused portion in logarithmic scale, and the vertical axis in FIG. 4 shows the adhesion strength of the coat in a dimensionless manner.
  • the vertical axis in FIG. 5 shows the deformation of the base material in a non-dimensional manner.
  • the electric discharge machine 25 includes a bed 27 extending in the X-axis direction and the Y-axis direction.
  • the bed 27 is provided with a column 29 extending in the Z-axis direction.
  • the bed 27 is provided with a table 31 which can be moved in the axial direction by driving an X-axis servomotor 33, and which can be moved in the Y-axis direction by driving a Y-axis servomotor 35. It is possible to move to.
  • the table 31 is provided with a processing tank 37 for storing the electrically insulating liquid L, and a support plate 39 is provided in the processing tank 37.
  • the support plate 39 is provided with a jig 41 on which the turbine blade 1 and the like can be set.
  • the jig 41 is electrically connected to the power supply 43 via the support plate 39 and the like.
  • the column 29 is provided with a processing head 45, which can be moved in the Z-axis direction by driving a Z-axis servo motor 47. Further, a holder 49 for holding the electrode 19 and the like is provided on the caroe head 45. The holder 49 is electrically connected to the power supply 43.
  • FIGS. 3 (a), 3 (b) and 6 a first embodiment for securing wear resistance on the sliding side 13s of the shroud 13 of the turbine blade 1 will be described.
  • the surface treatment method will be described.
  • the blade main body 5 is set on the jig 41 so that the rubbing side 13s of the shroud 13 faces upward.
  • the rotor blade body 5 is positioned so that the electrode 19 and the electrode 19 face each other. In some cases, it is sufficient to move the table 31 only in one of the X-axis direction and the Y-axis direction.
  • the hard layer 21 remains on the rubbing side 13 s of the shroud 13 while the hard layer 21 remains.
  • the lubricating layer 23 is formed on the front side of the hard layer 21, in other words, the lubricating layer 23 is formed with the hard layer 21 as a base.
  • the wear resistance of the coat 17 can be sufficiently increased.
  • the protective coat 17 When the protective coat 17 is placed in an atmosphere A at a temperature of 600 ° C or higher, the surface of the protective coat 17 becomes smooth due to friction with the shroud 13 of another turbine blade 1 ′, and the protective coat 17 The local surface pressure of the protective coat 17 is reduced, and the wear resistance of the protective coat 17 can be further increased.
  • the protective coat 17 can be used not only in an oxidizing atmosphere of 500 ° C or more but also in an oxidizing atmosphere of 300 ° C and 600 ° C. Sufficient lubrication can be achieved. As a result, even if the protective coat 17 is placed in an oxidizing atmosphere that changes over a wide temperature range of, for example, 300 ° C to 950 ° C, the protective coat 17 is protected as shown in the results of the wear resistance test of the protective coat shown in Fig. 7. The coat 17 can maintain sufficient abrasion resistance continuously. By setting the weight mixing ratio of Ti02 and Cr203 contained in the lubricating layer 23 to be 5:95, the protective coat 17 can maintain extremely sufficient wear resistance continuously.
  • the abrasion resistance test of the protective coat is performed under a predetermined test condition (load at normal temperature: 5 MPa, load at 480 ° C. or more: 7 MPa, cycle number: 106, amplitude: ⁇ 0. 5 mm),
  • the invention in FIG. 7 is a test article on which a protective coat 17 is formed
  • the comparative article in FIG. 7 is a Co--Cr alloy This is a test specimen in which the standard wear resistance was formed by welding.
  • the protective coat 17 is formed by the discharge energy, the range of the protective coat 17 can be limited to a range in which the discharge occurs, and in the production of the turbine rotor blade 1, the protective coat 17 is formed.
  • the accompanying pre-treatment and the post-treatment accompanying the formation of the protective coat 17 can be omitted.
  • the fusion portion B1 is configured to have a thickness of 3 m or more and 20 m or less. In other words, since the proper discharge conditions are selected when forming the protective coat 17, the adhesion strength of the protective coat 17 can be increased while suppressing the deformation of the base material of the rotor blade body 5. .
  • the lubricating action of the lubricating layer 23 and the protecting action of the hard layer 21 are exhibited, and the wear resistance of the protective coat 17 can be sufficiently increased.
  • the wear on the rubbing side 13s of the shroud 13 due to rubbing with the counterpart turbine blade 1 can be sufficiently suppressed, and the life of the turbine blade 1 can be extended.
