WO2016013433A1 - Ni合金部品の製造方法 - Google Patents
Ni合金部品の製造方法 Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
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- 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
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
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- 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
- B22F3/02—Compacting only
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- 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
- B22F3/12—Both compacting and sintering
- B22F3/16—Both compacting and sintering in successive or repeated steps
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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- 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
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
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- 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
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- 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
- B22F2302/00—Metal Compound, non-Metallic compound or non-metal composition of the powder or its coating
- B22F2302/45—Others, including non-metals
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- 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
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
Definitions
- the present invention relates to a method for manufacturing a Ni alloy part, and more particularly, to a method for manufacturing a Ni alloy part formed by sintering a precipitation hardening Ni alloy powder by a metal powder injection molding method.
- a precipitation hardening type Ni alloy having excellent heat resistance is used because it is necessary to ensure mechanical strength such as fatigue strength at a high temperature.
- a heat treatment including a solution treatment and an aging treatment is performed.
- Patent Document 1 describes that a forging material made of a precipitation hardening Ni alloy is subjected to a solution treatment at about 871 ° C. to about 954 ° C., and an aging treatment is performed after the solution treatment to produce a jet engine part or the like. ing.
- a molding method in which a metal powder is mixed with a binder and injection molded and then sintered to obtain a final product is called a metal powder injection molding method (MIM: Metal Injection Molding).
- MIM Metal Injection Molding
- the metal powder injection molding method is a manufacturing method in which a final shape part having a material strength approaching that of a forging material can be obtained while maintaining the same degree of freedom of shape as the synthetic resin injection molding. According to the metal powder injection molding method, a product having a complicated shape can be obtained without the need for a complicated assembling process. Therefore, application to Ni alloy parts such as jet engine parts has been studied.
- the solution treatment used for the forging material is applied to the sintered compact formed by the metal powder injection molding method using the precipitation hardening type Ni alloy powder, the solution treatment is performed at a relatively low solution treatment temperature.
- a hard and brittle ⁇ phase (delta phase) is precipitated at grain boundaries and the like, and mechanical strength such as fatigue strength may be lowered.
- an object of the present invention is to provide a method for producing a Ni alloy part that can further improve the mechanical strength characteristics of a Ni alloy part molded by a metal powder injection molding method using precipitation hardening Ni alloy powder. That is.
- the manufacturing method of the Ni alloy part according to the present invention is as follows: Ti: 0.65 mass% to 1.15 mass%, Al: 0.20 mass% to 0.80 mass%, Cr: 17.00 mass% or more 21.00 mass% or less, Nb: 4.75 mass% or more and 5.50 mass% or less, Mo: 2.80 mass% or more and 3.30 mass% or less, Ni: 50.00 mass% or more and 55.00 mass%
- the solution treatment step involves solution treatment of the sintered body at 1100 ° C. or more and 1250 ° C. or less.
- the manufacturing method of the Ni alloy part according to the present invention is as follows: Ti: 0.65 mass% to 1.15 mass%, Al: 0.20 mass% to 0.80 mass%, Cr: 17.00 mass% or more 21.00 mass% or less, Nb: 4.75 mass% or more and 5.50 mass% or less, Mo: 2.80 mass% or more and 3.30 mass% or less, Ni: 50.00 mass% or more and 55.00 mass%
- the precipitation hardening type Ni alloy powder consisting of Fe and inevitable impurities is sintered at 1100 ° C. to 1250 ° C. for 1 to 5 hours by metal powder injection molding, and then rapidly cooled to room temperature to form.
- An aging treatment step of holding the sintered body at 600 ° C. or more and 800 ° C. or less and then cooling to room temperature and aging treatment is provided.
- the Ni alloy component is a gas turbine component.
