WO2013133944A1 - Alliages pour recouvrements de soudure de renforcement - Google Patents

Alliages pour recouvrements de soudure de renforcement Download PDF

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Publication number
WO2013133944A1
WO2013133944A1 PCT/US2013/025982 US2013025982W WO2013133944A1 WO 2013133944 A1 WO2013133944 A1 WO 2013133944A1 US 2013025982 W US2013025982 W US 2013025982W WO 2013133944 A1 WO2013133944 A1 WO 2013133944A1
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Prior art keywords
alloy
alloys
composition
iron
weld
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PCT/US2013/025982
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English (en)
Inventor
Justin Lee Cheney
John Hamilton Madok
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Scoperta, Inc.
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Priority claimed from US13/413,583 external-priority patent/US8647449B2/en
Application filed by Scoperta, Inc. filed Critical Scoperta, Inc.
Priority to CN201380023661.XA priority Critical patent/CN104271788B/zh
Priority to CA2871851A priority patent/CA2871851A1/fr
Publication of WO2013133944A1 publication Critical patent/WO2013133944A1/fr

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/22—Ferrous alloys, e.g. steel alloys containing chromium with molybdenum or tungsten
    • 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
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3053—Fe as the principal constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/12—Ferrous alloys, e.g. steel alloys containing tungsten, tantalum, molybdenum, vanadium, or niobium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/24—Ferrous alloys, e.g. steel alloys containing chromium with vanadium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/26—Ferrous alloys, e.g. steel alloys containing chromium with niobium or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/28—Ferrous alloys, e.g. steel alloys containing chromium with titanium or zirconium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/32—Ferrous alloys, e.g. steel alloys containing chromium with boron
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/48—Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C45/00—Amorphous alloys
    • C22C45/02—Amorphous alloys with iron as the major constituent
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2201/00—Treatment for obtaining particular effects
    • C21D2201/03—Amorphous or microcrystalline structure
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/004—Dispersions; Precipitations
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/005—Ferrite

Definitions

  • the present invention relates generally to metallurgy. More particularly, some embodiments relate to: amorphous, nanocrystalline, or microcystalline metals; and weld overlay materials.
  • Amorphous metallic materials made of multiple components with a noncrystalline structure are also known as "metallic glass” materials.
  • the materials often have different behaviors from corresponding metals with crystalline structures.
  • an amorphous metallic material is usually stronger than a crystalline alloy of the same or similar composition.
  • Bulk metallic glasses are a specific type of amorphous materials or metallic glass made directly from the liquid state without any crystalline phase. Bulk metallic glasses typically exhibit slow critical cooling rates, e.g., less than 100 K/s, high material strength and high resistance to corrosion. Bulk metallic glasses may be produced by various processes, e.g., rapid solidification of molten alloys at a rate that the atoms of the multiple components do not have sufficient time to align and form crystalline structures. Alloys with high amorphous form ability can be cooled at slower rates and thus be made into larger volumes and can be produced using common industrial practices such as thermal spray processing or welding.
  • Amorphous material is commonly made using X- ray diffractometry.
  • Amorphous materials lack translational symmetry, and thus produce X-ray diffraction spectra composed of a single broad hump as opposed to the sharp peaks defined over a narrow diffraction angle range typical to crystalline materials.
  • the formation of metallic glasses is very complex as compared to
  • Nanocrystalline or fine-scale grained materials are known to contain higher hardness and strength than equivalent larger grained materials.
  • Metallic glasses are known to form nanocrystalline precipitates when cooled a slower rate than their glass forming ability requires. Even slower cooling produces complete crystallinity ranging from nanometer sized grains and up. In general, materials which form metallic glasses have slower crystallization kinetics and will thus form smaller grain sized than common materials processed under the same conditions. In addition controlling the rate of cooling, it is often possible to dictate the crystallinity fraction and grain size of a material though compositional control. By altering the
  • composition from its optimum glass forming concentration the precipitation of a particular crystalline phase can be encouraged under appropriate processing conditions.
  • This technique has been used to increase ductility in metallic glasses.
  • crystallization kinetics are such that a line-scale grain structure i likel to form.
  • hardfacing materials especially when dealing with weld overlays capable of exceeding 60 Rockwell C hardness, suffer from cracking during the weld process as well as poor toughness. In addition to other problems, this cracking limits such a materials use in any application where impact occurs. Accordingly, the durability of hardfacing weld overlays can be substantial improved by reducing the potential for cracking and increasing the overall toughness of the weld.
  • tungsten carbide as a hard particle reinforcement in the weld overlay technique is another typical method of hardfacing.
  • This technique involves pouring WC into the molten weld bead as the hardfacing material is being welded onto the substrate.