  • the protective coat 17 is placed in an oxidizing atmosphere that changes over a wide temperature range of, for example, 300 ° C to 950 ° C, the protective coat 17 must maintain sufficient abrasion resistance. Therefore, the life of the turbine blade 1 can be extended.
  • a pretreatment for forming the protective coat 17 and a post-treatment for forming the protective coat 17 can be omitted; The number of steps required for the production of 1 can be reduced, and the efficiency of the turbine rotor blade production operation can be improved.
  • the adhesion strength of the protective coat 17 can be increased while suppressing deformation of the base material of the rotor blade body 5, it is possible to sufficiently withstand fretting due to vibration of the gas turbine engine 3. As a result, the quality of the turbine blade 1 is stabilized.
  • the present invention is not limited to the description of the first embodiment.
  • the embodiment may be changed as follows.
  • a pulse-like discharge may be generated in the air having electric insulation instead of the liquid L having electric insulation.
  • a protective coat having the same configuration as the protective coat may be formed by discharge energy on the sliding side or sliding side of the engine component other than the turbine rotor blade with the mating engine component.
  • a protective coat having the same configuration as that of the protective coat is formed by discharge energy on the sliding side or sliding side of the high-temperature component other than the engine component, such as an impeller used in the turbocharger, with the other high-temperature component in the component body. You can do it.
  • FIGS. 1, 4, 8, and 9 a turbine rotor blade 51 according to the second embodiment will be described. Will be explained.
  • a turbine blade 51 according to the second embodiment is one of the engine components used in the gas turbine engine 3 and includes a blade main body 53 as a component body. ing.
  • the moving blade body 53 includes a blade 7, a platform 9, a dovetail 11, and a shroud 13, similarly to the moving blade body 5 of the turbine moving blade 1 according to the first embodiment.
  • the shroud 13 of the turbine rotor blade 51 has a frictional relationship with the shroud 13 of the partner turbine rotor blade 51 ′ as the partner engine component, and the shroud 13 slides with the partner turbine rotor blade 51 ′.
  • a wear-resistant protective coat 55 is formed on the side 13s. Then, the protective coat 55 uses an electrode 57 as shown in FIGS. 9 (a) and 9 (b), and in the electrically insulating liquid L such as oil, the sliding side 13s of the shroud 13 and the electrode 57 A discharge in the form of a pulse is generated during this time, and the material of the electrode 57 or a reactant of the material is welded to the sliding side 13s of the shroud 13 by the discharge energy. Note that the thickness of the protective coat 55 is from 0.05 mm to 0.5 mm.
  • the electrode 57 is made of a Co—Cr (cobalt-chromium) alloy powder as a main component, a Cr203 (chromium oxide) powder, a Ti02 (titanium oxide) powder, and a BaZr03 (barium zirconate) powder. It is constituted by a compact formed by compressing a mixed powder containing at least one of the powders as an auxiliary component, or a heat-treated compact.
  • the electrode 57 has a shape similar to the sliding side 13s of the shroud 13. Further, “welding” means to include welding together with diffusion, welding together with deposition, and welding together with deposition and diffusion.
  • the electrode 57 may be formed by slurry, MIM, thermal spraying or the like instead of being formed by compression.
  • the ratio (% by weight) of Ti02 to Cr203 is preferably 5:95.
  • the ratio (wt%) of Cr203 to BaZr03 is preferably set to 1: 2.
  • the ratio (% by weight) of the solid lubricant in the electrode 61 is desirably in the range of 3% to 7%. Good. This is because if the proportion of the solid lubricant is less than 3%, the protective coat 55 does not have a sufficient lubricating effect, while if the proportion of the solid lubricant is greater than 7%, the protective coat 55 This is because the tensile strength decreases.
  • another protective coat 59 may be formed on the slidable side 13s of the shroud 13 with the other turbine blade 51 '. Then, another protective coat 59 uses an electrode 61 as shown in FIGS. 9 (a) and 9 (b), and in an electrically insulating liquid L such as oil, the sliding side 13s of the shroud 13 and the electrode A pulse-like discharge is generated between the shroud 13 and the material of the electrode 57 or a reactant of the material on the sliding side 13s of the shroud 13 by the discharge energy.
  • the thickness of the protective coat 59 is from 0.05 mm to 0.5 mm.
  • the electrode 61 is formed by molding a mixed powder obtained by mixing a powder of a Co-Cr (cobalt 'chromium) alloy and a powder of a Ti (titanium) -based material by pressing with a press, or a heat treatment. It is constituted by the molded body.