- Ti 0.65 mass% or more and 1.15 mass% or less
- Al 0.20 mass% or more and 0.80 mass% or less
- Cr 17.00 mass% or more and 21.00 mass% or less
- Nb 4.75 mass% or more and 5.50 mass% or less
- Mo 2.80 mass% or more and 3.30 mass% or less
- Ni 50.00 mass% or more and 55.00 mass% or less
- a sintered compact formed by sintering precipitation hardening type Ni alloy powder composed of inevitable impurities by a metal powder injection molding method is held at 1050 ° C. or higher and 1250 ° C. or lower for 1 to 5 hours, and then rapidly cooled to room temperature.
- Ti 0.65 mass% or more and 1.15 mass% or less
- Al 0.20 mass% or more and 0.80 mass% or less
- Cr 17.00 mass% or more and 21.00 mass% or less
- Nb 4.75 mass% or more and 5.50 mass% or less
- Mo 2.80 mass% or more and 3.30 mass% or less
- Ni 50.00 mass% or more and 55.00 mass% or less
- the balance being Fe and Precipitation hardening type Ni alloy powder composed of inevitable impurities was sintered by holding at 1100 ° C. or higher and 1250 ° C.
- Hard, brittle ⁇ phase (Dell Phase) is the precipitation inhibition, such as grain boundaries, it is possible to improve the mechanical strength such as fatigue strength in Ni alloy part.
- FIG. 1 it is a flowchart which shows the structure of the manufacturing method of Ni alloy components.
- FIG. 1 it is a figure which shows the structure of Ni alloy components applied to a gas turbine.
- FIG. 1 it is a photograph which shows the metal structure observation result of the test piece of the comparative example 1.
- FIG. In embodiment of this invention it is a photograph which shows the metal structure observation result of the test piece of Example 1.
- FIG. 1 it is a photograph which shows the metal structure observation result of the test piece of Example 2.
- FIG. In embodiment of this invention it is a photograph which shows the metal structure observation result of the test piece of Example 3.
- FIG. In embodiment of this invention it is a photograph which shows the metal structure observation result of the test piece of Example 4.
- FIG. In embodiment of this invention it is a graph which shows the result of a room temperature fatigue test. In embodiment of this invention, it is a graph which shows the result of a high temperature fatigue test.
- FIG. 1 is a flowchart showing a configuration of a method for manufacturing a Ni alloy part.
- the manufacturing method of Ni alloy components includes a solution treatment step (S10) and an aging treatment step (S12).
- the sintered compact formed by sintering the precipitation hardening type Ni alloy powder by the metal powder injection molding method is held at 1050 ° C. or higher and 1250 ° C. or lower for 1 hour to 5 hours, This is a step of rapidly cooling to a solution treatment.
- the metal powder injection molding method includes a kneading process, an injection molding process, a degreasing process, and a baking process.
- a precipitation hardened Ni alloy powder and a binder composed of a thermoplastic resin or wax are mixed together by a kneader to produce a kneaded body.
- Ni alloy powder equivalent to Alloy 718 which is a precipitation hardening type Ni alloy excellent in heat resistance
- Ti (titanium) 0.65 mass% or more and 1.15 mass% or less
- Al (aluminum) 0.20 mass% or more and 0.80 mass% or less
- Cr (chromium) 17.00 mass% or more and 21.00 mass% or less
- Nb (niobium) 4.75 mass% or more and 5.50 mass% or less
- the balance is composed of Fe (iron) and inevitable impurities.
- Inevitable impurities include B (boron), Si (silicon), P (phosphorus), Mn (manganese), Co (cobalt), Ta (tantalum), Cu (copper), Pb (lead), and Bi (bismuth). ), Se (selenium), O (oxygen), C (carbon) or N (nitrogen).
- Ti which is an alloy component, is an element that forms a ⁇ ′ phase (gamma prime phase).
- the ⁇ ′ phase (gamma prime phase) is formed of an intermetallic compound mainly composed of [Ni 3 (Al, Ti)].
- Al is an element that forms a ⁇ ′ phase (gamma prime phase) and an element that improves oxidation resistance by forming an aluminum oxide such as alumina.
- Cr is an element that improves the oxidation resistance and corrosion resistance by forming a chromium oxide such as chromium oxide.
