WO2010137610A1 - Hélice appliquée à un compresseur et son procédé de fabrication - Google Patents

Hélice appliquée à un compresseur et son procédé de fabrication Download PDF

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Publication number
WO2010137610A1
WO2010137610A1 PCT/JP2010/058880 JP2010058880W WO2010137610A1 WO 2010137610 A1 WO2010137610 A1 WO 2010137610A1 JP 2010058880 W JP2010058880 W JP 2010058880W WO 2010137610 A1 WO2010137610 A1 WO 2010137610A1
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WIPO (PCT)
Prior art keywords
core
impeller
sintering
hole
axis
Prior art date
Application number
PCT/JP2010/058880
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English (en)
Japanese (ja)
Inventor
智裕 井上
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株式会社Ihi
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Filing date
Publication date
Application filed by 株式会社Ihi filed Critical 株式会社Ihi
Publication of WO2010137610A1 publication Critical patent/WO2010137610A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • 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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the present invention relates to an impeller applied to a supercharger and a manufacturing method thereof.
  • Superchargers are often used for the purpose of sending more air into an internal combustion engine.
  • the supercharger includes a compressor, and pressurizes and supplies air to the engine when the compressor is driven.
  • a turbocharger of a type called a turbocharger includes a turbine that receives engine exhaust, and energy extracted from the exhaust by the turbine drives a compressor.
  • the crankshaft of the engine is connected to a compressor and drives it.
  • the turbocharger turbine is equipped with an impeller for converting airflow into rotational force.
  • the impeller usually includes a wheel around a rotation axis and a plurality of blades extending in the radial direction from the wheel. Since each blade has an inclination with respect to the axial direction and further has an airfoil shape, the blade can be rotated by receiving an air flow of the exhaust gas, and can extract energy from the exhaust gas. In order to achieve high aerodynamic properties, the impeller needs to precisely realize complex shapes.
  • the turbine impeller Since the turbine impeller is exposed to high-temperature exhaust, it must withstand high heat of, for example, about 800 ° C. Therefore, the design and manufacture of a turbine impeller is more difficult than the compressor impeller in terms of material, structure, and manufacturing method, and requires advanced technology. For example, it is necessary to apply a heat-resistant alloy, but since this is inherently extremely difficult to process, it is difficult to apply ordinary processes such as casting and forging combined with processing. For example, integral molding by precision casting is applied to the manufacture of a turbine impeller. However, finishing processing cannot be omitted for a portion that requires a sharp shape such as the peripheral edge of each blade.
  • the present inventor is considering applying powder injection molding to the manufacture of a turbine impeller in order to precisely manufacture a complex shape without finishing. Although satisfactory results can be seen in precisely realizing a thin and sharp shape such as a blade, a problem has been found that internal defects are likely to occur in a thick portion such as a wheel. The present invention has been made to overcome such problems.
  • an impeller used for a supercharger and rotating around a shaft is a core extending along the shaft, and a main body formed into a single body by sintering, And a main body including a hole that is crimped and fitted to the core by shrinkage due to the sintering, and a plurality of blades arranged around the shaft.
  • a core extending along an axis, a main body formed into a single body by sintering, and a hole that is crimped and fitted to the core by shrinkage due to the sintering.
  • a method of manufacturing an impeller comprising a plurality of blades arranged around the shaft, and a columnar section or a core adapted to form the hole, and an outer surface of the impeller.
  • a cavity having a cavity adapted to form a diameter and assembling a mold that can be divided into a plurality of pieces, and injecting a kneaded material containing a metal or ceramic powder and a binder into the mold, Forming a green body having a cavity corresponding to the core, inserting the core into the cavity, and sintering the green body to contract the green body and press the cavity against the core.
  • FIG. 1 is a partial cross-sectional view of a supercharger according to an embodiment of the present invention, corresponding to a portion indicated by an arrow I in FIG.
  • FIG. 2 is a cross-sectional view showing the entire supercharger.
  • FIG. 3 is a sectional view of the impeller of the supercharger.
  • FIG. 4 is a view for explaining the manufacturing process of the impeller, and is a cross-sectional view of the mold and the green body at the stage of injection molding.
