WO2019117865A1 - Procédé, système et appareil destinés à être utilisés dans la fabrication additive d'un élément de superalliage à l'aide d'un soudage par impulsions magnétiques - Google Patents

Procédé, système et appareil destinés à être utilisés dans la fabrication additive d'un élément de superalliage à l'aide d'un soudage par impulsions magnétiques Download PDF

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Publication number
WO2019117865A1
WO2019117865A1 PCT/US2017/065785 US2017065785W WO2019117865A1 WO 2019117865 A1 WO2019117865 A1 WO 2019117865A1 US 2017065785 W US2017065785 W US 2017065785W WO 2019117865 A1 WO2019117865 A1 WO 2019117865A1
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WO
WIPO (PCT)
Prior art keywords
superalloy
flyer plate
successive
layer
coating
Prior art date
Application number
PCT/US2017/065785
Other languages
English (en)
Inventor
Gerald J. Bruck
Original Assignee
Siemens Energy, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Energy, Inc. filed Critical Siemens Energy, Inc.
Priority to PCT/US2017/065785 priority Critical patent/WO2019117865A1/fr
Publication of WO2019117865A1 publication Critical patent/WO2019117865A1/fr

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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
    • B23K20/06—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of high energy impulses, e.g. magnetic energy
    • 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
    • B23K20/16—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating with interposition of special material to facilitate connection of the parts, e.g. material for absorbing or producing gas
    • 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
    • B23K20/22—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded
    • B23K20/233—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer
    • 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
    • B23K20/24—Preliminary treatment
    • 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
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • 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