- Nb is an element that forms a ⁇ ′′ phase (gamma double prime phase).
- the ⁇ ′′ phase (gamma double prime phase) is formed of an intermetallic compound mainly composed of [Ni 3 Nb].
- Mo is an element that enhances the solid solution by solid solution in the ⁇ phase (gamma phase), which is the Ni matrix, and improves the corrosion resistance.
- Fe is an element which is solid-solution strengthened by solid solution in the ⁇ phase (gamma phase) which is the Ni parent phase.
- Ni is an element that forms a ⁇ phase (gamma phase), a ⁇ ′ phase (gamma prime phase), and a ⁇ ′′ phase (gamma double prime phase), which are Ni matrix phases. By doing so, a precipitation hardening Ni alloy having heat resistance and corrosion resistance can be obtained.
- the average particle size of the precipitation hardening Ni alloy powder is preferably smaller than 35 ⁇ m.
- the average particle size is, for example, the particle size distribution obtained by accumulating the particle size distribution results from the smaller particle size using the particle size distribution of the particles measured by the laser diffraction / scattering method, and the accumulated value becomes 50%. (Median diameter).
- gas atomized powder, water atomized powder, or the like can be used, but it is preferable to use gas atomized powder having a lower oxygen concentration than water atomized powder.
- a binder composed of a thermoplastic resin such as polystyrene resin or polymethyl methacrylate resin and a wax such as paraffin wax can be used.
- the precipitation hardening Ni alloy powder and the binder are kneaded with a kneader to form a kneaded body.
- an injection molding machine presses the kneaded body and injects it into a mold to form a preform.
- the same one as that used in the production of synthetic resin parts or the like can be used.
- the binder components are removed from the preformed body taken out of the mold by heating or solvent.
- the preform can be put into a degreasing furnace and heated in an inert atmosphere such as argon gas to be degreased.
- the degreased preform is heated and sintered in a vacuum atmosphere or an inert atmosphere such as argon gas to form a sintered body.
- the sintering temperature is 1100 ° C. to 1300 ° C.
- the firing time is 1 hour to 5 hours.
- a general metal material sintering furnace can be used. In this manner, a sintered body formed by the metal powder injection molding method using the precipitation hardening Ni alloy powder is obtained.
- the solution treatment of the sintered body formed by the metal powder injection molding method using the precipitation hardening type Ni alloy powder will be described.
- the sintered body is held at 1050 ° C. or higher and 1250 ° C. or lower for 1 to 5 hours, and then rapidly cooled to room temperature.
- the solution treatment is performed by an aging treatment to be described later, and a ⁇ ′ phase (gamma prime phase) mainly composed of [Ni 3 (Al, Ti)] or a ⁇ ”phase mainly composed of [Ni 3 Nb] ( Al that forms a ⁇ 'phase (gamma prime phase) or a ⁇ "phase (gamma double prime phase) in order to finely precipitate the gamma double prime phase) in the Ni matrix ⁇ phase (gamma phase), This is because alloy components such as Ti and Nb are dissolved in the ⁇ phase (gamma phase) which is the Ni parent phase.
- the solution treatment temperature is 1050 ° C. or higher.
- a hard and brittle ⁇ phase (delta phase) mainly composed of [Ni 3 Nb] precipitates at grain boundaries and the like. Because.
- the crystal structure of the ⁇ ”phase (gamma double prime phase) is tetragonal, whereas the crystal structure of the ⁇ phase (delta phase) is orthorhombic.
- the solution treatment temperature is 1250 ° C. or lower because when the temperature is higher than 1250 ° C., the growth of crystal grains increases, and the mechanical strength decreases due to the coarsening of the crystal grains.
- the solution treatment temperature is preferably 1100 or higher and 1250 ° C or lower. This is because precipitation of the ⁇ phase (delta phase) can be further suppressed by setting the solution treatment temperature to 1100 ° C. or higher.
- the retention time at the solution treatment temperature is 1 to 5 hours.