  • FIG. 5 is a diagram for explaining a modification of the manufacturing process of the impeller.
  • FIG. 6 is a schematic cross-sectional view showing the stage of degreasing the green body.
  • FIG. 7 is a schematic cross-sectional view showing the stage of sintering the degreased green body.
  • FIG. 8 is a cross-sectional view of an impeller according to a modification of the embodiment.
  • the impeller according to an embodiment of the present invention can be used for, for example, a supercharger for a vehicle, and can be used particularly for a turbocharger, but can also be used for other purposes.
  • a turbocharger turbine impeller will be described.
  • the turbocharger 1 generally includes a turbine portion drawn on the left in the drawing, a shaft portion drawn in the center in the drawing, and a compressor portion drawn on the right in the drawing. Energy is extracted from the exhaust of the engine by the turbine unit, and the energy is transmitted to the compressor unit through the shaft unit, and the compressor unit compresses the air and sends it to the engine.
  • the shaft portion includes a bearing housing 3, a radial bearing 5 and a thrust bearing 7 supported by the bearing housing 3, and a shaft 9 that is rotatably supported by both bearings 5 and 7.
  • the radial bearing 5 supports the shaft 9 in the radial direction
  • the thrust bearing 7 supports the shaft 9 in the axial direction, so that the shaft 9 can rotate around the axis C.
  • the compressor impeller 13 is coupled to the right end of the shaft 9 in the axial direction so as to rotate together around the axis C. Such coupling is performed by fastening with bolts, but if possible, other means such as welding or fitting may be used.
  • a compressor housing 11 is coupled to the right end of the bearing housing 3 so as to cover the compressor impeller 13. The connection can be by fastening bolts, but may be by other means. The compressor housing 11 secures an appropriate gap with respect to the impeller 13 so as not to interfere with the rotation.
  • the compressor impeller 13 includes a wheel 15 around the axis C and a plurality of blades 17 extending in the radial direction from the wheel 15.
  • the blades 17 are arranged at equal intervals around the wheel 15, but the arrangement is not necessarily limited to equal intervals.
  • Each blade 17 is inclined with respect to the axial direction, more preferably has an airfoil shape, and air is supplied in a centrifugal direction in a centrifugal direction as the wheel 15 rotates.
  • Each outer edge of each blade 17 is close to the inner wall of the compressor housing 11 so as to minimize airflow diversion.
  • the compressor housing 11 includes an air intake port 19 and a diffuser passage 21 communicating with the air intake port 19.
  • the air intake 19 is for taking in outside air, and is configured to be coupled to an intake pipe having an air cleaner (not shown).
  • the diffuser passage 21 is a slit-like passage formed so as to surround the outer edge of the base end of the compressor impeller 13, and the air pressurized in the centrifugal direction by the compressor impeller 13 passes through the diffuser passage 21.
  • the compressor housing 11 further includes a compressor scroll passage 23 that communicates with the diffuser passage 21.
  • the compressor scroll channel 23 is a spiral channel that goes around the compressor impeller 13 at least once, and the outer periphery of the diffuser channel 21 opens to the compressor channel 23 over the entire circumference.
  • the opening at the end of the compressor scroll passage 23 is configured to be coupled to an intake manifold (not shown) of the engine.
  • a turbine impeller 27 is coupled to the left end of the shaft 9 in the axial direction so as to rotate together about the axis C. Such coupling is by welding, but if possible, other means such as brazing or fitting may be used.
  • a turbine housing 25 is coupled to the left end of the bearing housing 3 so as to cover the turbine impeller 27. Such coupling is by fastening bolts or other suitable means. The turbine housing 25 secures an appropriate gap with respect to the turbine impeller 27 so as not to interfere with the rotation.
  • the turbine housing 25 includes a turbine scroll passage 49 having one end opened to the outside.
  • the turbine scroll flow path 49 is a spiral flow path that makes at least one round around the turbine impeller 27, and an inner periphery thereof opens toward the turbine impeller 27.
  • the externally open end is configured to couple with an exhaust manifold (not shown) to take in exhaust from the engine.
  • the turbine housing 25 includes a variable nozzle unit 29 disposed so as to be interposed between the turbine scroll flow path 49 and the turbine impeller 27.
  • the variable nozzle unit 29 includes a ring 31, a shroud ring 35, and a plurality of nozzles 39.
  • the ring 31 is fixed to the turbine housing 25 via a mounting ring 33.
  • the shroud ring 35 is fixed to the mounting ring 33 via a plurality of connecting pins 37, and a throat through which exhaust can pass is secured between the ring 31 and the shroud ring 35.
