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WO2008072303A1 - Soudage par friction, procédé de production d'une turbine à gaz centrifuge et procédé de production d'un turbo compresseur - Google Patents

Soudage par friction, procédé de production d'une turbine à gaz centrifuge et procédé de production d'un turbo compresseur Download PDF

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Publication number
WO2008072303A1
WO2008072303A1 PCT/JP2006/324658 JP2006324658W WO2008072303A1 WO 2008072303 A1 WO2008072303 A1 WO 2008072303A1 JP 2006324658 W JP2006324658 W JP 2006324658W WO 2008072303 A1 WO2008072303 A1 WO 2008072303A1
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WO
WIPO (PCT)
Prior art keywords
precipitation
strengthened
friction welding
pressure
based alloy
Prior art date
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Ceased
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PCT/JP2006/324658
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English (en)
Japanese (ja)
Inventor
Hideki Tamaki
Manabu Yagi
Yasushi Hayasaka
Masaru Sekihara
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Hitachi Ltd
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Hitachi Ltd
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Priority to PCT/JP2006/324658 priority Critical patent/WO2008072303A1/fr
Priority to JP2008549138A priority patent/JPWO2008072303A1/ja
Publication of WO2008072303A1 publication Critical patent/WO2008072303A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
    • B23K20/129—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding specially adapted for particular articles or workpieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/02—Iron or ferrous alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials
    • B23K2103/26—Alloys of Nickel and Cobalt and Chromium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/20—Manufacture essentially without removing material
    • F05B2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05B2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05B2230/239—Inertia or friction welding

Definitions

  • Friction welding method centrifugal gas turbine manufacturing method, and turbocharger manufacturing method
  • the present invention relates to a method of friction welding a precipitation-strengthened Ni-base alloy deposit and a precipitation-strengthened Ni-base alloy forged material or a precipitation-strengthened Fe-based alloy forged material.
  • the present invention also relates to a method of manufacturing a centrifugal gas turbine in which a turbine wheel and a shaft are formed of these materials, or a turbocharger in which an exhaust side impeller and a shaft are formed of these materials.
  • Precipitation-strengthened Ni-based alloys are used for the exhaust side impellers of turbochargers, which are high-speed rotating bodies, and the turbine bin wheels of centrifugal gas turbines.
  • chrome molybdenum steel tempered material, precipitation-strengthened Ni-base alloy forging or precipitation-strengthened Fe-base alloy forging is used for the shaft that is joined to the exhaust wheel or turbine wheel.
  • the exhaust side impeller or turbine wheel and the shaft are generally joined by friction welding.
  • Precipitation-strengthened alloys are composed of ⁇ 'phase, phase, ⁇ ' in the austenite phase ( ⁇ phase) of Ni or Fe.
  • Precipitation strengthened forging alloys other than Inconel 718 include, for example, Superalloys A Technical Guide second Edition (Attached to MJ Donacnie and bJ Donacme, ASM International al 2002) p4-5, Table 1.1 There are A-286, Nimonic80A, etc. which are listed as Precipitation-hardening alloys.
  • Patent Document 1 Japanese Patent Publication No. 58-19393
  • Patent Document 2 USP3, 720, 509
  • Patent Document 1 describes a method of friction welding a precipitation-strengthened Ni-base alloy alloy713C forged material and a chromium molybdenum steel tempered material. There is a large difference in high-temperature strength between the two materials, so the precipitation-strengthened Ni-based alloy forging material is hardly deformed when bonded by friction welding, and the soft layer formed in the P1 process and the P2 process More than 90% of the burrs discharged in the process are S-chromium-molybdenum steel.
  • Patent Document 1 discloses a method for improving the strength of the joint interface by preventing the carbides in the chromium-molybdenum steel from aligning with the joint interface at this time.
  • the chromium molybdenum steel SCM435 has a weight percentage of 0.
  • SCM440 is a weight 0/0 C: to 0.38 to 0 to 43%
  • precipitation strengthened Ni-based alloy forging AMS5662 is Flip wt%:.. 0 08% or less Because it contains only about 1/10 carbon of chrome-molybdenum steel! / ⁇ , it shouldn't be a big problem!
