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WO2002013996A1 - Procede servant a fabriquer des composites metalliques et composites fabriques au moyen de ce procede - Google Patents

Procede servant a fabriquer des composites metalliques et composites fabriques au moyen de ce procede Download PDF

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Publication number
WO2002013996A1
WO2002013996A1 PCT/AU2001/000974 AU0100974W WO0213996A1 WO 2002013996 A1 WO2002013996 A1 WO 2002013996A1 AU 0100974 W AU0100974 W AU 0100974W WO 0213996 A1 WO0213996 A1 WO 0213996A1
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WO
WIPO (PCT)
Prior art keywords
wear resistant
producing
resistant composite
composite product
temperature
Prior art date
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Ceased
Application number
PCT/AU2001/000974
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English (en)
Inventor
Paul Graeme Huggett
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Individual
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Individual
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Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to AU2001277412A priority Critical patent/AU2001277412B2/en
Priority to AU7741201A priority patent/AU7741201A/xx
Publication of WO2002013996A1 publication Critical patent/WO2002013996A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/06—Casting in, on, or around objects which form part of the product for manufacturing or repairing tools
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/04—Casting in, on, or around objects which form part of the product for joining parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/08—Casting in, on, or around objects which form part of the product for building-up linings or coverings, e.g. of anti-frictional metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D25/00—Special casting characterised by the nature of the product
    • B22D25/06—Special casting characterised by the nature of the product by its physical properties
    • B22D25/08—Special casting characterised by the nature of the product by its physical properties by uniform hardness