  • the plurality of nozzles 39 are arranged around the turbine impeller 27 at equal intervals, and are fitted to the rings 31 and 35 so as to be swingable.
  • Each nozzle 39 includes a vane located at the throat between the rings 31 and 35. The vane can adjust the opening degree of the throat by swinging the nozzle 39.
  • Each nozzle 39 includes a shaft 41 extending rightward in the drawing, and is connected to the synchronization mechanism 43 at the right end of the shaft 41.
  • the synchronization mechanism 43 includes, as an example, a ring member that can rotate around the axis C and a plurality of links that are respectively connected to the shaft 41 from the ring member.
  • the synchronization mechanism 43 is configured such that the links are driven by the rotation of the ring member, and the shaft 41 is respectively rotated to swing the plurality of nozzles 39 in synchronization.
  • the synchronization mechanism 43 is connected to the lever 47 via the transmission shaft 45 and can be driven by an external actuator.
  • variable nozzle unit 29 and the synchronization mechanism 43 described above are necessary only when the turbocharger 1 is a variable displacement type, and may be omitted in other cases.
  • the turbine scroll flow path 49 communicates with the turbine impeller 27 through an appropriate throat.
  • the turbine housing 25 includes a discharge port 51 so as to communicate with the left end in the axial direction of the turbine impeller 27.
  • the discharge port 51 is for discharging the exhaust gas that has passed through the turbine impeller 27, and is configured to be coupled to an exhaust pipe that includes a purification device (not shown).
  • the turbine impeller 27 includes a main body 53 and a core 61 that extends along the axis C and is coupled to the main body 53.
  • the main body 53 is made of metal or ceramic formed into a single body by powder injection molding described later, and includes a wheel portion 55, a plurality of blades 57 extending in the radial direction from the wheel portion 55, and holes formed in the wheel portion 55. 59.
  • the wheel portion 55 is configured to be coupled to the shaft 9 at the right end thereof.
  • the core 61 may be coupled to the shaft 9 instead of the wheel portion 55, or may be coupled by another appropriate interposed member. Due to the coupling with the shaft 9, the turbine impeller 27 can rotate around the axis C together with the shaft 9.
  • a hole 59 is formed around the axis C in the wheel portion 55.
  • the hole 59 may be a through hole as shown in FIG. 3 or a non-through hole having a bottom as shown in FIG.
  • the hole 59 is preferably a cylindrical shape that is axisymmetric with respect to the axis C, but may be non-cylindrical or asymmetric if possible.
  • the hole 59 is crimped to the core 61 by contracting in a sintering process described later.
  • the plurality of blades 57 are formed integrally with the wheel portion 55 and arranged around the axis C at equal intervals. If possible, it may not be equally spaced.
  • Each blade 57 has an inclination with respect to the direction of the axis C, and more preferably has an airfoil shape, in order to generate torque by receiving an exhaust airflow.
  • the turbine impeller 27 can extract energy from the exhaust and drive the compressor impeller 13 via the shaft 9.
  • Each outer edge of each blade 57 is proximate to the shroud ring 35 to minimize airflow diversion. When there is no variable nozzle unit 29, each outer edge is close to the inner wall of the turbine housing 25.
  • the core 61 has a shape adapted to the hole 59, that is, preferably a cylinder that is axisymmetric with respect to the axis C, but may be non-cylindrical or asymmetric if possible. Splines, keyways, or key protrusions may be provided.
  • the core 61 is fitted in the hole 59 and is crimped to the hole 59 as described above.
  • the core 61 is preferably solid but may have a hollow or internal structure if possible.
  • Exhaust gas discharged from the engine passes through the turbine scroll passage 49 from the intake port, and flows into the throat of the variable nozzle unit 29 in a spiral shape (the throat of the turbine housing when there is no variable nozzle unit), and further, the turbine impeller 27.
  • the exhaust gives torque to the turbine impeller 27 when passing between the plurality of blades 57 and is discharged to the discharge port 51.
  • Such torque is transmitted to the compressor impeller 13 by the shaft 9 and is used for air compression by rotating the compressor impeller 13.
  • the throat opening degree may be adjusted by swinging the plurality of nozzles 39 in accordance with the flow rate of the exhaust gas.
  • the turbine impeller 27 is manufactured by powder injection molding as follows.
  • the injection molding machine includes a fixed frame 65 and a movable frame 71 for supporting the mold 63.
  • the injection molding machine includes an injection machine (not shown), an injection nozzle 87, an actuator for driving the movable frame 71, and the like.
  • the mold 63 is made of an appropriate metal such as SKD11 (JIS G 4404) and can be appropriately divided.