- the ⁇ phase (gamma phase) that is the Ni matrix of the alloy component such as Al, Ti, Nb, etc. This is because there is a case where the solid solution cannot be sufficiently formed, and when the holding time is longer than 5 hours, the growth of the crystal grains becomes large and the crystal grains may be coarsened. .
- the alloy components such as Al, Ti, and Nb are rapidly cooled to bring them into a supersaturated state at room temperature.
- the cooling from the solution treatment temperature is preferably rapid cooling at a cooling rate equal to or higher than air cooling, and more preferably rapid cooling by gas fan cooling, water cooling, or the like.
- the solution treatment can be performed in a vacuum atmosphere or an inert atmosphere using an inert gas such as argon gas.
- an inert gas such as argon gas.
- a general metal material heat treatment furnace such as a solution treatment furnace can be used.
- the aging treatment step (S12) is a step in which the solution-treated sintered body is held at 600 ° C. or higher and 800 ° C. or lower and then cooled to room temperature and subjected to an aging treatment.
- the aging temperature is 600 ° C. or more and 800 ° C. or less.
- the ⁇ phase which is the Ni matrix phase
- the ⁇ ′ phase (gamma prime phase) and the ⁇ ′′ phase (gamma)
- the double prime phase can be finely precipitated and the precipitation of the ⁇ phase (delta phase) can be suppressed.
- the ⁇ ′′ phase (gamma double prime phase) is a metastable phase, it has a high temperature. When it is heat-treated, it transforms into a stable ⁇ phase (delta phase). Therefore, by setting the aging treatment temperature to 600 ° C. or more and 800 ° C.
- phase transformation from the ⁇ ′′ phase (gamma double prime phase) to the ⁇ phase (delta phase) is suppressed.
- Holding at the aging treatment temperature The time is preferably 5 hours to 30 hours, and the cooling from the aging treatment temperature to room temperature is performed by, for example, air cooling or gas fan cooling.
- the first aging treatment is performed by holding at 718 to 760 ° C. for 8 to 10 hours, cooling from 621 to 649 ° C. by furnace cooling, and then at 621 to 649 ° C. It can be held for 8 to 20 hours and cooled to room temperature by gas fan cooling or the like.
- the solution-treated sintered body is held at 718 ° C. for 8 hours, cooled to 621 ° C. by furnace cooling, then held at 621 ° C. for 8 hours, and cooled to room temperature by gas fan cooling. Is processed.
- the aging treatment can be performed in a vacuum atmosphere or an inert atmosphere using an inert gas such as argon gas.
- an inert gas such as argon gas.
- a general metal material heat treatment furnace such as an aging furnace can be used.
- the ⁇ ′ phase (gamma prime phase) and the ⁇ ′′ phase (gamma double prime phase) are finely dispersed in the ⁇ phase (gamma phase) which is the Ni parent phase.
- precipitation of hard and brittle ⁇ phase (delta phase) crystal grain boundaries that reduce ductility, toughness and the like, and coarsening of crystal grains due to crystal grain growth are suppressed.
- the mechanical strength such as tensile strength and fatigue strength of the Ni alloy part can be improved.
- the sintered compact formed by the metal powder injection molding method using the precipitation hardening Ni alloy powder is held at 1050 ° C. or higher and 1250 ° C. or lower for 1 to 5 hours, By quenching to a low temperature, precipitation of hard and brittle ⁇ phase (delta phase) is suppressed, and coarsening of crystal grains is suppressed.
- delta phase precipitation of hard and brittle ⁇ phase
- coarsening of crystal grains is suppressed.
- mechanical strength is improved by forcibly imparting strain and refining the crystal grains, and when the forging material is treated at such a high temperature, it recovers. And crystal grains become coarse due to recrystallization, and mechanical strength decreases.
- metal powder injection molding method metal powder with a small particle size is sintered and molded, so it is possible to refine crystal grains without forcibly applying strain to the sintered body. It becomes. For this reason, according to the said structure, even if it solution-treats at high temperature like 1050 degreeC or more and 1250 degrees C or less, the coarsening of a crystal grain is suppressed and the fall of mechanical strength is suppressed.