  • this technique offers a very good hardfacing layer, however it is difficult to apply a hardfacing layer of this type using a hard material as the matrix tor the WC particles, particularly when cracking in the hard facing layer is not desirable.
  • Extreme wear applications often demand improved wear performance beyond that which can be offered using a ductile matrix with WC particles, because the matrix itself is likely to wear away at an accelerated rate leaving the hard particles exposed to shatter or pull out from the surface. Under conditions of extreme impact as well as wear it is important to eliminate cracking in the weld bead.
  • Hardbanding is a technique used to protect the drill stem during operation in oil and gas drilling.
  • the hardbanding is a weld overlay made onto a round tool joint, typically 6" in diameter, which is applied in the field.
  • the hardbanding overlay is designed to be a hard wear resistant alloy which centers the drill stem within the casing, as well as protects the drill stem from wearing itself away on the casing.
  • weld overlay materials are disclosed.
  • one or more materials of the present disclosure can be used as a superior weld overlay material for the protection of tool joints in oil and gas drilling operations.
  • one or more materials of the present disclosure can be used for other overlay hardfacing applications.
  • an iron- based alloy can have a microstructure comprising a fine-grained ferritic matrix.
  • the alloy can have a 60+ Rockwell C surface.
  • the ferritic matrix can comprise ⁇ 10pm Nb and W carbide precipitates.
  • a method of welding can comprise forming a crack free hardbanding weld overlay coating with an iron-based alloy.
  • the alloy can have a microstructure comprising a fine-grained ferritic matrix.
  • the alloy can have a 60+ Rockwell C surface.
  • the ferritic matrix can comprise ⁇ 10 ⁇ Nb and W carbide precipitates.
  • a method of designing an alloy capable of forming a crack free hardbanding weld overlay comprising the step of determining an amorphous forming epicenter composition.
  • the method can further comprise the step of determining a variant composition having a predetermined change in constituent elements from the amorphous forming epicenter composition.
  • the method can further comprise forming and analyzing an alloy having the variant composition.
  • Figure 1 ⁇ is a table illustrating a variety of atomic radii for some elements that may serve as constituents of some embodiments of the invention.
  • Figures IB- 11 are graphs illustrating various characteristics of some embodiments of the invention.
  • Figure 2 is an x-ray diffraction spectrum of an embodiment of the invention.
  • Figure 3 is an x-ray diffraction spectrum of an embodiment of the invention.
  • Figure 4 is an x-ray diffraction spectrum of an embodiment of the invention.
  • Figure 5 is an x-ray diffraction spectrum of an embodiment of the invention.
  • Figure 6 is a wear performance comparison between an embodiment of the invention and other materials.
  • Figure 7 is a coefficient of friction comparison between an embodiment of the invention and other materials.
  • Figure 8 is a galvanic potential comparison between an embodiment of the invention and another material.
  • Figure 9 is a scanning electron microscope image of an embodiment of the invention.
  • Figure 10 is a dry sand wear test comparison between an embodiment of invention and other materials.
  • Figure 1 1 is a scanning electron microscope image of the results of a Vickers indentation test on an embodiment of the invention.
  • Figure 12 is a scanning electron microscope image of an embodiment of the invention.
  • Figures 13A and 13B are scanning electron microscope images of an embodiment of the invention.
  • Figure 14 is a scanning electron microscope image of an embodiment of the invention.
  • Figure 15 is a scanning electron microscope image of an embodiment of the invention.
  • Figure 16 is a scanning electron microscope image of an embodiment of the invention.
  • Figure 17 is a scanning electron microscope image of an embodiment of the invention.
  • Figure 18 is MIG weld bead of alloy on 4140 steel 6" diameter pipe showing no cracking or cross-checking as measured using liquid dye penetrant.
  • Figure 19 is a diagram depicting an alloy design process according to certain aspects of the present disclosure.
  • Figure 20 is a graph illustrating an amorphous forming composition epicenter and an associated amorphous forming composition range according to certain aspects of the present disclosure.
  • Figure 21 shows an exemplary arc melter that can be used to melt an homogeneous alloy ingot for solidification analysis.
  • Figure 22 is a phase diagram that is used for predicting behavior of an alloy when specific alloying elements are either added or subtracted from an amorphous forming epicenter composition according to certain aspects of the present disclosure..
  • Figure 23 is a diagram illustrating an exemplary alloy formation and analysis procedure.
  • Figure 24 is a diagram depicting liquid composition versus cooling curves for various constituent compositions.
  • the figures are not intended to be exhaustive or to limit the invention to the precise form disclosed. It should be understood that the invention can be practiced with modification and alteration, and that the invention be limited only by the claims and the equivalents thereof.
  • the primary solute elements are defined as the solute which are larger than the solvent elements.
  • the primary solute elements may be approximately as at least 5% larger than the solvent elements.