Definitions

  • the present invention relates generally additive manufacturing using
  • Additive manufacturing is a process that builds up a component on a layer by layer basis.
  • Each layer is generally very thin, for example, between 20 to 100 pm.
  • a component is deposited on a working surface i.e. the build plate for the first layer and the previously deposited surface for subsequent layers.
  • Energy from a heat source such as lasers, electron beams and arcs, is directed onto pre-spread powder following a cross sectional area shape of the component to create a layer of the component, which then becomes a new working surface for a next layer.
  • Superalloys can be used for applications in which high mechanical strength and corrosion resistance is required at high temperatures such as, for gas turbine blades.
  • superalloy components are generally considered to be difficult to weld due to their tendency to crack during solidification or upon reheating following the melting process.
  • a precise geometric control of deposited material is also limited by size and shape of solidifying weld puddle. Thin layers and narrow passes, for
  • using additive manufacturing with selective laser melting may help improve precision but deposition is slow and micro structure is necessarily very fine and
  • Magnetic pulse welding is a solid-state welding process that may achieve metallic bonding through plastic deformation and without melting or with just incipient localized melting at adjoining weld interface.
  • a solid-state welding process may offer a potential to avoid cracking on superalloys associated with additive manufacturing melting and solidification.
  • a solid-state welding process may provide opportunities to manufacture a superalloy component having fine geometric details and to control both micro structure and composition on a layer by layer basis of the superalloy component.
  • Magnetic pulse welding may require materials to be welded having an excellent electrical conductivity to generate enough Lorentz forces and an excellent fracture toughness to withstand the necessary forces for bonding.
  • superalloys typically have poor electrical conductivity and poor fracture toughness.
  • aspects of the present invention relate to additive manufacturing of a superalloy component using magnetic pulse welding.
  • a process for additive manufacturing a superalloy component using magnetic pulse welding comprises providing a coil.
  • the process comprises providing a superalloy base substrate.
  • the process comprises providing a superalloy flyer plate comprising a conductive coating applied on one surface and a fracture tough and ductile coating applied on another surface.
  • the process comprises arranging the superalloy flyer plate between the coil and the superalloy base substrate in a way such that the conductive coating is adjacent to the coil and the fracture tough and ductile coating is adjacent to the superalloy base substrate.
  • the process comprises building up an additive layer on a top of the superalloy base substrate by welding the superalloy flyer plate to the superalloy base substrate using the magnetic pulse welding.
  • the fracture tough and ductile coating of the superalloy flyer plate is ejected during the magnetic pulse welding.
  • a system for additive manufacturing a superalloy component using magnetic pulse welding comprises a coil.
  • the system comprises a superalloy base substrate.
  • the system comprises a superalloy flyer plate comprising a conductive coating applied on one surface and a fracture tough and ductile coating applied on another surface.
  • the superalloy flyer plate is arranged between the coil and the superalloy base substrate in a way such that the conductive coating is adjacent to the coil and the fracture tough and ductile coating is adjacent to the superalloy base substrate.
  • An additive layer is built up on a top of the superalloy base substrate by welding the superalloy flyer plate to the superalloy base substrate using the magnetic pulse welding.
  • the fracture tough and ductile coating of the superalloy flyer plate is ejected during the magnetic pulse welding.
  • an apparatus to be used for additive manufacturing a superalloy component using magnetic pulse welding comprises a superalloy flyer plate comprising a conductive coating applied on one surface and a fracture tough and ductile coating applied on another surface.
  • FIG. 1 illustrates a schematic diagram of a system for magnetic pulse welding, in which an embodiment of the invention may be incorporated;
  • FIG. 2 illustrates a schematic diagram of a conventional magnetic pulse welding process
  • FIGs. 3 to 5 illustrate schematic diagrams of a process for additive manufacturing a superalloy component using a magnetic pulse welding according to an embodiment of the invention.
  • FIG. 1 illustrates a schematic diagram of a system 100 for magnetic pulse welding. Embodiments of the invention may be incorporated in the system 100.
  • the system 100 includes a pulse generator 110.
  • the pulse generator 110 contains a capacitor bank 112 and a discharge switch 114 that are connected to each other.
  • the system 100 includes a coil 120.
  • the coil 120 is connected to the pulse generator 110.
  • a base plate 220 and a flyer plate 230 are to be welded together.
  • the base plate 220 and the flyer plate 230 are arranged in the system 100 with a gap 234 relative to each other before welding.
  • the base plate 220 may be supported on a fixture 130.
  • the flyer plate 230 contains high electrical conductive material and is arranged between the base plate 220 and the coil 120.
  • FIG. 2 illustrates a schematic diagram of a conventional magnetic pulse welding process 200.
  • the magnetic pulse welding process 200 starts with charging the capacitor bank 112 by a high-voltage power source (not shown).
  • the discharge switch 114 is closed once the capacitor bank 112 is charged to a required energy level.
  • the pulse generator 110 generates a high intensity electrical current in short pulses.
  • the high intensity electrical current flowing from the capacitor bank 112 through the coil 120 generates an intense magnetic field in the flyer plate 230 which generates a significantly large Lorentz force.
  • the Lorentz force accelerates the flyer plate 230 at a very high speed which cause a plastic deformation on the flyer plate 230 and collides onto the base plate 220.
  • a solid-state weld 240 is then created between the base plate 220 and the flyer plate 230 by the collision.
  • a jet of materials 250 such as, oxidation, dirt and other contaminants at contact surface of the collision, may be expelled due to the high speed collision. Such expulsion may be made more effective and directed with the flyer plate 230 at slight angle (e.g. less than a few degrees) to surface of the base plate 220.