  • the tempered material is friction welded, whereas in the case of precipitation strengthened Ni-based alloy forgings, the solution heat treatment state (generally hardened) In which the pressure does not exceed 277 with Brinell), and then an aging treatment is employed.
  • the room temperature 0.2% resistance during pressure welding in the solution heat treatment state is 350 to 650 MPa, which is a chrome molybdenum steel tempered material.
  • the room temperature yield stress of SCM440 is lower than 835 MPa or more. This means that when friction welding is performed under the condition of pressure P2 of 500 MPa, in the conventional chrome molybdenum steel tempered material, most of the low-temperature part other than the soft solder layer is in the elastic region, whereas the solution heat treatment state, for example, This means that precipitation-strengthened Ni-base alloy forgings with 0.2% resistance to 450MPa at room temperature enter the plastic region even at low temperatures.
  • the margin of deviation (U) that is, the length of the foreside before welding + the length of the forged material before pressure welding (the product after pressure welding) Total length.
  • the allowance (U) should be the total length reduction due to the soft layer discharge, but if the low temperature part other than the soft layer is also in the plastic zone, the amount of plastic deformation in the low temperature part Is also added to the approaching margin (U).
  • materials have almost no variation in deformation behavior in the elastic region, but the deformation behavior (stress-strain relationship) in the plastic region varies greatly between materials.
  • the dispersion between materials is large in the solution heat treatment state before the final heat treatment.
  • Variation in the margin of allowance (U) due to variations in strength between materials is a major problem in terms of quality assurance of friction welding parts of high-speed rotating bodies such as turbochargers and centrifugal gas turbines.
  • An object of the present invention is to provide a high-V at a stable margin in a method of friction welding a precipitation-strengthened Ni-base alloy deposit and a precipitation-strengthened Ni-base alloy forging or a precipitation-strengthening Fe-base alloy forging. It is intended to provide a friction welding method that can obtain joint strength and is extremely effective in improving the quality of the friction welding portion of a high-speed rotating body such as a turbo charger or a centrifugal gas turbine.
  • the present invention relates to a friction welding method of a precipitation strengthened Ni-based alloy forged material and a precipitation strengthened Ni-based alloy forged material or a precipitation strengthened Fe-based alloy forged material. Physically, it is characterized by a solution heat treatment and an aging treatment to increase the strength, and then applying friction welding by applying a two-stage joining pressure.
  • the present invention provides a relative relationship between one material made of precipitation-strengthened Ni-based alloy forging and the other material made of precipitation-strengthened Ni-based alloy forging or precipitation-strengthened Fe-based alloy forging.
  • the friction pressure welding method in which friction pressure welding is performed by applying pressure P1 while rotating to generate frictional heat on the contact surface, and then joining with the higher pressure P2 being applied.
  • the 0.2% resistance is increased to 700 MPa or more so that the force can be joined, and the pressure P2 is set to at least 500 MPa.
  • the present invention provides a relative relationship between one material made of precipitation-strengthened Ni-based alloy forging and the other material made of precipitation-strengthened Ni-based alloy forging or precipitation-strengthened Fe-based alloy forging.
  • the elastic limit stress of the two materials is the pressure. It is characterized in that heat treatment is performed so as to be higher than P2, the force is bonded, and the pressure P2 is at least 500 MPa.
  • the present invention relates to a turbine wheel that also serves as a precipitation-strengthened Ni-based alloy material and a shaft that comprises a precipitation-strengthened Ni-based alloy forged material or a precipitation-strengthened Fe-based alloy forged material by friction welding.
  • a turbine wheel that also serves as a precipitation-strengthened Ni-based alloy material
  • a shaft that comprises a precipitation-strengthened Ni-based alloy forged material or a precipitation-strengthened Fe-based alloy forged material by friction welding.
  • the 0.2% resistance in the range of ° C is set to at least 700MPa, and friction friction welding is performed, and in the friction welding process, pressure P1 is applied while the turbine wheel and the shaft are rotated relative to each other to contact the surface. Then, frictional heat is generated, and then bonding is performed under a pressure of at least 500 MPa higher than the pressure P1.