  • Figure 1 A is a table illustrating atomic radii of various elements that may serve as components in various alloys according to some embodiments of the invention.
  • a class or group of compositions is determined using two criteria.
  • the first criteria is that the primary solute elements are larger than the solvent element
  • the second criteria is that the thermodynamic properties of the compositions vary from those that would be predicted from the constituent elements alone.
  • the primary solute element may comprise an element that is at least approximately 10% larger than the solvent element.
  • a first class of alloys that satisfy these criteria may be formed when the solvent elements comprise transition metals ranging in atomic sizes from approximately 1.27 to 1.34 A. As illustrated in Figure 1A, some of these candidate elements may comprise V, Cr, Mn, Fe, Co, Ni, or Cu, for example.
  • some bulk metallic glasses may be formed by the addition of a larger primary solute element having an atomic size at least approximately 10% larger than the size of the solvent element.
  • these primary solute elements range from elements having atomic radii of at least about 1.41 A for solvent elements having atomic radii of approximately 1.27 A to elements having atomic radii of at least about 1.47 A for solvent elements having atomic radii of 1.34 A,
  • some possible candidate primary solutes comprise Mo, Pd, W, Ag, Al, Ti, or larger elements.
  • Compositions formed according to this embodiment may further accommodate secondary or tertiary solute elements comprising metalloids or nonmetal elements.
  • such elements might comprise C, B, Si, P, N, or S.
  • this range of compositions may be more precisely defined according to certain thermodynamic properties.
  • the second criteria for the class of compositions is satisfied when the alloys have a low liquid energetic state in comparison with the energy of the solid-state.
  • deep eutectics may be used as an experimental measure of the thermodynamic strength of the liquid in relation to the potential solid phases which it can form.
  • these energy comparisons may be performed by quanti ying the eutectics of the compositions using a comparison between the actual melting or liquidus temperature of a specific alloy is compared to a calculated predicted liquidus temperature of the alloy.
  • the calculated liquidus temperature may be determined using a rule of mixtures type equation using the atomic percentages of the component elements and their respective pure melting temperature. For example, the calculated liquidus temperature T c is determined according to the equation T.
  • alloys within the compositional ranges of some embodiments of the invention may have calculated liquidus temperatures, T c , that are at least approximately 5% greater than the actual melting temperatures of the alloys. In further embodiments, different ratios between actual and calculated melting temperatures may be used.
  • some embodiments may comprise alloys having some degree of crystallinity, for example some alloys may comprise a micro or nanocrystalline alloys. Alloys within these embodiments may have calculated temperatures that are, for example, at least approximately 2% or 3% greater than the actual melting temperatures of the alloys.
  • alloys within these embodiments may have calculated temperatures that are, for example, at least approximately 7% or 8% greater than the actual melting temperatures of the alloys.
  • the components of alloys may occupy distinct topological sites within the alloy. For example, a larger primary solute element may act as a centralized cluster site for solvent atoms to bind to during cooling. In these embodiments, these clusters allow the formation of a non-trans lational atomic packing scheme which resists crystallization.
  • these larger solute atoms may generate elastic strain energy in an emerging crystalline embryo lattice composed of solvent elements and increase the likelihood for such an embryo to re-dissolve instead of acting as a seed for crystallization.
  • the topologies of these embodiments further allow secondary and tertiary solute elements to occupy interstitial sites that occur between the dense packing clusters. In some eases, these secondary or tertiary solute elements may create strong chemical interactions with the solvent elements.
  • a class f metallic glass forming alloys comprises transition metal solvents with atomic radius sizes ranging from 1.27 to 1.34 A.
  • primary solute sites may make up between 3 to 20 at.% of the alloy composition. These primary solute sites may be occupied by elements with atomic radii that are at least approximately 10% larger than those of the solvent.
  • This embodiment may further comprise secondary solute sites that comprise approximately 10 to 25 at.% of the alloy composition. These secondary solute sites may be occupied by metalloid or nonmetal elements., for example C, B, Si, P, N, or S.
  • the alloys within this embodiment further comprise alloys having melting temperatures that are at least approximately 5% less than a theoretical melting temperature calculated using a sum of the pure melting temperature of the components of the alloy weighted by their atomic percentages.
  • Figures I B through 11 illustrates some characteristics of examples of such alloys, in these figures the alpha parameter is determined according
  • melting temperature of ;th element, and T / is the liquidus temperature of the alloy. As these figures illustrate, alloys that form amorphous structures tend to occur in ranges described herein.
  • the number of available— or occupied— solute sites may vary according to various characteristics of the components.
  • the available secondary solute site may be somewhat dependent on characteristics of the primary solute or the solvent.
  • a primary solute that has a radius approximately 15% larger than that of the solvent may allow different secondary solutes or different amounts of secondary solutes to be used while still retaining metallic glass forming characteristics.