Definitions

  • the present invention relates to a method of manufacturing a wear resistant composite material by a vacuum casting process and composites produced by the same process.
  • These materials are characterised by hard carbides in a metallic matrix. Generally it can be considered that these materials, although possessing good to excellent abrasion resistance, are not particularly easy to work with. They tend to be difficult if not practically impossible to weld. As these materials are brittle they tend to fracture when attached to the application with mechanical fasteners and fail catastrophically when subject to high impact loads.
  • One of the ways to obtain a compromise in the material properties is to form a composite product.
  • the composite products often have an extremely wear resistant product coupled to a weldable or machinable substrate.
  • the processes for coupling the abrasion resistant product to the tough substrate can range from mechanically interlocking to full metallurgical bonding.
  • These composite products include Tungsten Carbide tiles silver soldered to carbon steel.
  • the main problem associated with this procedure is the bond strength.
  • the bond strength is limited because of the predominantly mechanical joint resulting and the need for close tolerances between the mating faces.
  • Hardfacing processes range form oxyfuel gas welding to the various types of arc welding and the advanced techniques of plasma transferred arc and laser welding. These hardfacing processes have some similarity in that a surface is coated using consumables. The consumables are selected so that the resulting coating has the desired chemical and microstructural properties.
  • Vacuum brazing has been used successfully to join white irons to mild steel through the use of a copper-brazing alloy.
  • the parts are heated to a temperature above the melting point of the copper to allow the copper to wet both surfaces.
  • the molten copper combines with the ferrous alloys to produce a columnar growth of copper/iron grains across the interface.
  • Carbon steel is often the substrate for these composite materials because it is easy to work with basic tooling and is cheap. Carbon steel also has the user- r friendly properties of being easily weldable in the field using commonly available techniques. This allows the wear product to be held in place by welding of the substrate to the application or by the welding of studs to the substrate and then bolting the wear product to the application. There are however significant limitations to the preparation of composite materials using conventional manufacturing techniques including:
  • the present invention includes a method of producing a wear resistant composite product including the steps of: contacting a first material with a second material, the first material having a liquidus temperature that is lower than a solidius temperature of the second material; heating the first and second materials at less than atmospheric pressure at sea level to a temperature above the liquidus temperature of the said first material; maintaining the temperature of the first and second said materials above the liquidus temperature of the first material for a predetermined period of time so that the first material at least partially fuses to the second material
  • the products may be subject to a post production heat treatment to optimize the final product properties for anticipated service. Through suitable control of the cooling cycle it is possible to eliminate the need for this post production heat treatment.
  • the matrix alloy can be chosen from a range of materials that exhibit at least partial solid solubility with the substrate material including iron, aluminium, nickel and titanium alloys when used in conjunction with a ferrous substrate. The selection of which matrix alloy would depend on the material characteristics required of the final composite.
  • the matrix alloy has a composition within the following ranges in weight percent.
  • Another embodiment of the present invention includes a matrix alloy with a liquidus temperature of between 650°C and 1350°C.
  • the liquidus temperature of the matrix alloy being at least 100°C less than the solidus point of the substrate.
  • the matrix alloy can be manufactured in a separate process prior to the vacuum casting.
  • conventional foundry techniques can be employed although advanced techniques such as atomization, forging, diecasting may also be employed.
  • the substrate material is selected from a range of material that exhibits at least partial solid solubility with the matrix alloy. Predominantly, this would be a ferrous alloy but could include nickel or titanium base alloys. The actual analysis of this material can vary and would be chosen to balance the solidus of the alloy with the high temperature strength and solid solubility with the matrix alloy.
  • the substrate material can be chosen from a range of materials, especially from those materials that are weldable with common welding apparatus such as mig, tig and stick welding. A range of manufacturing techniques such as forging, fabricating or casting can be used to produce the substrate.
  • the substrate can be in the form of a shell.
  • the furnace temperature can operate in the range of between 50°C and 250°C above the liquidus temperature of the matrix alloy. 5
  • the furnace is held at a temperature above the liquidus temperature of the matrix alloy for some time.
  • the furnace may be held above the liquidus temperature of the matrix alloy for a minimum of 10 minutes for every 50mm of cross section of the product.
  • the inert atmosphere is at a partial pressure of between lOOmbar and 10 500mbar.
  • the inert atmosphere is preferably nitrogen although argon, argon/helium, inert gas, reducing atmosphere or any other gas suitable for welding may be employed.
  • Another embodiment of the invention provides composite products that are 15 sufficiently wear resistant and tough, manufactured using the above described method with the addition of hard carbide or ceramic material being substituted for a proportion of the matrix alloy.
  • Such products could be used in applications involving extreme abrasion where the component is subject to impact loading or where a complex shape is required. This process could also be used for the 0 repair of large wear components suffering extreme localised wear such as slurry pump components.
  • the hard carbide or ceramic material includes carbides, nitrides and borides of Ti, W, Cr, Mo, Ta, V, Nb, and B
  • the ceramic material may include oxides, nitrides and titanates of Si, Al, 5 Mg, Ti, V, B, and Nb either individually of in combination with any other carbide, oxide, nitride, boride wear resistant material.
  • the shell used to form the shape of the component manufactured using the vacuum casting technique is a non-consumable item.
  • This shell may be coated with a refractory 0 compound applied to the remelt bar being placed in the shell.
  • the substrate may be placed on top of the remelt with some weights so as to keep the substrate in positive contact with the remelt alloy.
  • This assembly is then heated in a vacuum furnace as previously described. It will be understood that various arrangements are possible using this technique and the geometry of the arrangements whereby the substrate is placed on the matrix alloy could vary significantly.
  • the substrate may be arranged to engage the matrix alloy during the heat treatment process such that when the matrix has solidified after processing a composite product is achieved.
  • Such embodiments could include the non-consumable mould being of such a geometric configuration that the remelt material can be melted and contained in such a manner as to form a composite product with the substrate acting as an insert or partial mould for the remelted material.
  • the final product could consist of a number of zones: a) the prefabricated component that forms the bulk of the substrate; b) the transition between the prefabricated component and the wear material, where the wear material is fused to the substrate (in some arrangements the substrate could be an insert or could be in the form of a shell with the matrix alloy being located inside the substrate); c) the matrix alloy or cast formed portion. This part could be formed in a non-consumable mould in such a way as to engage the substrate material.