- the solution treatment step (S10) is performed. It may be omitted. This is because in this case, the sintering treatment also functions as a solution treatment in the solution treatment step (S10). Since the aging treatment after the sintering treatment is the same as the aging treatment step (S12) described above, detailed description is omitted.
- FIG. 2 is a diagram showing a configuration of the Ni alloy component 10 applied to the gas turbine.
- a compressor blade that is a gas turbine part is shown as the Ni alloy part 10.
- the compressor blade is a component constituting the air flow path, mechanical strength such as fatigue strength sufficient for vibration is required.
- such a compressor blade is formed into a sintered body by a metal powder injection molding method using a precipitation hardening type Ni alloy powder equivalent to ALLOY 718 (registered trademark), and the above structure is formed into a solution.
- the treatment step (S10) and the aging treatment step (S12) it is possible to produce a compressor blade having improved mechanical strength characteristics such as fatigue strength at a lower cost.
- Ti 0.65 mass% or more and 1.15 mass% or less
- Al 0.20 mass% or more and 0.80 mass% or less
- Cr 17.00 mass% or more and 21.00 mass% %
- Nb 4.75 mass% or more and 5.50 mass% or less
- Mo 2.80 mass% or more and 3.30 mass% or less
- Ni 50.00 mass% or more and 55.00 mass% or less
- a sintered compact formed by sintering precipitation hardened Ni alloy powder composed of Fe and inevitable impurities by a metal powder injection molding method is held at 1050 ° C. or higher and 1250 ° C.
- ⁇ phase (gamma) which is Ni matrix
- ⁇ phase (gamma) which is Ni matrix
- [Ni 3 (Al, Ti )] and mainly gamma 'phase (gamma prime phase) or, [Ni 3 Nb] the mainly gamma "phase (gamma double prime phase) is finely dispersed
- the precipitation of hard and brittle ⁇ phase (delta phase) crystal grain boundaries and the like, and the coarsening of crystal grains due to the growth of crystal grains are suppressed. It is possible to improve mechanical strength such as fatigue strength in the part.
- Ti 0.65 mass% or more and 1.15 mass% or less
- Al 0.20 mass% or more and 0.80 mass% or less
- Cr 17.00 mass% or more and 21.00 mass% or less
- Nb 4.75 mass% or more and 5.50 mass% or less
- Mo 2.80 mass% or more and 3.30 mass% or less
- Ni 50.00 mass% or more and 55.00 mass% or less
- the balance being Fe and Precipitation hardening type Ni alloy powder composed of inevitable impurities was sintered by holding at 1100 ° C. or higher and 1250 ° C.
- the ⁇ phase (gamma prime phase) or ⁇ is contained in the ⁇ phase (gamma phase) which is the Ni matrix.
- Phase (gamma double prime phase) are dispersed finely, and precipitation of hard and brittle ⁇ phase (delta phase) crystal grain boundaries, etc., which lowers mechanical strength, and coarsening of crystal grains due to crystal growth are suppressed. Therefore, it is possible to improve the mechanical strength such as fatigue strength of Ni alloy parts etc.
- the sintering process of the metal powder injection molding method also has a function as a solution treatment, so that the solution treatment Therefore, the manufacturing cost can be reduced.
- a sintered body was formed by a metal powder injection molding method using precipitation hardening Ni alloy powder. About the sintered compact, it shape
- Precipitation hardening type Ni alloy powder and a binder composed of thermoplastic resin and wax were kneaded with a kneader to prepare a kneaded body.
- the kneaded body was injected into a mold by an injection molding machine to form a preformed body.
- the preform was taken out from the mold, and the preform was heated to remove the binder.
- the preform from which the binder had been removed was placed in an atmosphere furnace and heated and sintered in an inert atmosphere to form a sintered body.
- the sintering temperature was 1100 ° C. to 1250 ° C., and the sintering time was 1 hour to 5 hours.