  • the present invention relates to an exhaust side impeller made of a precipitation-strengthened Ni-base alloy and a shaft made of a precipitation-strengthened Ni-base alloy forging or a precipitation-strengthened Fe-base alloy forging by a friction welding method.
  • the temperature of the precipitation strengthened Ni-based alloy metal and the precipitation-strengthened Ni-based alloy forging or precipitation-strengthened Fe-based alloy forging is 650 ° C.
  • Friction welding is performed after setting the 0.2% resistance in the range of at least 700 MPa, and pressure P1 is applied while relatively rotating the exhaust-side impeller and the shaft in the friction welding process. Then, friction heat is generated, and then joining is carried out under a pressure of at least 500 MPa higher than the pressure P1.
  • a stable joint and a high joint are obtained.
  • High joint strength with a strength, for example, room temperature notch tensile strength of 1700 MPa or more can be obtained.
  • the reliability of high-speed rotating bodies such as turbochargers and centrifugal gas turbines can be greatly improved.
  • FIG. 1 is a diagram showing the relationship between stress and strain of a precipitation strengthened alloy forging.
  • FIG. 2 is a schematic diagram showing the shape of a notch specimen for evaluating the strength of a joint.
  • FIG. 3 A diagram showing the relationship between notch tensile strength and offset.
  • FIG. 5 is a schematic diagram showing a shape of a centrifugal gas turbine before pressure contact between a turbine wheel and a shaft.
  • FIG.6 Shows the shape of a centrifugal gas turbine after pressure contact between the turbine wheel and shaft Schematic diagram.
  • FIG. 7 is a schematic view showing a shape before pressure contact between a turbine wheel and a shaft in a centrifugal gas turbine, wherein the shaft is processed into a stepped shape.
  • the precipitation-strengthened Ni-base alloy forged material or the precipitation-strengthened Fe-based alloy forged material side is also formed in as many portions as possible except for the soft soot layer generating portion.
  • the maximum pressure stress must be within the elastic stress range. In order to obtain high joint strength, a large pressure stress is required.
  • it is effective to use two materials to be joined in friction welding with strength ranging from room temperature to 650 ° C, specifically 0.2% resistance to 700 MPa or more. It is. It is also effective to set the pressure P2 to 500 MPa or more. In order to increase the 0.2% resistance in the range from room temperature to 650 ° C to 700 MPa or more, it is desirable to perform solution heat treatment and aging treatment.
  • both of the two materials are at least in most areas except the soft layer, that is, during pressure contact.
  • the portion where the temperature is in the range from room temperature to 500 ° C. can be within the elastic stress range.
  • a deposit made of precipitation-strengthened Ni-base alloy and a forging material made of precipitation-strengthened Ni-base alloy or precipitation-strengthened Fe-base alloy In the case of friction welding, it is desirable that the room temperature notch bow I tensile strength of notch tensile specimens taken from the joint and notched in the joint is 1700 MPa or more. By making the joint room temperature notch tensile strength high in this way, the number of start / stop operations as a product increases, and even when a high load is applied to the joint, it can withstand. In order to obtain room temperature notch tensile strength of 1700 MPa or more, it is desirable that the allowance (U) is 14 mm or more.
  • the friction welding method of the present invention requires a high-strength material to cope with high-speed rotation at high temperatures, and is a turbine wheel that also serves as a precipitation-strengthened Ni-based alloy material for centrifugal gas turbines. Therefore, it is suitable as a method for joining shafts that also become precipitation-strengthened Ni or Fe-based alloy forging materials.
  • the friction welding method of the present invention includes an exhaust side impeller made of a precipitation-strengthened Ni-based alloy in a high-speed turbo charger and a shaft made of a precipitation-strengthened Ni or Fe-based alloy forging. It is also suitable as a method of joining the two.