  • the Ti-based materials include, in addition to TiC (titanium carbide), materials such as Ti and TiH2 (titanium hydride) that are carbonized by discharge to become TiC.
  • welding includes welding together with diffusion, welding together with deposition, and welding together with deposition and diffusion.
  • the electrode 61 may be formed by slurry, MIM, thermal spraying or the like instead of being formed by compression.
  • the electrode 61 has a shape similar to the sliding side 13s of the shroud 13.
  • the protective coat 59 when the protective coat 59 is placed in an oxidizing atmosphere at 600 ° C. or higher by operation of the gas turbine engine 3, the protective coat 59 changes from a layer containing a Co—Cr alloy and TiC to a layer containing Cr203 and Ti02. It is configured to change to.
  • fused portions (fused layers) B2 and B3 whose composition ratios change inclining in the thickness direction are generated.
  • the fused portions B2 and B3 are configured to have a thickness of 3 m or more and 20 m or less.
  • the appropriate discharge conditions are that the peak current is 30 A or less and the pulse width is 200 ⁇ s or less. Force S20A or less, pulse width 20 ⁇ s or less.
  • the reason that the thickness of the fusion parts # 2 and # 3 is not less than 3 ⁇ m and not more than 20 ⁇ m is the same as in the fusion part B1 in the first embodiment, as shown in FIGS. This is based on the test results shown below.
  • the blade main body 53 is set on the jig 41 so that the rubbing side 13s of the shroud 13 faces upward.
  • the rotor blade body 53 is positioned so that the electrode 57 or the electrode 61 faces each other. In some cases, it is sufficient to move the table 31 in any one of the X-axis direction and the Y-axis direction.
  • a pulse-like discharge is generated between the sliding side 13 s of the shroud 13 and the electrode 57 or the electrode 61 under the appropriate discharge conditions. Occurs.
  • the material of the electrode 57 or the electrode 61 is welded to the sliding side 13s of the shroud 13 by the discharge energy, and the wear-resistant side 13s of the shroud 13 is abraded.
  • the protective coat 55 or the protective coat 59 having a property can be formed.
  • the electrode 57 or the electrode 61 is reciprocated in the Z-axis direction by a small amount by the driving of the Z-axis servomotor 47 integrally with the kagami head 45.
  • the protective coat 55 Even if the protective coat 55 is placed in an oxidizing atmosphere at 300 ° C to 600 ° C, the Co--Cr alloy as the main component of the protective coat 55 does not change to Cr203 which is a high-temperature lubricant. Since the protective coat 55 contains a high-temperature lubricant (at least one of Cr203, Ti02, and BaZr03) as an auxiliary component, the protective coat 55 can have a sufficient lubricating action. In particular, when the protective coat 55 contains Cr203 and BaZr03, or when it contains Cr203 and Ti02, the protective coat 55 is oxidized at 300 ° C to 600 ° C. Can have a more sufficient lubricating effect.
  • a high-temperature lubricant at least one of Cr203, Ti02, and BaZr03
  • the protective coat 55 When the protective coat 55 is placed in an oxidizing atmosphere at a temperature of 600 ° C. or higher by operating the gas turbine engine, the Co—Cr alloy as a main component of the protective coat 55 becomes Cr203 which is a high-temperature lubricant. In addition to the high-temperature lubricant (at least one of Ti02 and BaZr03) as a sub-component of the protective coat 55, the protective coat 55 has a more sufficient lubricating action.
  • the high-temperature lubricant at least one of Ti02 and BaZr03
  • the protective coat 55 can maintain sufficient abrasion resistance continuously.
  • the abrasion resistance test of the protective coat is performed under predetermined test conditions (load at normal temperature: 5 MPa, load at 480 ° C. or more: 7 MPa, cycle number: 106, amplitude: ⁇ 0. 5mm),
  • the invention in FIG. 10 is a test article on which a protective coat 55 is formed
  • the comparative article in FIG. 10 is a Co--Cr alloy. This is a test specimen with a standard protective coat formed by welding.
  • the protective coat 59 When the protective coat 59 is placed in an oxidizing atmosphere of 600 ° C or higher by operating the gas turbine engine 3, the protective coat 59 changes from a layer containing a Co—Cr alloy and TiC to a layer containing Cr203 and Ti02. Therefore, the protective coat 59 can have a sufficient lubricating effect in an oxidizing atmosphere of 600 ° C. or more and also in an oxidizing atmosphere of 300 ° C. to 600 ° C. Therefore, even if the protective coat 59 is placed in an oxidizing atmosphere that changes in a wide temperature range from 300 ° C to 950 ° C, for example, the protective coat 59 must maintain sufficient abrasion resistance. Can be.