  • a second class of alloys may comprise alloys having solvent elements with atomic sizes in the range of 1.39 to 1.58 A.
  • solvent elements within this second class may comprise Al, Ti, Zr, Nb, or Mo.
  • alloys within this class can accommodate a tertiary solute element in addition to primary and secondary solute elements.
  • primary solute sites may make up approximately 10 to 30 at.% f the alloy composition.
  • These primary solute sites may be occupied by metallic elements having atomic radii that are at least approximately 5% smaller than the solvent elements.
  • These alloys may further comprise elements making up 2 to 10 at.% of the alloy composition and occupying secondary solute sites.
  • these secondary solute elements may comprise elements having atomic radii that are at least approximately 5% larger than the solvent elements.
  • these alloys may further comprise elements making up 5-20 at.% of the alloy composition and occupying tertiary solute sites. These elements occupying tertiary solute sites may comprise metalloid or nonmetal elements such as C, B, Si, P, N, or S.
  • the alloys of these embodiments may be further defined according to their melting temperatures, wherein their melting temperature is below a predetermined percentage of a theoretical integer calculated using a weighted sum of the pure melting temperatures of the alloy's components.
  • the alloys may be defined according to a melting temperature that is at least approximately 5% less than such a theoretical temperature.
  • this tertiary solute element may increase packing density and thereby further increase viscosity of the alloy.
  • the described alloys may be modified to produce alloys forming micro or nanocrystalline structures.
  • the relative sizes or amounts of the solvents or solutes may be varied to promote such formations.
  • the use of 1-2% more of a solvent may result in an alloys that forms a nanocrystalline or fine-grained structure instead of an amorphous structure.
  • the temperature requirements of some embodiments may be relaxed so that alloys having slightly higher melting temperatures, such as 2% less than the theoretical melting temperature, may be investigated for micro or
  • bulk metallic glass alloys may be used to form micro, nanocrystalline or partially crystalline alloys without modification.
  • alloys within the above classes may be cooled at different rates or under di ferent conditions to allow at least some crystallinity in the alloy.
  • Figures 2 through 5 are x-ray diffraction spectrograms of alloys determined according to an embodiment of the invention. As discussed herein, in some applications may be desirable to provide compositions that are partially amorphous and partially nanocrystalline. For example, these coatings may be useful in wear and corrosion resistant twin wire arc spray coatings. In some applications, the coating may benefit from having some limited amount of crystallinity in the coating to act as a binder phase for the remaining hard amorphous particles.
  • Figure 2 is an x-ray diffraction spectrogram illustrating a twin wire arc spray coating having the following composition:
  • an amorphous phase fraction of approximately 75-85% was formed in the composition.
  • the Fe, Cr, and Ni occupy solvent sites
  • the Mo and W occupy primary solute sites
  • the C and B occupy secondary solute sites.
  • elements occupying solvent sites comprise approximately 73 at,% of the alloy
  • elements occupying primary solute sites comprise approximately 7,3 at.% of the alloy
  • elements occupying secondary solute sites comprise approximately 19,6 at.% of the alloy.
  • the specific elements occupying the topological sites may vary without significantly changing the atomic percentages of elements occupying those top logical sites.
  • an alloy may be formed by reducing the percentage of chromium while increasing the percentage of nickel to form an alloy having a melting temperature that is approximately 5% less than the calculated rule-of- mixtures melting temperature.
  • the percentage of occupied sites may vary.
  • the atomic percentages of elements occupying the secondary solute sites may be increased at the expense of the elements occupying the solvent sites to form an alloy having a melting temperature that is approximately 3% less than the calculated rule-of-mixtures melting temperature.
  • Figure 3 is an x-ray diffraction spectrogram illustrating a twin wire arc spray coating having the following composition:
  • the illustrated composition has an amorphous phase fraction of approximately 45-55 %.
  • the Fe, Cr, Ni, and Mn occupy solvent sites
  • the Nb occupies primary solute sites
  • the Si and B occupy secondary solute sites.
  • the elements occupying the solvent sites make up approximately 74.9 at.% of the composition
  • elements occupying the primary solute sites make up approximately 4.5 at.% of the composition
  • elements occupying secondary solute sites comprise approximately 20.6 at.% of the composition.
  • some variations of this alloy might comprise substituting similarly sized elements at appropriate topological sites, such as a substituting Ga for Ni; other variations of this alloy might comprise increasing or decreasing the atomic
  • Figure 4 is an x-ray diffraction spectrogram illustrating a twin wire arc spray coating having the following composition:
  • the illustrated composition has an amorphous phase fraction of approximately 35-45 %.
  • the Fe, Cr, and Mn occupy solvent sites
  • the Nb occupies primary solute sites
  • the Si and B occupy secondary solute sites.