  • Figure 1 is a flow chart showing the sequence of events in the practice of the method of the present invention.
  • Figure 2 is a schematic diagram illustrating production of a composite material in accordance with a method of the invention
  • Figure 3 is a phase diagram of matrix material showing liquidus range of 1175-1275°C;
  • Figure 4 Typical temperature and pressure profile for a product produced with a consumable steel shell
  • Figure 5 is an optical micrograph of a composite product produced in accordance with the thermal and pressure profile of Figure 4 showing the interface produced between the substrate and matrix alloy
  • Figure 6 is a schematic diagram illustrating production of a composite in accordance with a method of the invention including a non-consumable mould;
  • Figure 7 Typical temperature and pressure profile for a product produced with a ceramic-coated mould;
  • Figure 8 is a graph showing the relationship between temperature and time and acceptable product quality.
  • the process for producing composite materials has a series of steps as shown in the general flow diagram of Figure I, and reference to Figures 2-5 is required to illustrate certain features of the invention.
  • a trial matrix ( Figure 2- 12) material was cast using conventional open air casting methods (Figure 1-1) of approximate composition of carbon 4%, chromium 9%, manganese 1.6%, nickel 1%, silicon 1%. This material was cast into sand moulds to produce a base matrix allow for further experiments.
  • the liquidus temperature (11) for the matrix material (12) was determined by thermal analysis and cross checked with the phase diagram for the alloy system ( Figure 3) the liquidus line (11) being that line where the material changes from ausenite or M 7 C 3 carbide and liquid to liquid.
  • the substrate ( Figure 2- 14) in this example was manufactured ( Figure 1- 2) using a conventional open-air casting process the same as for the matrix material.
  • the substrate ( Figure 2-14) was in the form of a shell nominally of 0.2% carbon steel or 1% carbon tool steel. After manufacture of the matrix alloy (12) and the substrate (14) both are prepared for further processing by using high- pressure water and dried, or with mild grit blasting to remove any oxidation and surface scale (3). In other experiments the substrate ( Figure 2-14) was fabricated using standard steel sections.
  • the prepared substrate (14) containing the required amount of matrix material (12) is placed in a furnace capable of having atmospheric composition and pressure conditions changed (5) in this case the furnace used was a vacuum furnace.
  • the vacuum furnace is evacuated and purged with an inert gas (in this case nitrogen) to remove oxygen from the chamber (6).
  • the vacuum furnace was filled with a partial pressure of nitrogen to 208-mbar (6). It was surprisingly found that greater vacuum did not result in improved bond quality but a honeycomb type structure due to the vaporisation of some elements. At higher pressure, it was found that the bond quality was compromised due to interface reactions.
  • Furnace is then set to run through a predetermined heat treatment program based on the liquidus temperature (11) of the matrix material (12) and the hold time required to obtain satisfactory product. Including the steps of:
  • the heat treatment is shown in Figure 4 in combination with the pressure cycle.
  • the furnace is opened (9).
  • the substrate and now remelted matrix alloy composite products (10) are removed from the furnace and allowed to air cool to room temperature prior to final finishing processes.
  • FIG. 5 shows an optical micrograph of the resulting microstructure from which it was determined that the bond was fully fused and metallurgical in nature.
  • the composite product consisted of a matrix alloy (12) in this case a wear resistant low melting point white iron (12), an interface/bond (13) and a substrate in the form of a consumable shell of approximately 0.2% to 1 % carbon steel (14).
  • the metallurgical bond had an interface size (13) of approximately 10 microns. Adjacent to the interface (13) in the zone that was molten during processing; there is a carbide depleted zone (15). This carbide depleted zone (15) can be manipulated based on cooling rate and material composition.
  • the substrate (14) microstructure consisted of pearlite 16 with the formation of intergranular carbides (17). These are seen as light areas at the grain boundaries on the micrograph.
  • the matrix alloy consists of austenite (18) with eutectic chromium carbides (19).
  • the bond layer (20) consisting of the bond interface (13) and the carbide depleted zone (15) has altered morphology showing a depletion of chromium this is identified by the lack of carbides in these zones (13 and 15). It can be seen that the bond layer (13 and 15) between the matrix alloy (12) and the substrate (14) is relatively porosity free with some migration of the matrix alloy (12) into the substrate (14).
  • the finished product was measured for dimensional accuracy and it was found that the composite product had not undergone significant dimensional change.
  • the temperature and pressure profile is shown in Figure 4. This cycle is based on the liquidus temperature of the matrix material and time.
  • Figure 6 illustrates another aspect of the invention.
  • the shell or mould used is reusable ( Figure 6) and non-consumable.
  • the mould (26) is prepared and coated with a refractory substance.
  • the matrix alloy, or remelt ingots, (2) are charged into the mould (26) and a substrate (30), or in this case an original worn part (30), is arranged so that when the matrix alloy (12) melts, it fills the mould (26) and also comes into intimate contact with the substrate (30) so as to fuse or partially fuse with the substrate (30).
  • a coating system for the mould (26) was used.
  • a steel shell (26) can be used as a non-consumable mould providing a suitable barrier coating (27) is applied to the mould prior to use.
  • the steel shell mould is first cleaned using high-pressure water and dried, or with mild grit blasting, to remove any residual ceramic coatings or scale from previous use.
  • the topcoat of magnesite based refractory is applied using either spray, flow coat or dipping. Only one coat of the magnesite based refractory is applied. The standard coating is suspended in alcohol. 6. The final coat is allowed to thoroughly dry prior to the mould being used. ⁇
  • the kaolin based refractory coating used on its own was inadequate in stopping the molten alloy from bonding to the steel shell.
  • the magnesite based refractory used in a single coating was inadequate in stopping the molten alloy from bonding to the steel shell.
  • Various other types of coatings were trailed individually and in combination, and the system used above was proven to be the most efficient barrier coating (27) system for the current casting process.
  • the liquidus temperature of the matrix alloy (12) was determined either by thermal analysis during manufacture by using the phase diagram ( Figure 3) for the particular matrix material (12).
  • the matrix material (12) used in this example had a liquidus temperature (11), of approximately 1190-1200°C .
  • the temperature above the liquidus temperature (11) to be reached and time required at this temperature during the heat treatment (6) can be established.
  • the temperature to be reached above the liquidus temperature (11) follows an inverse relationship with time of soak. The higher the temperature of the heat treatment above the liquidus temperature (11), the shorter the time required.
  • the temperature above the liquidus temperature (11) that the process can be run at is limited by the Solidus temperature of the substrate (14). If the operating temperature is too high the substrate (14) or mould (26) will not have sufficient strength to hold the molten matrix material (12)