  • the mold 63 is divided into a base 67 and an outer mold 77, and the outer mold 77 is further divided into a plurality in the circumferential direction.
  • the combination of the molding surface 69 of the base 67 and the molding surface 79 of the outer mold 77 defines a cavity 81 that is adapted to mold the outer shape of the turbine impeller 27.
  • the columnar portion protruding from the base 67 is suitable for forming the hole 59 of the turbine impeller 27.
  • the columnar portion may be slightly tapered in order to facilitate extraction after injection molding. Since volume shrinkage of about 20% occurs by sintering, the mold 63 and the base 67 are designed in consideration of such volume shrinkage.
  • a block 73 is interposed between the mold 63 and the movable frame 71.
  • the block 73 has a conical concave surface 75, and the mold 63 has a corresponding tapered surface.
  • the movable frame 71 pressurizes the mold 63 due to the contact between the concave surface 75 and the tapered surface, the portions of the outer mold 77 are in close contact with each other in the circumferential direction.
  • an actuator is provided to move each outer mold 77 in the radial direction. Such an actuator may be configured to drive the outer mold 77 in synchronization with the movable frame 71.
  • the fixed frame 65 further includes a spool 89 that communicates with the injection nozzle 87, and the stand 67 includes a runner 85 and a gate 83 that communicate with the spool 89 and allow the ejected material to pass therethrough.
  • a plurality of runners 85 are provided so as to penetrate the base 67, and more preferably provided so as to penetrate the columnar portion of the base 67.
  • the gate 83 opens to the right end of the cavity 81, and more preferably opens to the columnar portion.
  • the gate 83, the runner 85, and the spool 89 may be provided in the outer mold 77 or other elements in place of the base 67 or in addition to the base 67.
  • the base 67 and the core 91 may be separated.
  • the core 91 is adapted to mold the hole 59 of the turbine impeller 27.
  • the core 91 may be slightly tapered in order to facilitate extraction after injection molding.
  • the core 91 may be made of a disappearing material instead of being made of metal.
  • the evanescent material include thermoplastic resins such as styrene, acrylic, cellulose, polyethylene, vinyl, nylon, and fluorocarbon resins. Appropriate additives may be added. Since the vanishing core is decomposed and evaporated in the degreasing step described later, the extraction after the injection molding can be omitted.
  • the injection M is kneaded.
  • a mixture of metal powder or ceramic powder and a binder is suitable.
  • metal powder or ceramic powder powders of various materials can be used according to required characteristics.
  • Ni-base heat-resistant alloy Inconel 713C, IN100, MAR-M246, etc.
  • ceramic powder such as silicon nitride and sialon
  • a known powder injection molding binder can be used as the binder.
  • a powder injection molding binder for example, a material obtained by adding an additive such as paraffin wax to a thermoplastic resin such as polystyrene or polymethyl methacrylate can be suitably used.
  • Such a binder after solidifying after injection, retains the form of the injection product until the degreasing step described later, decomposes and evaporates in the degreasing step, and leaves no trace on the sintered product.
  • the mixture of the metal powder or ceramic powder and the binder is heated to, for example, 100 to 150 ° C. and kneaded.
  • the kneading temperature can be appropriately selected depending on the composition of the kneaded product. After kneading, the injection M is obtained by cooling appropriately.
  • the elements of the base 67 and the outer mold 77 are placed on the fixed frame 65. If the core 91 is a separate body, it is placed on the stand 67. A known release agent may be applied to these in advance.
  • the outer mold 77 is moved inward in the radial direction by the actuator, and the components of the outer mold 77 are brought into contact with each other.
  • the block 73 is brought into contact with these and pressed by the movable frame 71.
  • the movement of the outer mold 77 by the actuator may be synchronized with the movement of the movable frame 71. Therefore, the outer mold 77 and the base 67 are in close contact with each other, and the mold 63 is assembled.
  • the injection M is heated to, for example, 160 to 200 ° C. to give sufficient fluidity, and is injected into the mold 63 through the injection nozzle 87 with a pressure of about 100 MPa.
  • the heating temperature and the injection pressure can be appropriately selected depending on the composition of the kneaded product.
  • the injection is solidified and the green body 53F is formed.
  • the movable frame 71 is separated from the mold 63, and the outer mold 77 is further separated from the green body 53F.
  • the green body 53F remains temporarily fixed on the base 67.
  • the green body 53F is pulled away from the table 67 and taken out by appropriate means such as a plunger.
  • the core 91 is a separate body, the green body 53F can be handled by holding the core 91.