  • the turbine wheel made of precipitation-strengthened Ni-based alloy material has a Ni content of 50% or more by weight%, C: 0.05-0.3%, B: 0.01 ⁇ 0.05%, Hf: 0.5 ⁇ 3.0%, Co: 8 ⁇ 18%, Ta: 3 ⁇ 8.5%, Cr: l .5 ⁇ 16%, Mo: 0 ⁇ l%, W: 5 ⁇ 15% , Ti: 0 ⁇ l.5%, A1: 4.5 ⁇ 5.8%, Nb: 0 ⁇ 2%, Re: 0 ⁇ 6%, V: 0 ⁇ 1%, Zr: 0 ⁇ 0.01%, Pt or platinum group element 1 type or a combination of 2 or more types: 0 to 2%, Y or a combination of 1 or 2 types of rare earth elements: 0 to 2%, a combination of 1 type or 2 types of Mg or alkaline earth metals
  • the turbine wheel made of precipitation-strengthened Ni-based alloy material is 50% Ni or more by weight, C: 0.1 to 0.3%, B: 0.016-0.05%, Hf: l. 3-3.0%, Co: 10.2-18%, Ta: 3-5%, Cr: 1.
  • the composition is 0 to 5% or less.
  • the turbine wheel is made of Ni by weight of 50% or more, C: 0.1 to 0.3%, B: 0.016 to 0.05%, Hf: l.3 to 3.0%, Co: 10.2 to 18%, Ta: 2.8 ⁇ 4.7%, Cr: l.5 ⁇ 16%, Mo: 0 ⁇ l%, W: 9 ⁇ 15%, Ti: 0 ⁇ l%, Al: 5 ⁇ 5.8%, Nb: 0 ⁇ 2%, Re : It is preferable that the yarn is composed of 0.2 to 6%, V: 0.15% or less, and Zr: 0.03 to 0.08%.
  • a turbine wheel that also serves as a precipitation-strengthened Ni-based alloy freight and a shaft that also serves as a precipitation-strengthened Ni- or Fe-based alloy forging material are each heat-treated, so that the room temperature force is within a range of 650 ° C.
  • the cutting amount of the shaft due to the mechanical cage is large, such as a stepped shaft, the friction welding surface of the shaft, the radial machining allowance and the axial machining allowance are set, and the Brinell hardness is 277.
  • the shaft and the turbine wheel are processed in a state that does not exceed that of the solution heat treatment, and then the 0.2% proof stress in the range from room temperature to 650 ° C is adjusted to 700 MPa or more by heat treatment. After bonding, it is effective to heat-treat for 2 to 8 hours in the range of 600 ° C force and 800 ° C, and then check the final shape.
  • the AMS5662 standard stipulates that the Brinell hardness of the solution material should not exceed 277.
  • the heat treatment was solution heat treatment with 1200 ° CZ2hZAr gas cooling in vacuum after fabrication, followed by two-stage aging treatment (1080 ° CZ4hZAr gas cooling in vacuum + 871 ° CZ20hZAr gas cooling in vacuum).
  • Table 1 shows the pressure welding conditions
  • Tables 2 and 3 show the tensile properties and joining results of the materials.
  • Precipitation strengthened alloy forging AMS5662 standard material Precipitation strengthened alloy forging elastic limit Pa 242-490 902- 1000 Precipitation strengthened alloy forging 0.2 3 ⁇ 4 MPa resistance 378 to 628 1 138-1187 Primary stress P1 (MPa) 150
  • the precipitation strengthening type alloy forging material those shown in Table 2 using lots A to C having an elastic limit at room temperature of 242 to 490 MPa and a 0.2% proof stress S378 to 628 MPa are the conventional technologies.
  • the present invention is shown in Table 3 using lots D to F prepared by applying an aging heat treatment to this and adjusting the elastic limit to 902 to 1000 MPa and 0.2% strength to 1138 to 1187 MPa.
  • FIG. 1 is a stress strain diagram at room temperature of the AMS5662 material used for this pressure welding.