  • the protective coats 55 and 59 are formed by welding the material of the electrodes 57 and 61 to the sliding side 13 s in the shroud 13 rather than the discharge energy that is caused by thermal spraying, the area of the protective coats 55 and 59 is discharged.
  • the pretreatment for forming the protective coats 55 and 59 and the post-treatment for forming the protective coats 55 and 59 can be omitted.
  • the fusion parts B2 and B3 are configured to have a thickness of 3 ⁇ m or more and 20 ⁇ m or less, that is, in other words, when forming the protective coats 55 and 59, Since appropriate discharge conditions are selected, it is possible to increase the adhesion strength of the protective coats 55 and 59 while suppressing deformation of the base material of the rotor blade body 53.
  • the life of the turbine blade 51 can be extended.
  • the protective coats 55 and 59 are placed in an oxidizing atmosphere that changes in a wide temperature range from 300 ° C. to 950 ° C., for example, Since 59 can maintain sufficient wear resistance continuously, the wear of the sliding side 13s of the shroud 13 can be continuously and sufficiently suppressed, and the life of the turbine blade 51 can be extended.
  • the protective coats 55 and 59 have a porous structure, oxidation of the entire protective coats 55 and 59 is promoted, and the wear resistance of the protective coats 55 and 59 is further enhanced.
  • the life of the turbine bucket 51 can be further extended.
  • the pretreatment for forming the protective coats 55 and 59 and the post-processing for forming the protective coats 55 and 59 can be omitted. This reduces the number of processes required to improve the efficiency of the manufacturing operation of the Turbi blade 51.
  • the deformation of the base material of the rotor blade body 53 can be suppressed, and the adhesion strength of the protective coats 55 and 59 can be increased, so that the gas turbine engine 3 can sufficiently withstand fretting due to vibration. And the quality of the turbine blade 51 is stabilized.
  • a pulse-like discharge may be generated in the air having electric insulation instead of the liquid L having electric insulation.
  • a protective coat having the same configuration as the protective coats 55 and 59 is formed by discharge energy on the sliding side or sliding side of the engine component parts other than the turbine rotor blade 51 with the mating engine part. Is also good.
  • a protective coat having the same configuration as the protective coats 55 and 59 is discharged on the sliding side or sliding side of the high-temperature parts other than the engine parts such as the impeller used for the turbocharger, with respect to the other high-temperature parts. It may be formed by energy.
  • the force-strain prevention structure 71 is used in a compressor 73 in a gas turbine engine 3 and has a frictional compression. This prevents force between the dovetail 77 of the bucket 75 and the fitting groove 81 of the compressor disk 79.
  • a porous protective coat 83 is formed on the sliding side (a pair of sliding sides) 77s of the dovetail 77 with the fitting groove 81 of the compressor disk 79, and the thickness of the protective coat 83 is It is 0.05 mm and 0.15 mm.
  • the protective coat 83 uses the electrode 85 to generate a pulse-like discharge between the rubbing side of the dovetail 77 and the electrode 85 in an electrically insulating liquid such as oil, and the discharge energy It is formed by welding a material of the electrode or a reactant of the material to the rubbing side of the dovetail 77.
  • the electrode 85 is formed of a compact formed by pressing a powder of a Co alloy (25% Cr—10% Ni—7% W—remainder Co) by pressing or a heat-treated compact. Is to be done.
  • the electrode 85 has a shape similar to the sliding side 77s of the dovetail 77.
  • the Co alloy powder any of Cu—Ni—In alloy powder, Cu—Ni alloy powder, Cu—A1-Fe alloy powder, and Ni alloy powder may be used.
  • welding includes welding together with diffusion, welding together with deposition, and welding together with deposition and diffusion.
  • the electrode 85 may be formed by mud penetration, MIM, thermal spraying or the like instead of being formed by compression.
  • a fusion portion (fusion layer) B4 whose composition ratio changes in a gradient direction in the thickness direction is generated.
  • the fusion portion B4 is configured to have a thickness of 3 m or more and 20 m or less.
  • the appropriate discharge conditions are a peak current of 30 A or less and a pulse width of 200 s or less, preferably, a peak current of 20 A or less and a pulse width of 20 ⁇ s or less.