  • the elements occupying the solvent sites make up approximately 84 at.% of the composition
  • elements occupying the primary solute sites make up approximately 3 at.% of the composition
  • elements occupying secondary solute sites comprise approximately 14 at.% of the composition.
  • Figure 5 is an x-ray diffraction spectrogram illustrating a twin wire arc spray coating having the following composition:
  • the Fe and Cr occupy solvent sites
  • the Nb and W occupy primary solute sites
  • the C and B occupy secondary solute sites.
  • the illustrated composition has an amorphous phase fraction of approximately 0-20 %.
  • amorphous phase fraction and coating hardness will vary according to varying spray parameters.
  • the coating hardness as range from approximately between 800 and 1 100 Vickers hardness.
  • the particle hardness as our functions of the material compositions and not the coating porosity or inter particle adhesion. Typical embodiments of amorphous or nanocrystalline alloys formed within these classes have hardnesses that exceed 1200 Vickers.
  • Figures 6 and 7 are figures comparing known materials to the performance of an alloy according to an embodiment of the invention. In these figures,
  • Fe67.sCr9.6C2.iBi.6Wg,8Nbio.6 and the two other Fe-based alloys were deposited on a surface as under a twin wire arc spray coating. Due to the properties of WC/Co, this material was deposited using a high velocity oxygen fuel thermal spray process.
  • embodiments of this invention may serve as superior materials for a variety of applications requiring hardness and wear resistance.
  • some embodiments of this invention may serve as superior materials for bearing coatings, or for bearings themselves.
  • Figure 6 demonstrates the results of a volume loss comparison using the ASTM G77 metal sliding wear test. As the figure demonstrates,
  • Bi,6Wg,8Nbio 6 had about a 0.07 mm 3 volume loss in the test, while WC/Co had about a 0.13 mm 3 volume loss and Alloy 1 and 2 each demonstrated about a 0.17 mm 3 volume loss.
  • Figure 7 demonstrates the results of a coefficient of friction comparison using the ASTM G77 metal sliding wear test. As the figure demonstrates,
  • Fe67.5Cr 9, 6C2.iB 1 .6Wg.gNbio . 6 demonstrated about a 15% improvement over WC/Co and Alloy 1, and a 23% improvement over Alloy 2.
  • Figure 8 shows the results of a galvanic potential comparison between an embodiment of the invention and a comparison alloy. In this test,
  • Fe&55,Cr24i,Nb 4 , 6 B 2 Sii . 5Mni ,2 was compared to FebaianceC.04-.06Si . 6-1.5Cr25-30Ni5- Mn1.2- 2.4B3 . 2-3.7 in a seawater galvanic cell with 316 stainless steel serving as a reference electrode.
  • the alloy according to an embodiment of the invention demonstrated a galvanic potential of about -275 raV as compared to about -375 mV for FehaianceC.04-.06- Si,6 ⁇ . 5Cr2 5 -3oNis ⁇ Mni.2-2,4B3.2-3.7.
  • embodiments of the invention have potentials similar to that of 400 series stainless steels. Accordingly, embodiments of the invention may serve as superior wear resistant coatings in applications such as ship hulls where traditional Fe-based coatings, even corrosive resistant coatings such as FebaianceC.04-.06- Si.6-1.5Cr25.30Ni5.7Mn1.2-2.463.2-3.7, degrade too rapidly.
  • bulk metallic glass forming materials may be determined according to the formula Fe ⁇ fiCro ⁇ CMo.Nb ⁇ -niCjB ⁇ io ⁇ .g io- i . sMno-i 2W0-3 g, and particularly according to the formulae
  • composite materials may be formed by combining components that are formed according to these formulae.
  • nanocrystalline or fine grained structure may comprise materials defined by the formula Fe67.69Cr9.6- 1 o.9(Mo,Nb) 9, 2-i 0. C 1 , 4-2.1 B ! .6-1.gSio-o.2Tio-o.2W7 . 3-9, and more particularly according to the formulae Fe 6 7.6 Cr .6-io.9Ci.4-2.iBi.6-i.8W7.3.9Nb 9 .2-io.6 and Fe67-69Cr9.6-10.9Mo4-5.3C1.4- 2.1B1.6-1.8W7 3.9>3 ⁇ 44_5.3.
  • composite materials may be formed by combining components that are formed according to these formulae.
  • other amorphous forming materials may be similarly modified to result in materials that form nanocrystalline or fine grained structures.
  • composite materials may be made that tend to form partially amorphous and partially nanocrystalline or fine grained structures.
  • one or more components defined by the above formulae for amorphous structured materials may be combined with one or more components defined by the above formulae for nanocrystallinc or fine grained structured materials.