  • the core 91 is extracted from the extracted green body 53F using an appropriate jig.
  • the core 91 is subjected to a degreasing process described later while being fitted in the green body 53F, and is decomposed and evaporated in the degreasing process and disappears.
  • the step of removing the columnar portion or the core 91 from the green body 53F may be any of these.
  • the molded green body 53F is about 20% larger than the final shape in consideration of shrinkage due to sintering, as described above.
  • a hole 59F is provided in the wheel part 55F.
  • the green body 53F is introduced into an appropriate atmosphere control furnace 93. While introducing nitrogen gas into the furnace and maintaining the nitrogen atmosphere, the inside of the furnace is heated to an appropriate high temperature not exceeding 800 ° C. by appropriate heating means such as a carbon heater, and is maintained for 30 minutes or more. The Through such a degreasing process, the binder contained in the green body 53F (when the vanishing core 91 is used, the core 91 is also melted, decomposed, and evaporated to be removed).
  • the degreasing step may be replaced with other known methods such as elution with an appropriate solvent instead of the above-described method.
  • the core 61 is inserted into the hole 59F of the degreased green body 53F, and the whole is supported by an appropriate jig and introduced into an appropriate atmosphere control furnace 93.
  • the core 61 is made of the same material as that of the above-described metal powder or ceramic powder, or is made of another appropriate material. At this time, since it is before shrinkage due to sintering, a slight gap is maintained between the core 61 and the hole 59F.
  • the inside of the furnace 93 is placed under an appropriate reduced pressure, and the inside of the furnace is heated to an appropriate sintering temperature, for example, 1000 to 1500 ° C. by an appropriate heating means such as a carbon heater, for an appropriate time, for example, 1 hour or more. Retained.
  • an appropriate heating means such as a carbon heater
  • the sintering progresses and the green body 53F contracts.
  • the hole 59F is reduced in diameter and is in contact with the core 61, and the core 61 is pressure-bonded to the hole 59 after sintering. As shown in FIG.
  • the degreasing step and the sintering step are independent, but these may be carried out continuously.
  • nitrogen or the like is introduced to bring the inside of the furnace 93 to atmospheric pressure, and the sintered turbine impeller 27 is taken out. It may be used as it is, or an appropriate surface treatment may be applied to remove the film covering the surface.
  • interference fit is a fit in which one part is forcibly pressed into a space provided by a counterpart part. Usually, an interference fit is achieved by press-fitting the one part into the space.
  • the space provided by the impeller 27, that is, the hole 59 is forcibly pressed against the core 61 by shrinkage due to sintering. In other words, this is the opposite of normal interference fit.
  • powder injection molding is applied instead of precision casting, it can be precisely realized even with a thin and sharp shape such as a blade, and a troublesome process such as finishing is omitted. be able to.
  • the wheel portion 55 is sufficiently thin because it is formed with the holes 61 in advance, and therefore there is little risk of internal defects. Since the holes 59 are closed by the core 61 and are strongly pressed against each other by the remaining compressive stress, the fixing between the wheel portion 55 and the core 61 is sufficiently strong.
  • the fatigue life of the turbine impeller is remarkably improved. Centrifugal force acts on the turbine impeller due to the rotation of the turbine, and thus tensile stress is generated in the radial direction. As the rotational speed varies, the tensile stress also varies, so that repeated stress variations that cause fatigue are imparted to the turbine impeller. According to the present embodiment, since the compressive stress is applied in advance in the direction to cancel the tensile stress, the total stress is at a very small level. That is, the fatigue life is significantly improved because the stress fluctuates at a very small level.
  • a structure of a turbine impeller capable of precisely manufacturing a complicated shape and a method for manufacturing the turbine impeller are provided with little risk of internal defects.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Combustion & Propulsion (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention porte sur une hélice, utilisée pour un compresseur de suralimentation et tournant autour de l'axe, qui comporte : un noyau qui s'étend le long de l'axe et qui peut être relié à l'arbre du compresseur ; un corps qui est moulé en un seul corps par frittage, le corps ayant un trou qui vient en prise avec le noyau au moyen d'une adaptation par pression par contraction dans l'opération de frittage, ainsi que des pales qui sont disposées autour de l'axe.
PCT/JP2010/058880 2009-05-26 2010-05-26 Hélice appliquée à un compresseur et son procédé de fabrication WO2010137610A1 (fr)