  • the reason why the thickness of the fusion portion # 4 is set to be not less than 3 ⁇ m and not more than 20 ⁇ m is as follows. Similar to the fusion part Bl in the embodiment, it is based on the test results shown in FIG. 4 and FIG.
  • microporous portion 87 in the protective coat 83 is filled with a solid lubricant 89 containing MoS2 or Cr203 as a main component.
  • the manufacturing method of the kinking prevention structure includes (I) a coating step and (II) a filling step. Is used.
  • the compressor blade 75 is clamped by the jig 41 so that the one sliding side 77s of the dovetail 77 faces upward.
  • the table 31 is moved in the X-axis direction and the Y-axis direction by the drive of the X-axis servo motor 33 and the Y-axis servo motor 35, as shown in FIG. Position compressor blade 75 so that 77s and electrode 85 face each other. In some cases, it is sufficient to simply move the table 31 in one of the X-axis direction and the Y-axis direction.
  • a pulse-like discharge is generated between the sliding side 77 s of the dovetail 77 and the electrode 85 under the above-described appropriate discharge conditions.
  • the material of the electrode 85 and the like are welded to the one sliding side 77s of the dovetail 77 by the discharge energy, and the one sliding side 77s of the dovetail 77 is welded.
  • a porous protective coat 83 can be formed.
  • the compressor blade 75 is clamped by the jig 41 so that the other sliding side 77 s of the dovetail 77 faces upward. Then, by repeating the same operation as described above, a porous protective coat 83 is formed on the other rubbing side 77s of the dovetail 77.
  • the jig 41 is unclamped and the compressor blade is Remove 75 from processing tank 37. Then, brush the fine holes 87 in the protective coat 83 with a brush.
  • the solid lubricant 89 is filled by dipping, rubbing or the like.
  • the protective coat 83 is formed by welding the material of the electrode 85 to the sliding side 77s of the dovetail 77 from the discharge energy, the protective coat 83 is protected.
  • the range of the coat 83 can be limited to the range in which electric discharge occurs, and in the manufacture of the squeezing prevention structure 71, the pretreatment accompanying the formation of the protective coat 83 and the post-treatment accompanying the formation of the protective coat 83 are omitted. be able to.
  • the fusion portion B4 is configured to have a thickness of 3 ⁇ m or more and 20 ⁇ m or less. Therefore, in other words, in forming the protective coat 83, appropriate discharge conditions are set. Since this is selected, the adhesion strength of the protective coat 83 can be increased while suppressing deformation of the base material of the compressor rotor blade 75.
  • the ratio (porosity) of the micropores 87 in the protective coat 83 can be increased.
  • the protective coat 83 is made of a sufficient material.
  • the anti-galling structure 71 is used in a high temperature environment of 600 ° C-1000 ° C while maintaining strength, Cr in the protective coat 83 is oxidized to generate Cr203, and the protective coat 83 has a self-lubricating property. It will take off.
  • the protective coating 83 is not used even if the squeezing prevention structure 71 is used in a high temperature environment of 500 ° C to 1000 ° C!
  • the solid lubricant 89 is mainly composed of Cr203, Even when used in a high temperature environment of 1 ° C to 1000 ° C, the lubricating action of the solid lubricant 89 can be sufficiently exerted.
  • the pretreatment accompanying the formation of the protection coat 83 and the post-treatment accompanying the formation of the protection coat 83 are omitted. Can reduce the number of steps required to manufacture the anti-galling structure 71,
  • the efficiency of the 71 manufacturing operations can be improved.
  • the ratio of the microporous portion 87 in the protective coat 83 can be increased, the solid lubricating material 89 is sufficiently filled in the microporous portion 87 in the protective coat 83, and the force is reduced by the galling preventing structure 71.
  • the kinking can be stably and sufficiently prevented.
  • the deformation of the base material of the compressor rotor blade 75 can be suppressed, and the adhesion strength of the protective coat 83 can be increased, so that the quality of the force-prevention structure 71 is stabilized.
  • a pulse-like discharge may be generated in the air having electric insulation instead of the liquid L having electric insulation.
  • a galling preventing structure having the same configuration as the galling preventing structure 71 may be used. .