  • such a material may comprise a mixture of components selected from the group comprising: (1) Fe 62 Cr !3 Mo,2CnB2 .2 W 3. gNi4 . g,
  • Figure 9 is a scanning election microscope (SEM) image of an alloy according to an embodiment of the invention, Fe67. 5 Cr9.6C 2 .iBi.6Wg.8Nbio.6> demonstrating this fine grain structure in a weld overlay coating.
  • Figure 10 illustrates the results of a test comparing the alloy of Figure 9 to a first Fe-based fine grain coating comprising
  • the alloy according the embodiment of the invention demonstrates a mass loss of about 0.07 G, compared to about 0.14 G for Alloy 1 and about 0.26 G for Alloy 2. Accordingly, the alloy o the embodiment of the invention demonstrates around a 100% to 200% improvement over Alloys 1 and 2.
  • WC or other hard particles are used as reinforcing the weld overlay.
  • coarse hard carbide particles may be introduced into the weld bead as it is being deposited.
  • Figure 1 1 is an SEM image demonstrating the results of 1000 kg load Vickers indentation on a hardfacing weld overlay comprising a matrix of an alloy formed according to an embodiment of the invention and coarse carbide particles.
  • CrioNb ioB 6sTi , 25 was used as a matrix for coarse carbide particles where the coarse carbide particles constituted 50% by volume of the weld overlay.
  • Figure 12 is an Sh ⁇ l showing a portion of this interface. As this figure illustrates, the hard carbide particles reprecipitate at the interface as opposed to dissolving into the matrix, which would otherwise introduce brittleness into the matrix.
  • Figure 13 is a further illustration of the toughness of a carbide reinforced weld overlay according to an embodiment of the invention.
  • Figure 13A demonstrates the fine grain structure of a carbide reinforced weld overlay comprising Fe 7 5 iCri 0 NbioB 4.6 sTi ,2 5.
  • Figure 13B illustrates a further 1000 kg load Viekers indentation test, again demonstrating an absence of cracking at the interface between the carbide particles and the matrix.
  • a range of alloys is defined by the formula: Fe67.-71 Cr9.6-9. 7 (Mo,Nb)8.8-io.6Ci 8-2.2B 1 . 4-1 .6 ⁇ TA- 8 .
  • the alloy discussed with respect to Figures 9 and 10 is an alloy within this embodiment.
  • the range of alloys comprises alloys defined by the formula Fe67_-nCr . 6-9 . 7 0 8.8 0.5Ci.8-2.2Bi.4-i .6W 7 .4_8 .
  • an alloy may be made up of a plurality of components, wherein one or more of the components comprises alloys defined by these formulae. Materials formed according to these embodiments have typical hardnesses of 1300-1450 Viekers hardness throughout the entire microstructures.
  • a material that is suitable for hard particle reinforcement weld overlays comprises a component defined by the formula Fe43-54Cr . 7-7 . 2 (Mo,Nb)6. 6 - 15 .5C 1- j.3B 1- i.8W9 . 98 -28 Tii. 7 .
  • such a component may be defined by the formula Fe5 0. 5-53 . 2Cr6 -7. 2Mo6.6-7.
  • a component of a material may be defined partially by the first formula and partially by the second.
  • a component might comprise Fe52Cr5.7M08.9Cij W26.2Ti6 1.
  • an alloy comprises a plurality of components, wherein the components are each defined by one of the above formulae.
  • Embodiments of the invention formed according to these formulae may demonstrate substantial precipitation of hard particles in reinforced weld overlay applications.
  • Figure 14 is a SEM demonstrating the precipitation of WC particles in a slow quenched ingot having a matrix comprising .7M01 5 . 5C 1 . sB 1 W27 . 5T15.
  • Figure 14 further demonstrates that alloys formed according to these embodiments retain a fine-grained microstructure even under slow cooling conditions. Materials formed according to these embodiments have typical hardnesses of 1300- 1450 Vickers hardness throughout the entire microstructures.
  • a material that demonstrates hard particle precipitation comprises a component defined by the formula
  • materials may be formed having a component that is defined by the formula Fe70-75 r -10Nb7-10B4-1.6Ti.25-7, Fe54-63Cr7.2- .6M08.6-1 .7C 1 . -2.1B 1 .1- 1.7Ws 5-9.5 ⁇ 3-7. Additionally, in some embodiments, materials may be formed having components that comprise combinations of these formulae. Materials formed according to these embodiments have typical hardnesses of 1300-1450 Vickers hardness throughout the entire microstructures.
  • materials may be formed that comprise mixtures of alloys formed according to the formulae described herein.
  • a material may be formed comprising a plurality of components that are defined by the formulae
  • a material comprises a mixture of one or more of the following components:
  • coarse hard particles are combined with a hard matrix material comprising components described herein.
  • This process comprises melting a component as described herein over a layer of coarse particles.