  • the materials (D), (E), and (F) are elastic regions in the range up to about 900 MPa. Therefore, even when the secondary stress P2 is increased to 600 MPa, the deformation in the low temperature region other than the softened layer is basically released after unloading. ) Is not added. Therefore, in the method of the present invention, the variation in the margin of allowance (U) is greatly reduced.
  • a notch specimen having the shape shown in FIG. 2 was taken from the radial center of the joint.
  • Fig. 2 (a) is an overall view of the notched specimen
  • Fig. 2 (b) is a detailed view of part A.
  • materials (A) to (C ) Prior to specimen collection, materials (A) to (C ) was heated at 720 ° C for 8 hours, then cooled to 625 ° C in 2 hours, and then heated at 625 ° C for 8 hours.
  • the above heat treatment was simplified, heated at 720 ° C for 2 hours, cooled to 625 ° C in 1 hour, and further heated at 625 ° C for 2 hours.
  • the reason for simplifying the heat treatment is that materials (D) to (F) are already subjected to aging treatment before pressure welding! This is because it is only necessary to reprecipitate the precipitate phase in a part, that is, a slight heat-affected zone near the bonding interface.
  • the effect of simplified heat treatment was confirmed by measuring the hardness near the interface. Immediately after welding, the partial force softened from 220 to 280 in picker hardness. By simplified heat treatment, it is 420 to 500 in Vickers hardness, which is equivalent to the part that is affected by frictional heat during welding. It was recovered to.
  • notched specimen having the shape shown in FIG. 2 was used because the strength after the aging treatment is higher than that of precipitation strengthened Ni-based alloy porcelain in the AMS5662 material. This is because, if a piece is used, it breaks at the smooth part on the precipitation-strengthened Ni-base alloy porcelain side, and an accurate comparison of joint strength cannot be made.
  • Tables 2 and 3 show the evaluation results of the notch tensile strength.
  • a general screw type tensile tester was used, and the temperature was set to room temperature.
  • Notch tensile strength is the load at break divided by the cross-sectional area of the notch. From this result, in the conventional technology, the notch tensile strength of the joint was 1679 MPa at the maximum, but in the case of the present invention, it was at least 1769 MPa, and the variation was greatly reduced. Recognize.
  • FIG. 3 shows the relationship between the margin (U) and the notch tensile strength of the joining test piece according to the prior art and the present invention. It can be seen that the product of the present invention has an excellent joint strength with little variation in the shift margin (U). In addition, it can be seen from Fig. 3 that the greater the margin (U), the higher the notch tensile strength, that is, the joint strength.
  • the secondary stress P2 has already exceeded the room temperature elastic limit on the precipitation-strengthened Ni-base alloy forging material side, so the secondary stress is further increased and the offset margin (U) is increased. It is difficult to increase the bonding strength.
  • Fig. 4 shows a cross-sectional macro photograph of the joint portion of the conventional technique and the present invention, (a) is the present invention, and (b) is the prior art.
  • the softening layer discharge angle indicated by 0 in the figure is the angle between the outer diameter before bonding and the discharged soft soot phase, and is on the precipitation strengthened Ni-base alloy forging side. Depends on material strength.
  • the joint specimen of the present invention has almost no change in outer diameter except at the discharge part. This means that most of the parts other than the softened layer were within the elastic deformation range at the time of pressure welding, and it is a typical joint shape of a pressure welded product with little variation in the margin (U). on the other hand
  • the outer diameter change of the joining test piece according to the prior art is observed even at a portion other than the discharge portion. This means that plastic deformation also occurred in the parts other than the softened layer, and the variation in the margin (U) is large! /, Which is a typical joint shape of the welded product.
  • a 0.2% proof stress in the range of 650 ° C at room temperature is 700 MPa by heat treating the forging material. It is preferable to prepare so that it becomes the above.
  • the precipitation-strengthened Ni-based alloy porridge is higher in strength at a higher temperature than in the case of Example 1, in weight percent C: 0.13 to 0.23%, B: 0.013 to 0.00. 023%, Hf: l. 4 to 2.2%, Co: 10 to ll%, Ta: 3.5 to 5%, Cr: 6 to 8%, Mo: 0.1 to 1%, W: 11 to 12. 5%, Nb: 0.5 to 1%, Re: l. 2 to 1.5%, A1: 5 to 5.5%, Zr: 0.005 to 0.0015%, Residual force Ni A Ni-based superalloy composed of inevitable impurities was used, and friction welding was performed according to the method of the present invention.