  • Skin depth is a depth through which interaction of the magnetic coil field and induced magnetic field in the flyer plate 230 is limited within the flyer plate 230.
  • the interaction of the magnetic coil field and induced magnetic field in the flyer plate 230 is the source of the Lorentz force.
  • Skin depth is highest at a surface of the flyer plate 230 and decays exponentially with depth within the flyer plate 230. The most efficient bonding may be obtained when the skin depth equals to a thickness of the flyer plate 230. Skin depth is generally high for high resistance materials and low for low resistance materials.
  • the flyer plate 230 needs to have an excellent electrical conductivity to generate the sufficient Lorentz force for bonding the base plate 220 and the flyer plate 230.
  • a higher electrical conductivity of the flyer plate 230 generates a stronger Lorentz force and decreases a skin depth of the flyer plate 230.
  • the base plate 220 and the flyer plate 230 need to have excellent fracture toughness to withstand the large Lorentz force for bonding.
  • the magnetic pulse welding process 200 produces a solid-state weld 240 through plastic deformation without melting or just beginning of localized melting at adjoining weld interface between the base plate 220 and the flyer plate 230.
  • the magnetic pulse welding process 200 may be used for welding superalloy components due to their heat sensitive property and tendency to crack during solidification and reheating.
  • a magnetic pulse welding process 200 may be used to build up additively manufactured superalloy components.
  • superalloy components have poor electrical conductivity and poor fracture toughness.
  • the poor electrical conductivity of superalloy components may not generate the required Lorentz force for bonding.
  • the poor fracture toughness of superalloy components may not be sufficient to withstand the necessary Lorentz force for bonding.
  • the magnetic pulse welding process 200 may not be applicable for welding superalloy components without modifications.
  • FIGs. 3 to 5 illustrate schematic diagrams of a process 300 for additive manufacturing a superalloy component 310 using magnetic pulse welding according to an embodiment of the invention.
  • the superalloy component 310 includes a superalloy base substrate 320 and an additive layer 322.
  • the additive layer 322 is built up by welding a suprealloy flyer plate 330 on a top of the superalloy base substrate 320 with a solid-state weld 240.
  • the suprealloy flyer plate 330 is arranged between the coil 120 and the superalloy base substrate 320.
  • a coating 332 is applied on one surface of the superalloy flyer plate 330 that is adjacent to the coil 120.
  • the coating 332 consists of a high conductivity material that is sufficient to generate an effective Lorentz force to accelerate the superalloy flyer plate 330 for bonding the superalloy flyer plate 330 to the superalloy base substrate 320 by a solid-state weld 240.
  • the high conductivity material in the coating 332 may include, for example, silver, silver alloy, copper, copper alloy, aluminum, aluminum alloys, etc.
  • the conductive coating 332 may be sufficiently thick to capture majority of skin depth in the superalloy flyer plate 330. Higher conductivity material in the coating 332 may require a thinner thickness of the coating 332.
  • the conductive coating 332 may be sufficiently thin to be ejected along with the jet of material 250 during the magnetic pulse welding. For example, thickness of the conductive coating 332 may be in an order of 50 pm for high conductive material, such as silver or silver alloy.
  • Thickness of the conductive coating 332 may be in an order of 200 pm for high conductive material, such as copper or copper alloy. Thickness of the conductive coating 332 may be in an order of 400 pm for high conductive material, such as aluminum or aluminum alloy.
  • a coating 334 is applied on another surface of the superalloy flyer plate 330 that is adjacent to the superalloy base substrate 320.
  • the coating 334 consists of fracture tough and ductile material that is sufficient to absorb and minimize a collision impact between the superalloy flyer plate 330 and the superalloy base substrate 320.
  • the fracture tough and ductile coating 334 protects the superalloy flyer plate 330 and the superalloy base substrate 320 from fracture.
  • the fracture tough and ductile material in the coating 334 may include, for example, copper, copper alloy, aluminum, aluminum alloys, etc.
  • the fracture tough and ductile coating 334 may be sufficiently thick to withstand the impact of the required Lorentz force that accelerates the superalloy flyer plate 330 to collide with the superalloy base substrate 320 for bonding.
  • the fracture tough and ductile coating 334 may be sufficiently thin to be ejected along with the jet of material 250 during the magnetic pulse welding.
  • thickness of the fracture tough and ductile coating 334 may be in an order of 50 pm, 100 pm, or 150 pm, etc.
  • a softening layer 336 may be applied on one surface of the superalloy flyer plate 330 prior to applying the conductive coating 332 on said surface. Another softening layer 336 may be applied on another surface of the superalloy flyer plate 330 prior to applying the fracture tough and ductile coating 334 on said surface. A softening layer 336 may be applied on the top of the superalloy base substrate 320 prior to the magnetic pulse welding. The softening layer 336 may improve ductility and fracture toughness of the superalloy flyer plate 330 and ductility and fracture toughness of the superalloy base substrate 320. The softening layer 336 may be sufficiently thin to be ejected along with the jet of material 250 during the magnetic pulse welding.
  • the softening layer 336 may be applied by a superficial softening surface treatment.
  • the superficial softening surface treatment may include leaching of strengthening agents to reduce gamma prime in the superalloy flyer plate 330 and the superalloy base substrate 320.
  • the strengthening agents may include, such as aluminum, titanium, niobium, etc.
  • the superficial softening surface treatment may include pack heat treatment to introduce softening agents or remove strengthening agents near the surface of the superalloy flyer plate 330 and the superalloy base substrate 320.
  • the softening agents may include, such as thorium, cerium, etc.
  • Pre-weld heat treatments may be applied to the superalloy flyer plate 330.
  • Pre-weld heat treatments may be applied to the superalloy base substrate 320.