  • an arc melter may be used to melt a matrix material over a bed of coarse WC particles.
  • the coarse particles are disposed on a cooling body, such as a grooved hearth.
  • a water-cooled grooved copper hearth may be used.
  • the coarse particles are kept at a lower temperature to increase their resistance to dissolution. Accordingly, in these embodiments, the WC particles are allowed to metallurgically bind to the matrix without substantially dissolving into the matrix. In particular experiments, this procedure was conducted using 30%, 40%, and
  • Figures 16 and 17 are SEM images demonstrating typical results of these experiments.
  • Figure 16 illustrates a typical result where 4-8 mesh 80-20 WC/Co was used as the hard particle, forming a composite material: Fe37. Cr5Nb5C1.8B2.4W42 . 2C06.
  • the matrix forms a metallurgical bond with the WC/Co particle without substantially dissolving the particle into the matrix.
  • Figure 17 illustrates a typical result where 4-8 mesh 88-12 WC/Co particles served as the hard particle, forming a composite material: Fe52 .7 Cr 7 Nb 7 C 1 8 3 ,3 W23C06.
  • This figure also demonstrates a metallurgical bond between the WC/Co particle and the matrix, without substantial dissolution of the particle into the matrix.
  • the materials formed according to this embodiment are Fe and W based compositions comprising composite materials of WC hard particles embedded in a hard matrix.
  • the Vickers hardness of the WC is approximately 1400
  • the matrix demonstrated Vickers hardnesses of approximately 1200 due to some dissolution of the coarse particles into the matrix.
  • the materials also demonstrate resistance to cracking at the interface between the particles and the matrix. Accordingly, these material are well-suited for applications where both extreme impact and extreme abrasive wear occur.
  • these materials may be pre-formed for use as components in other applications. As the materials cool, they may contract. Accordingly, the cooling surfaces, such as the grooved hearth, will typically be adjusted for such contractions.
  • these composite materials may be formed using components defined by the formula (Fe54.6 -7 5 . 3Cr 7 .2- 2 4.6Moo - 1 9.7Co-2.3Bi . 5-4. 7 Wo-9 .5 Nb 0- ioTio-7Sio-i,5 no. l 2) x (W 7 6.g-84.5C 3 .2-3.5Coi2-2o)ioo- x where x -50-70.
  • these composite materials may be formed using components defined by the formula (Fe54.6 -7 5 . 3Cr 7 .2- 2 4.6Moo - 1 9.7Co-2.3Bi . 5-4. 7 Wo-9 .5 Nb 0- ioTio-7Sio-i,5 no. l 2) x (W 7 6.g-84.5C 3 .2-3.5Coi2-2o)ioo- x where x -50-70.
  • a matrix material may therefore be defined by the formula Fe 54 6 - 75.3Cr 7 ,2-2 .6 oo-i9 7Co-2. 3 Bi.5 ⁇ .7Wo- .5Nbo-ioTio-7Sio-i.5Mno-i.2.
  • a composite material comprises one or more components defined by the formulae:
  • other materials disclosed herein may serve as suitable matrix materials.
  • the compounds described above with respect to weld overlay applications may serve as suitable matrix materials for these composite materials.
  • a variety of elements may occupy solvent sites in various embodiments of the invention.
  • both Fe and Ni have an atomic radius of 128 A. Accordingly.
  • Ni may be substituted for some or all of an amount of Fe in the materials and components described herein.
  • arbitrary amounts of Ni may be substituted for arbitrary amounts of Fe, such that the melting temperature of the resultant alloy remains at least approximately 5% less than the melting
  • these materials containing Ni may be particularly well-suited for brazing applications.
  • these brazing alloys comprise alloys having components defined by the formula (Ni,Fe)5o-9s(Si,B,P)o-2oCro-3s.
  • the relationship between Ni and Fe may be further defined according to the methods and processes described herein, such as inspection of melting temperatures compared to rule of mixture melting temperatures.
  • such a braze material comprises at least one component selected from the group comprising Ni 52 Bi7Si 3 Fe 2 H, Ni55Bi8Cr 4 Fe 2 4, Ni 54 B l4 Si 45 Cr 4 Fe 2 4, Ni 52 B2oFe 2 g, and Fe 4 3Cr 33 Nii 0 B
  • the alloys may further contain additives to enhance or introduce various features.
  • additives small amounts of Al, Ca, Y, misch metal, or other materials may be added as oxygen getters.
  • the addition of these oxygen getters results in the formula (Ni,Fe) 5 o-95(Si,B,P)o-2oCr,j_
  • binder materials such as Al may be added to the compositions described herein.
  • the materials employed in twin wire arc spray methods described herein may be wrapped with a sheath such as mild steel, stainless steel, nickel, nickel chrome, or aluminum such that the resultant coating shows an increase in bond strength.