  • the material on the porcelain side is a 47 mm ⁇ X lOOmmL round bar, as in Example 1. (1080 ° CZ4hZAr gas cooling in vacuum + 87 lCZ20hZAr gas cooling in vacuum).
  • the precipitation-strengthened Ni-based alloy forging is the same as in Example 1 and is heated to 720 ° C for 8 hours on a solution heat-treated material based on the AMS5662 standard, and then cooled to 625 ° C in 2 hours. Furthermore, it is an aging material that has been heat-treated at 25 ° C for 8 hours, and the shape is 47mm ⁇ X 150mmL round A stick.
  • the pressure contact conditions were the same as in Example 1, with a primary stress P1 of 150 MPa and a secondary stress P2 of 6 OOMPa.
  • Table 4 shows the results of pressure welding and the evaluation results of notch bow I tension strength by the same method as in Example 1.
  • Example 4 After heating for an hour, it was cooled to 625 ° C in 1 hour and further heated at 625 ° C for 2 hours. From the results shown in Table 4, it is evident that even in this combination of materials, the same high joint strength as in Example 1 can be obtained.
  • the room-temperature inertia limit stress on the steel side is 686 MPa, so the secondary stress P2 is made higher than 600 MPa, and more than that, the offset margin (U) is increased. It's difficult to make it bigger.
  • the combination of materials shown in Table 4 has a room temperature elastic limit stress of 800MPa on the skeleton side, and it is possible to improve the joint strength by further increasing the secondary stress P2.
  • Example 1 Based on the test results of Example 1, a centrifugal turbine wheel having an axial length of about 120 mm, a blade part diameter of about 225 mm, and a pressure contact part diameter of 50 mm and a diameter of 50 mm ⁇ X length by the friction welding method of the present invention.
  • a 700mm shaft was joined.
  • Turbine wheel, C by weight 0/0:. 0 14% , B:. 0 015%, Hf:. L 54%, Co: 9. 99%, Ta: 3. 03%, Cr: 8. 33% , Mo: 0.71%, W: 9.98%, Ti: l. 01%, A1: 5.59%, the balance being a Ni-based superalloy made of Ni and inevitable impurities.
  • This alloy was subjected to solution heat treatment with 1200 ° CZ2hZAr gas cooling in vacuum, followed by two-stage aging treatment (1080 ° CZ4hZAr gas cooling in vacuum + 871 ° CZ20hZAr gas cooling in vacuum) after fabrication.
  • the shaft was an aged material obtained by heating a solution heat treatment material based on the AMS5662 standard at 720 ° C for 8 hours, cooling to 625 ° C in 2 hours, and then heating at 625 ° C for 8 hours.
  • the pressure welding conditions were a primary stress P1 of 150 MPa and a secondary stress P2 of 600 MPa.
  • the shift margin (U) was the joint test. It was 14.6 mm, almost the same as the piece.
  • the length X plastic strain is added to the shift margin (U) as the amount of plastic deformation, and changes in the material length affect the shift margin (U).
  • most of the portions other than the soft heel layer are in the elastic region, and therefore, the change in the material length hardly affects the amount of deviation (U). This is extremely effective in terms of setting conditions and quality control.
  • the friction welding method of the present invention is also effective in the shape of the actual machine, and is a turbine wheel made of precipitation-strengthened Ni-based alloy and a shaft made of precipitation-strengthened Ni or Fe-based alloy forging. It was found that this method is suitable as a method of joining the two.
  • FIG. 5 shows a shape of the centrifugal wheel 1 before the press contact of the turbine wheel 1 and the shaft 2 of the centrifugal gas turbine.
  • the turbine wheel is manufactured by forging.
  • the above heat treatment is performed before pressure welding, and then the pressure receiving surface and the joint surface are processed.