  • the pre- weld heat treatments may maximize fracture toughness and ductility of the superalloy flyer plate 330 and fracture toughness and ductility of the superalloy base substrate 320.
  • the pre-weld heat treatments may include, for example, pre-weld heating, annealing and overage heat treatments.
  • the superalloy flyer plate 330 is welded on the top of the superalloy base substrate 320 by a solid-state weld 240 to build up an additive layer 322.
  • the fracture tough and ductile coating 334 of the superalloy flyer plate 330 at contact surface of the solid-state weld 240 is ejected along with the jet of material 250 during building up the additive layer 322.
  • Other layers at the contact surface of the solid-state weld 240 are also ejected along with the jet of material 250 during building up the additive layer 322, such as the softening layer 336 of the superalloy flyer plate 330 adjacent to the fracture tough and ductile coating 334, the softening layer 336 of the superalloy base substrate 320 and surface oxidation and contaminants.
  • FIG. 4 illustrates a superalloy component 310 having a sequence of successive additive layers 322 that are welded on top of previous additive layers 322.
  • a successive superalloy flyer plate 330 is arranged between the coil 120 and a previous additive layer 322.
  • the conductive coating 332 is applied on one surface of a successive superalloy flyer plate 330 that is adjacent to the coil 120.
  • the fracture tough and ductile coating 334 is applied to another surface of the successive superalloy flyer plate 330 that is adjacent to a previous additive layer 322.
  • the conductive coating 332 on the surface of the previous superalloy flyer plate 330 is ejected along with the jet of material 250 during building up the successive additive layer 322.
  • the fracture tough and ductile coating 334 on the surface of the successive superalloy flyer plate 330 is ejected along with the jet of material 250 during building up the successive additive layer 322.
  • Other layers at the contact surface of the weld 240 are also ejected along with the jet of material 250 during building up the successive additive layer 322, such as the softening layer 336 of the previous superalloy flyer plate 330 adjacent to the conductive coating 332, the softening layer 336 of the successive superalloy flyer plate 330 adjacent to the fracture tough and ductile coating 334, and surface oxidation and contaminants.
  • the process 300 may be repeated until the last additive layer 322 is built up.
  • the superalloy component 310 may include a machined detail 340, such as a cavity or cooling channel, etc.
  • the machined detail 340 may be pre-machined. Geometric shape of the machined detail 340 needs to be preserved during the magnetic pulse welding.
  • the machined detail 340 may be filled with filler material 342 prior to the magnetic pulse welding.
  • the filler material 342 may absorb impact loading during the magnetic pulse welding to preserve the geometric shape of the machined detail 340.
  • the filler material 342 may include granulated or fracturable material, for example, dry ice, water, or various fine tight packing powders that may not be readily welded to the superalloy flyer plate 330 or to themselves.
  • the fine tight packing powders may include, for example, S1O2, AI2O3, or Zr0 2 , etc.
  • a dimension of the fine tight packing powders may be defined as small relative to a size of the machined detail 340 that may be readily drained out of the machined detail 340.
  • the dimension of the fine tight packing powders may be a fraction of the size of the machined detail 340. For example, for a 1 mm width of the machined detail 340, the dimension of the fine tight packing powders may be in a range of 0.01 to 0.1 mm.
  • the process 300 continues until a completion of the additive manufacturing of the superalloy component 310, as illustrated in FIG. 5.
  • the conductive coating 332 of the last superalloy flyer plate 330 is on top of the superalloy component 310. Said conductive coating 332 may be removed after the superalloy component 310 is built. The conductive coating 332 may be machined away from the top of the superalloy component 310. The softening layer 336 of the last superalloy flyer plate 330 adjacent to the conductive coating 332 may also be removed.
  • the filler material 342 may be disposed from the machined detail 340 after the superalloy component 310 is built. The filler material 342 may be drained out of the machined detail 340.
  • the conductive coating 332 and the fracture tough and ductile coating 334 may consist of the same materials that are included in the superalloy component 310.
  • the softening layer 336 may also consist of the same materials that are included in the superalloy component 310.
  • a small amount of the same materials in the coatings 332 and 334 and layer 336 may be remained in the weld 240 without adversely affecting property of the superalloy component 310.
  • a small amount of aluminum, nickel, chromium, titanium, tantalum, tungsten, or boron, etc. in the coatings 332 and 334 and layer 336 may be remained in a nickel based superalloy component 310 including the same materials.
  • a small amount may be in an order of fractional percentages.
  • the proposed additive manufacturing process 300 uses coating enhanced magnetic pulse welding to additively manufacture a heat sensitive superalloy component 310.
  • the proposed additive manufacturing process 300 avoids high heat input and thus avoids cracking during solidification or upon reheating.
  • the proposed additive manufacturing process 300 may avoid difficulty of precise geometric control of deposited material due to limitation of size and shape of solidifying weld puddle when using conventional arc, or beam welding in an additive manufacturing process.
  • the proposed process 300 provides a precise geometric control of deposited material during the additive manufacturing.
  • the proposed process 300 improves efficiency of the additive manufacturing by avoiding slow and thin material deposition in an additive
  • the proposed additive manufacturing process 300 may be applied to a superalloy component 310 in which high mechanical strength and corrosion resistance at high temperatures is required, such as turbine blades in a turbomachinery.
  • the terms“mounted,”“connected,”“supported,” and“coupled” and variations thereof are used broadly and encompass direct and indirect mountings, connections, supports, and couplings. Further,“connected” and“coupled” are not restricted to physical or mechanical connections or couplings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Butt Welding And Welding Of Specific Article (AREA)