- the cooling from the sintering temperature to room temperature was quenched by air cooling.
- the sintered body was held at 1050 ° C. for 1 hour, and then rapidly cooled to room temperature by cooling with a gas fan and subjected to a solution treatment.
- the solution-treated sintered body is held at 718 ° C. for 8 hours, cooled to 621 ° C. by furnace cooling, then held at 621 ° C. for 8 hours, and cooled to room temperature by gas fan cooling and aging treatment did.
- Example 2 the sintered body was held at 718 ° C. for 8 hours, cooled to 621 ° C. by furnace cooling, then held at 621 ° C. for 8 hours, cooled to room temperature by gas fan cooling, and subjected to aging treatment. . In addition, in the heat processing of Example 2, solution treatment is not performed.
- Example 3 In the test piece of Example 3, after the sintered body was held at 1100 ° C. for 1 hour, it was rapidly cooled to room temperature by gas fan cooling and subjected to a solution treatment. Next, the solution-treated sintered body is held at 718 ° C. for 8 hours, cooled to 621 ° C. by furnace cooling, then held at 621 ° C. for 8 hours, and cooled to room temperature by gas fan cooling and aging treatment did.
- the sintered body was held at 1250 ° C. for 5 hours, and then cooled to room temperature by cooling with a gas fan and subjected to a solution treatment.
- the solution-treated sintered body is held at 718 ° C. for 8 hours, cooled to 621 ° C. by furnace cooling, then held at 621 ° C. for 8 hours, and cooled to room temperature by gas fan cooling and aging treatment did.
- the sintered body was held at 970 ° C. for 1 hour, and then rapidly cooled to room temperature by cooling with a gas fan and subjected to a solution treatment.
- the solution-treated sintered body is held at 718 ° C. for 8 hours, cooled to 621 ° C. by furnace cooling, then held at 621 ° C. for 8 hours, and cooled to room temperature by gas fan cooling and aging treatment did.
- FIG. 3A is a photograph showing the metal structure observation result of the test piece of Comparative Example 1
- FIG. 3B is a photograph showing the metal structure observation result of the test piece of Example 1
- FIG. 3D is a photograph showing the metal structure observation result of the test piece of Example 3
- FIG. 3E is a photograph showing the metal structure observation result of the test piece of Example 4. It is a photograph shown.
- the fatigue test was performed at room temperature and high temperature according to ASTM E466.
- the test temperature was 538 ° C.
- the stress ratio R ⁇ 1 (double swing stress)
- the stress amplitude was 500 MPa to 600 MPa.
- the room temperature fatigue test it implemented about the test piece of the comparative example 1 and Example 2
- the high temperature fatigue test it implemented about the test piece of Example 1 and Example 2.
- FIG. about the thing which does not carry out fatigue fracture with 1 * 10 ⁇ 7 > cycles, the test was stopped at that time.
- FIG. 4 is a graph showing the results of a room temperature fatigue test.
- the horizontal axis represents the number of cycles
- the vertical axis represents the stress amplitude
- the test result of the test piece of Example 2 is represented by a white circle
- the test result of the test piece of Comparative Example 1 is represented by a black triangle.
- the number of cycles is 1 ⁇ 10 7 times and fatigue failure does not occur
- the white circle is indicated by an arrow. It was found that the fatigue characteristics of the test piece of Example 2 were improved compared to the test piece of Comparative Example 1.
- FIG. 5 is a graph showing the results of a high temperature fatigue test.
- the horizontal axis represents the cycle number
- the vertical axis represents the stress amplitude
- the test result of the test piece of Example 1 is represented by a white circle
- the test result of the test piece of Example 2 is represented by a black triangle.
- the number of cycles is 1 ⁇ 10 7 times and fatigue failure does not occur, and an arrow is added to the black triangle.
- high fatigue characteristics were obtained. The reason for this is considered to be that the ⁇ phase (delta phase) is not precipitated in the test pieces of Example 1 and Example 2.