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne l'utilisation d'une électrode composée d'une pièce moulée au moyen d'une poudre qui renferme comme composé principal une matière à base de titanium (Ti) ou d'une pièce obtenue par traitement thermique de la pièce moulée susmentionnée. Une décharge d'impulsions est provoquée dans un liquide ou gaz d'isolation électrique entre l'électrode et le côté coulissant frictionnel ou le côté coulissant de la pièce auxiliaire de moteur dans un corps de pièce. L'énergie de décharge permet de faire fusionner la matière de l'électrode ou la substance réactive de la matière avec le côté coulissant frictionnel ou le côté coulissant du corps de la pièce. Ainsi, un revêtement protecteur à résistance à l'usure est formé sur le côté coulissant frictionnel ou le côté coulissant du corps de la pièce.
PCT/JP2005/000393 2004-01-14 2005-01-14 Piece de moteur, piece de temperature elevee, procede de traitement surfacique, moteur a turbine a gaz, structure de prevention de grippage, et procede de production d'une telle structure WO2005068670A1 (fr)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
JP2004-007284 2004-01-14
JP2004007284 2004-01-14
JP2004024882 2004-01-30
JP2004-024882 2004-01-30
JP2004-024885 2004-01-30
JP2004024885 2004-01-30

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WO2005068670A1 true WO2005068670A1 (fr) 2005-07-28

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WO (1) WO2005068670A1 (fr)

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JP2007170376A (ja) * 2005-12-21 2007-07-05 General Electric Co <Ge> 耐久性のための蟻継ぎ表面強化
WO2007113914A1 (fr) 2006-04-05 2007-10-11 Mitsubishi Electric Corporation Revetement et son procede de formation
WO2008032359A1 (fr) * 2006-09-11 2008-03-20 Mitsubishi Electric Corporation Procédé de production d'une électrode pour traitement de surface par décharge électrique et électrode pour traitement de surface par décharge électrique
JP2008095837A (ja) * 2006-10-12 2008-04-24 Ihi Corp 摺動構造体及び皮膜形成方法
WO2008117802A1 (fr) * 2007-03-26 2008-10-02 Ihi Corporation Composant résistant à la chaleur
EP3954869A1 (fr) * 2020-08-14 2022-02-16 Raytheon Technologies Corporation Revêtement pour interface entre pied d'aube et disque et interface revêtue entre pied d'aube et disque

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JPH06280044A (ja) * 1993-03-24 1994-10-04 Res Dev Corp Of Japan 放電加工による表面処理方法及び装置
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Publication number Priority date Publication date Assignee Title
JP2007170376A (ja) * 2005-12-21 2007-07-05 General Electric Co <Ge> 耐久性のための蟻継ぎ表面強化
JP4705677B2 (ja) * 2006-04-05 2011-06-22 三菱電機株式会社 被膜および被膜の形成方法
WO2007113914A1 (fr) 2006-04-05 2007-10-11 Mitsubishi Electric Corporation Revetement et son procede de formation
JPWO2007113914A1 (ja) * 2006-04-05 2009-08-13 三菱電機株式会社 被膜および被膜の形成方法
US8287968B2 (en) 2006-04-05 2012-10-16 Mitsubishi Electric Corporation Coating film and coating-film forming method
WO2008032359A1 (fr) * 2006-09-11 2008-03-20 Mitsubishi Electric Corporation Procédé de production d'une électrode pour traitement de surface par décharge électrique et électrode pour traitement de surface par décharge électrique
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EP2062998A1 (fr) * 2006-09-11 2009-05-27 Mitsubishi Electric Corporation Procédé de production d'une électrode pour traitement de surface par décharge électrique et électrode pour traitement de surface par décharge électrique
EP2062998A4 (fr) * 2006-09-11 2010-04-14 Mitsubishi Electric Corp Procédé de production d'une électrode pour traitement de surface par décharge électrique et électrode pour traitement de surface par décharge électrique
JP2008095837A (ja) * 2006-10-12 2008-04-24 Ihi Corp 摺動構造体及び皮膜形成方法
JP4692462B2 (ja) * 2006-10-12 2011-06-01 株式会社Ｉｈｉ 摺動構造体及び皮膜形成方法
JPWO2008117802A1 (ja) * 2007-03-26 2010-07-15 株式会社Ihi 耐熱部品
WO2008117802A1 (fr) * 2007-03-26 2008-10-02 Ihi Corporation Composant résistant à la chaleur
EP3954869A1 (fr) * 2020-08-14 2022-02-16 Raytheon Technologies Corporation Revêtement pour interface entre pied d'aube et disque et interface revêtue entre pied d'aube et disque
US11952916B2 (en) 2020-08-14 2024-04-09 Rtx Corporation Self-lubricating blade root/disk interface

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