Abstract

L'invention concerne une fabrication additive d'un élément de superalliage (310) à l'aide d'un soudage par impulsions magnétiques. Un revêtement conducteur (332) est appliqué sur une surface de la plaque à ailette de superalliage (330) adjacente à la bobine (120) en vue de générer une force de Lorentz nécessaire. Un revêtement résistant à la rupture et ductile (334) est appliqué sur une autre surface de la plaque à ailette de superalliage (330) adjacente au substrat de base de superalliage (320) en vue d'absorber un impact de collision entre la plaque à ailette de superalliage (330) et le substrat de base de superalliage (320). Une couche additive (322) est formée par soudage d'une plaque à ailette de superalliage (330) sur un substrat de base de superalliage (320) avec une soudure à l'état solide (240). L'élément de superalliage (310) est formé de manière additive jusqu'à ce que la dernière couche additive (322) soit formée au-dessus de la couche additive précédente (322). Des revêtements (334, 336) sur la surface de contact des soudures (240) sont éjectés pendant le soudage par impulsions magnétiques. Des détails usinés (340) sont conservés par un matériau de remplissage (342) qui est retiré après formation de l'élément de superalliage (310).
PCT/US2017/065785 2017-12-12 2017-12-12 Procédé, système et appareil destinés à être utilisés dans la fabrication additive d'un élément de superalliage à l'aide d'un soudage par impulsions magnétiques WO2019117865A1 (fr)

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PCT/US2017/065785 WO2019117865A1 (fr) 2017-12-12 2017-12-12 Procédé, système et appareil destinés à être utilisés dans la fabrication additive d'un élément de superalliage à l'aide d'un soudage par impulsions magnétiques

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PCT/US2017/065785 WO2019117865A1 (fr) 2017-12-12 2017-12-12 Procédé, système et appareil destinés à être utilisés dans la fabrication additive d'un élément de superalliage à l'aide d'un soudage par impulsions magnétiques

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Cited By (2)

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CN114799466A (zh) * 2022-06-06 2022-07-29 西南大学 铝镁铝复合材料制备工艺及设备
CN116021139A (zh) * 2023-01-20 2023-04-28 福州大学 基于跑道型线圈的板件磁脉冲焊接装置及其工作方法

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US20160311064A1 (en) * 2015-04-24 2016-10-27 Engineered Materials Solutions, Llc Self brazing material and a method of making the material
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Publication number Priority date Publication date Assignee Title
US20020066769A1 (en) * 2000-10-16 2002-06-06 Haynes Gardner S. Self-brazing materials for elevated temperature applications
US20160311064A1 (en) * 2015-04-24 2016-10-27 Engineered Materials Solutions, Llc Self brazing material and a method of making the material
DE102016100470A1 (de) * 2016-01-13 2017-07-13 Faurecia Emissions Control Technologies, Germany Gmbh Baugruppe mit mindestens zwei Bauteilen einer Abgasanlage und Verfahren zum Fügen
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114799466A (zh) * 2022-06-06 2022-07-29 西南大学 铝镁铝复合材料制备工艺及设备
CN116021139A (zh) * 2023-01-20 2023-04-28 福州大学 基于跑道型线圈的板件磁脉冲焊接装置及其工作方法

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