Applications Claiming Priority (2)

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JP2009126807A JP2010275878A (ja) 2009-05-26 2009-05-26 インペラ、過給機、及びインペラの製造方法
JP2009-126807 2009-05-26

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WO2010137610A1 true WO2010137610A1 (fr) 2010-12-02

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Cited By (1)

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JP2013148050A (ja) * 2012-01-23 2013-08-01 Kawasaki Heavy Ind Ltd 軸流圧縮機翼とその製造方法

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Publication number Priority date Publication date Assignee Title
US20150050126A1 (en) * 2012-03-01 2015-02-19 Borgwarner Inc. Exhaust-gas turbocharger
DE102012211481A1 (de) * 2012-07-03 2014-01-09 Robert Bosch Gmbh Verfahren und Vorrichtung zum Herstellen eines Bauteils
WO2014050530A1 (fr) 2012-09-28 2014-04-03 株式会社Ihi Unité à buse variable, compresseur à capacité variable et procédé de fabrication d'éléments de transmission de puissance
EP2960465B1 (fr) * 2013-02-22 2017-05-10 Mitsubishi Heavy Industries, Ltd. Ensemble compresseur
JP6276117B2 (ja) * 2014-06-18 2018-02-07 株式会社神戸製鋼所 圧縮機及び圧縮機の製造方法
US20170022816A1 (en) * 2015-07-24 2017-01-26 Borgwarner Inc. MIM-FORMED TiA1 TURBINE WHEEL SURROUNDING A CAST/MACHINED CORE
CN109312661B (zh) * 2016-09-02 2020-12-25 株式会社Ihi 增压器用叶轮

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JPS62228602A (ja) * 1986-03-28 1987-10-07 Toyota Central Res & Dev Lab Inc 熱機関用回転体
JP4240512B1 (ja) * 2008-10-29 2009-03-18 株式会社テクネス タービンホイールの製造方法

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JPS62228602A (ja) * 1986-03-28 1987-10-07 Toyota Central Res & Dev Lab Inc 熱機関用回転体
JP4240512B1 (ja) * 2008-10-29 2009-03-18 株式会社テクネス タービンホイールの製造方法

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013148050A (ja) * 2012-01-23 2013-08-01 Kawasaki Heavy Ind Ltd 軸流圧縮機翼とその製造方法
US9631635B2 (en) 2012-01-23 2017-04-25 Kawasaki Jukogyo Kabushiki Kaisha Blades for axial flow compressor and method for manufacturing same

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