- the mechanical strength such as fatigue strength can be improved, so that it can be applied to a compressor blade of a gas turbine.
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Abstract
Description
析出硬化型Ni合金粉末を用いて金属粉末射出成形法により焼結体を成形した。焼結体については、金属組織観察用及び疲労試験用に各々成形した。析出硬化型Ni合金粉末には、Alloy718(登録商標)粉末を使用した。析出硬化型Ni合金粉末の合金組成については、20.40質量%のCrと、16.40質量%Feと、3.10質量%のMoと、5.20質量%のNbと、1.00質量%のTiと、0.50質量%のAlと、を含み、残部がNiと、0.05質量%のC等の不可避的不純物とにより構成されている。析出硬化型Ni合金粉末には、平均粒径が35μmよりも小さいガスアトマイズ粉末を用いた。
金属粉末射出成形法で成形した焼結体を、各熱処理条件で熱処理して実施例1から4、比較例1の試験片を作製した。なお、焼結体については、いずれの試験片も同じ成形条件で作製したものを使用した。
次に、各熱処理後の試験片について、金属組織観察を行った。なお、金属組織観察については、試験片を埋込樹脂に埋め込んだ後に研磨とエッチィングとを行って、光学顕微鏡により観察した。図3Aは、比較例1の試験片の金属組織観察結果を示す写真であり、図3Bは、実施例1の試験片の金属組織観察結果を示す写真であり、図3Cは、実施例2の試験片の金属組織観察結果を示す写真であり、図3Dは、実施例3の試験片の金属組織観察結果を示す写真であり、図3Eは、実施例4の試験片の金属組織観察結果を示す写真である。
疲労試験については、ASTM E466に準拠して室温と高温とにより行った。室温疲労試験については、応力比R=-1(両振り応力)、応力振幅400MPaから600MPaとした。高温疲労試験については、試験温度538℃、応力比R=-1(両振り応力)、応力振幅500MPaから600MPaとした。なお、室温疲労試験については、比較例1及び実施例2の試験片について実施し、高温疲労試験については、実施例1及び実施例2の試験片について実施した。なお、サイクル数が1×107回で疲労破壊しないものについては、その時点で試験を中止した。
Claims (4)
- Ti:0.65質量%以上1.15質量%以下、Al:0.20質量%以上0.80質量%以下、Cr:17.00質量%以上21.00質量%以下、Nb:4.75質量%以上5.50質量%以下、Mo:2.80質量%以上3.30質量%以下、Ni:50.00質量%以上55.00質量%以下、残部がFe及び不可避的不純物からなる析出硬化型Ni合金粉末を金属粉末射出成形法で焼結させて成形した焼結体を、1050℃以上1250℃以下で1時間から5時間保持した後に、室温まで急冷して溶体化処理する溶体化処理工程と、
前記溶体化処理した焼結体を、600℃以上800℃以下で保持した後に、室温まで冷却して時効処理する時効処理工程と、
を備えるNi合金部品の製造方法。 - 請求項1に記載のNi合金部品の製造方法であって、
前記溶体化処理工程は、前記焼結体を1100℃以上1250℃以下で溶体化処理するNi合金部品の製造方法。 - Ti:0.65質量%以上1.15質量%以下、Al:0.20質量%以上0.80質量%以下、Cr:17.00質量%以上21.00質量%以下、Nb:4.75質量%以上5.50質量%以下、Mo:2.80質量%以上3.30質量%以下、Ni:50.00質量%以上55.00質量%以下、残部がFe及び不可避的不純物からなる析出硬化型Ni合金粉末を金属粉末射出成形法により、1100℃以上1250℃以下で1時間から5時間保持して焼結し、室温まで急冷させて成形した焼結体を、600℃以上800℃以下で保持した後に、室温まで冷却して時効処理する時効処理工程を備えるNi合金部品の製造方法。
- 請求項1から3のいずれか1つに記載のNi合金部品の製造方法であって、
前記Ni合金部品は、ガスタービン部品であるNi合金部品の製造方法。
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