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)

Abstract

L'invention concerne un procédé servant à fabriquer un produit composite résistant à l'usure, ce qui consiste à: mettre en contact un premier matériau avec un deuxième matériau, ce premier matériau possédant une température de liquidus inférieure à la température de solidus du deuxième matériau; réchauffer le premier et le deuxième matériau à une pression atmosphérique inférieure à la pression standard à une température supérieure à la température de liquidus dudit premier matériau; maintenir la température du premier et du deuxième matériau au-dessus de la température de liquidus du premier matériau pendant une durée prédéterminée, de façon que ce premier matériau fusionne, au moins partiellement, avec le deuxième matériau.
PCT/AU2001/000974 2000-08-10 2001-08-09 Procede servant a fabriquer des composites metalliques et composites fabriques au moyen de ce procede Ceased WO2002013996A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU2001277412A AU2001277412B2 (en) 2000-08-10 2001-08-09 A method of manufacturing metallic composites and composites produced thereby
AU7741201A AU7741201A (en) 2000-08-10 2001-08-09 A method of manufacturing metallic composites and composites produced thereby

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AUPQ9334 2000-08-10
AUPQ9334A AUPQ933400A0 (en) 2000-08-10 2000-08-10 A method of manufacturing metallic composites produced thereby

Publications (1)

Publication Number Publication Date
WO2002013996A1 true WO2002013996A1 (fr) 2002-02-21

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009155655A1 (fr) * 2008-06-27 2009-12-30 Excalibur Steel Company Pty Ltd Fabrication de composants composites résistants à l'usure
US20110259541A1 (en) * 2008-12-23 2011-10-27 Excalibur Steel Company Pty Ltd Method of manufacturing components
US9561562B2 (en) 2011-04-06 2017-02-07 Esco Corporation Hardfaced wearpart using brazing and associated method and assembly for manufacturing
US20190368164A1 (en) * 2016-11-17 2019-12-05 Doosan Infracore Co., Ltd. Construction machine bucket part and manufacturing method therefor
US10543528B2 (en) 2012-01-31 2020-01-28 Esco Group Llc Wear resistant material and system and method of creating a wear resistant material

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2126512A (en) * 1982-08-26 1984-03-28 Hoverdale Engineering Limited Method of hard-surfacing
AU4441589A (en) * 1988-11-02 1990-05-10 Mason & Cox Proprietary Limited Composite wear resistant product
WO2000076666A1 (fr) * 1999-06-10 2000-12-21 Svedala New Zealand Limited Composants composites sacrificiels

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2126512A (en) * 1982-08-26 1984-03-28 Hoverdale Engineering Limited Method of hard-surfacing
AU4441589A (en) * 1988-11-02 1990-05-10 Mason & Cox Proprietary Limited Composite wear resistant product
WO2000076666A1 (fr) * 1999-06-10 2000-12-21 Svedala New Zealand Limited Composants composites sacrificiels

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009155655A1 (fr) * 2008-06-27 2009-12-30 Excalibur Steel Company Pty Ltd Fabrication de composants composites résistants à l'usure
AU2009262357B2 (en) * 2008-06-27 2015-10-01 Excalibur Steel Company Pty Ltd Manufacture of wear resistant composite components
US20110259541A1 (en) * 2008-12-23 2011-10-27 Excalibur Steel Company Pty Ltd Method of manufacturing components
US9561562B2 (en) 2011-04-06 2017-02-07 Esco Corporation Hardfaced wearpart using brazing and associated method and assembly for manufacturing
US10730104B2 (en) 2011-04-06 2020-08-04 Esco Group Llc Hardfaced wear part using brazing and associated method and assembly for manufacturing
US10543528B2 (en) 2012-01-31 2020-01-28 Esco Group Llc Wear resistant material and system and method of creating a wear resistant material
US20190368164A1 (en) * 2016-11-17 2019-12-05 Doosan Infracore Co., Ltd. Construction machine bucket part and manufacturing method therefor
US11814819B2 (en) * 2016-11-17 2023-11-14 Doosan Infracore Co., Ltd Construction machine bucket part and manufacturing method therefor

Also Published As

Publication number Publication date
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