  • the shaft is a forged material, and after the heat treatment described above, the outer diameter processing, pressure receiving surface and joint surface processing are performed.
  • pressure welding after heating at 720 ° C for 2 hours, cooling to 625 ° C in 1 hour, heat treatment at 625 ° C for 2 hours, and then processing the shaft side into the shape shown in Fig. 6 .
  • Fig. 6 shows a shape of the centrifugal wheel 1 before the press contact of the turbine wheel 1 and the shaft 2 of the centrifugal gas turbine.
  • the turbine wheel is manufactured by forging.
  • the above heat treatment is performed before pressure welding, and then the pressure receiving surface and the joint surface are processed.
  • the shaft is a forged material, and after the heat
  • the shaft side is processed into the shape shown in Fig. 7 at the solution heat treatment stage, then heated at 720 ° C for 8 hours, then cooled to 625 ° C in 2 hours, and further heated at 625 ° C for 8 hours. Treated.
  • the stepped portion of this shaft was used as the pressure-receiving surface on the shaft side, and the primary stress P1 was 150 MPa and the secondary stress P2 was 600 MPa.
  • the processing after the heat treatment was an outer diameter processing of about 2 mm in diameter and Only full length adjustment was used.
  • the amount of cutting from the shape of FIG. 5 on the conventional shaft side to the shape of FIG. 6 can be carried out in a solution state where the material is easy to work! ⁇ (low hardness!) This has made it possible to significantly reduce costs by prolonging the replacement cycle of consumables for machining and shortening the cutting time.
  • a high-strength material can be applied to a turbocharger and a centrifugal gas turbine, and an effect of improving efficiency is expected.

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  • Supercharger (AREA)
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  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé dans lequel une coulée d'alliage à base de Ni durci par précipitation et soit un forgeage d'alliage à base de Ni durci par précipitation, soit un forgeage d'alliage à base de Fe durci par précipitation sont soumis à un soudage par friction, tout en appliquant des pressions dans les deux étapes, à savoir, une pression (P1) et une pression supérieure (P2). Le procédé peut atteindre une résistance de soudure élevée et atteindre une réduction de la fluctuation de distance de refoulement. Les deux matériaux devant être soudés sont soumis à un traitement thermique de solution et à un traitement de vieillissement de façon à conduire à une résistance à la charge d'épreuve de 0,2 % à une température se situant dans la plage de la température ambiante à 650°C de 700 MPa ou plus. Ensuite, un soudage par friction est effectué, tout en régulant la pression (P2) pendant le soudage à 500 MPa ou plus. Ainsi, une résistance de soudure de 1.700 MPa ou plus en termes de résistance à la traction à la température ambiante sur pièce entaillée est obtenue.
PCT/JP2006/324658 2006-12-11 2006-12-11 Soudage par friction, procédé de production d'une turbine à gaz centrifuge et procédé de production d'un turbo compresseur Ceased WO2008072303A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/JP2006/324658 WO2008072303A1 (fr) 2006-12-11 2006-12-11 Soudage par friction, procédé de production d'une turbine à gaz centrifuge et procédé de production d'un turbo compresseur
JP2008549138A JPWO2008072303A1 (ja) 2006-12-11 2006-12-11 摩擦圧接方法、遠心式ガスタービンの製造方法及びターボチャージャーの製造方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2006/324658 WO2008072303A1 (fr) 2006-12-11 2006-12-11 Soudage par friction, procédé de production d'une turbine à gaz centrifuge et procédé de production d'un turbo compresseur

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WO2008072303A1 true WO2008072303A1 (fr) 2008-06-19

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017046851A1 (fr) * 2015-09-14 2017-03-23 三菱日立パワーシステムズ株式会社 Procédé de fabrication d'aubes de rotor de turbine
WO2018148110A1 (fr) * 2017-02-08 2018-08-16 Borgwarner Inc. Nouveaux alliages pour composants de turbocompresseur
EP3401050A1 (fr) * 2017-05-11 2018-11-14 United Technologies Corporation Traitement thermique et libération des contraintes pour alliages de nickel soudé à l'état solide
EP3578865A1 (fr) 2018-06-07 2019-12-11 Rolls-Royce plc Cardans et procédés de fabrication de cardans
CN111485154A (zh) * 2020-04-16 2020-08-04 北京北冶功能材料有限公司 一种屏蔽材料用低烧结温度钨镍铁合金
CN116043003A (zh) * 2023-01-31 2023-05-02 天津大学 一种惯性摩擦焊发动机叶盘焊缝的摩擦挤压强化方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6444291A (en) * 1987-08-12 1989-02-16 Kobe Steel Ltd Production of turbine wheel
JPH06106366A (ja) * 1992-09-25 1994-04-19 Daido Steel Co Ltd 摩擦圧接中空バルブの製造方法
JPH10298663A (ja) * 1997-04-23 1998-11-10 Daido Steel Co Ltd 異種金属材の接合熱処理方法
JP2002371801A (ja) * 2001-03-23 2002-12-26 Alstom (Switzerland) Ltd ターボ機械用ロータ及び該ロータの製作法
JP2003041903A (ja) * 2001-04-17 2003-02-13 United Technol Corp <Utc> ブレード一体型ローターの製造方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6444291A (en) * 1987-08-12 1989-02-16 Kobe Steel Ltd Production of turbine wheel
JPH06106366A (ja) * 1992-09-25 1994-04-19 Daido Steel Co Ltd 摩擦圧接中空バルブの製造方法
JPH10298663A (ja) * 1997-04-23 1998-11-10 Daido Steel Co Ltd 異種金属材の接合熱処理方法
JP2002371801A (ja) * 2001-03-23 2002-12-26 Alstom (Switzerland) Ltd ターボ機械用ロータ及び該ロータの製作法
JP2003041903A (ja) * 2001-04-17 2003-02-13 United Technol Corp <Utc> ブレード一体型ローターの製造方法

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107849672A (zh) * 2015-09-14 2018-03-27 三菱日立电力系统株式会社 涡轮动叶片的制造方法
RU2689307C1 (ru) * 2015-09-14 2019-05-27 Мицубиси Хитачи Пауэр Системс, Лтд. Способ изготовления лопатки ротора турбины
RU2689307C9 (ru) * 2015-09-14 2019-10-17 Мицубиси Хитачи Пауэр Системс, Лтд. Способ изготовления лопатки ротора турбины
WO2017046851A1 (fr) * 2015-09-14 2017-03-23 三菱日立パワーシステムズ株式会社 Procédé de fabrication d'aubes de rotor de turbine
US11214852B2 (en) 2017-02-08 2022-01-04 Borgwarner Inc. Alloys for turbocharger components
WO2018148110A1 (fr) * 2017-02-08 2018-08-16 Borgwarner Inc. Nouveaux alliages pour composants de turbocompresseur
EP3401050A1 (fr) * 2017-05-11 2018-11-14 United Technologies Corporation Traitement thermique et libération des contraintes pour alliages de nickel soudé à l'état solide
US11826849B2 (en) 2017-05-11 2023-11-28 Rtx Corporation Heat treatment and stress relief for solid-state welded nickel alloys
US10946476B2 (en) 2017-05-11 2021-03-16 Raytheon Technologies Corporation Heat treatment and stress relief for solid-state welded nickel alloys
EP3578865A1 (fr) 2018-06-07 2019-12-11 Rolls-Royce plc Cardans et procédés de fabrication de cardans
US11136893B2 (en) 2018-06-07 2021-10-05 Rolls-Royce Plc Gimbals and methods of manufacturing gimbals
CN111485154A (zh) * 2020-04-16 2020-08-04 北京北冶功能材料有限公司 一种屏蔽材料用低烧结温度钨镍铁合金
CN116043003A (zh) * 2023-01-31 2023-05-02 天津大学 一种惯性摩擦焊发动机叶盘焊缝的摩擦挤压强化方法
CN116043003B (zh) * 2023-01-31 2024-04-09 天津大学 一种惯性摩擦焊发动机叶盘焊缝的摩擦挤压强化方法

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