  • a sheath such as mild steel, stainless steel, nickel, nickel chrome, or aluminum
  • an amorphous or nanocrystalline coating produced using the twin wire arc spray method manufactured using a mild steel, stainless steel, nickel, or nickel chrome sheath resulted in bond strengths exceeding 8000 psi as measured by ASTM C 633.
  • wrapping an Al sheath around a solid or cored wire containing Ni-base materials described herein also may result in increased bond strengths.
  • Al may be added to any material described herein in a range of concentrations. In these embodiments, the other elements of the material will typically be reduced by a proportional amount so maintain their relative
  • Al may be added in concentrations of 0.5-10% to form materials having components defined by:
  • the addition of Al to materials described herein may further increase the materials ' utilities in applications requiring high coating bond strength and abrasion resistance.
  • Certain materials disclosed in the present disclosure can be directed toward weld overlay materials. In some embodiments, although they are suitable for other weld overlay hard facing applications, the materials serve as a superior weld overlay material for the protection of tool joints in oil and gas drilling operations.
  • Some embodiments comprise an iron-based alloy capable of forming a crack free hardbanding weld overlay coating on a curved substrate of 6" or smaller without any p re-heating or slow cooling methods, resulting in a 60+ Rockwell C surface.
  • the alloy when welded, has a welded microstructure comprising a fine-grained terrific matrix containing ⁇ 10 ⁇ Nb and W carbide precipitates.
  • the alloys may be magnetic or non-magnetic in nature.
  • Particular embodiments comprise alloys falling within the range of alloys defined by the formula (in weight percent): Fe6 7 .3-77 . o 5 Cr 3 .7Nb4.7C0.5-1.4B0.6-1.7s W 9 . 15. 45 Tio-o. 5 Sio-o.5Mno-2Nio.2- Other embodiments comprise alloys falling within the range of alloys defined by the formula (in eight percent): Fe67.3-77.05Cr3_7Nb4-7C0.5- 1.4B0.6-1.75W9.5.15 45Tio-o. 5 Sio-o .5 no- 6 Ni 0 -3.
  • a specific embodiment comprises the alloy given by the formula (in weight percent): Fe74 s r b V2B
  • 5Sio. i 5Tio 25- Other embodiments comprise the alloy given by the formula (in weight percent); B1 . 15. 1.25C1.0.1.
  • Other embodiments comprise the alloy given by the formula (in weight percent): B1 . 15-1.25C 1 . 0- 1.1 Cr4.8-
  • FIG 18 illustrates a metal inert gas (MIG) weld bead of an alloy
  • alloy 1800 comprised the alloy defined by the formula (in weight percent): Fe07j.77 . 05Cr3.7Nb4. 7Co.5-i.4Bo.6-i . 5 W9 . 5.i 5 .4 5Tio-o . 5Sio-o.5 no-6Nio- 3 .
  • the weld bead 1800 was applied to a 4140 steel 6" diameter pipe 1801 . As measured using a liquid dye penetrant, the weld bead shoed no cracking or cross-checking.
  • a microstructure of an alloy by the formula (in weight percent): Fe74j5Cr5Nb4V2B 1 Co . 8W12 . 45Sio . 15Tio . 25 is provided.
  • the microstructure of this alloy includes an optimized microstructure with a ferrite matrix havin finegrained niobium and tungsten based precipitates. These precipitates are less than about ⁇ ⁇ on average and produce an alloy having a unique hardness and toughness.
  • the matrix is a fine-grained ferritic/austentic matrix which is fully interconnected. The matrix is able to blunt cracking and provides toughness to the overall material
  • the secondary phases and are extremely hard and are plenti ful in the microstructure, forming up to 30% by volume fraction, but are isolated from each other by the interconnected matrix.
  • alloy compositions have been determined for manufacture into welding wires for hardbanding testing.
  • the alloys have been determined from experimental results as part of an ongoing project to design hardbanding alloys, and subsequent laboratory analysis of potential alloys compositions. Initial laboratory results suggested these alloys as ideal candidates and the experimental welding trials have been conducted.
  • crack-free as deposited welds The alloys disclosed can be welded onto curved surfaces without the use of pre-heating or slow cooling techniques, and form a continuous crack free weld bead. The lack of pre-heating required is very
  • hardbanding alloys for tool joints. Typical hardbanding alloys report 60+ Rockwell C values only when measured in the undiluted condition. However, in actual single pass weld overlays with significant dilution, which is the condition used for these applications, these alloys experience lower hardness values.
  • the alloys described in this patent possess improved wear resistance compared to the previously most advanced hardbanding alloys used in oil and gas drilling operations.
  • the wear resistance is measured using the ASTM G65 dry sand wear test.
  • the wear loss of this alloy in the diluted condition was 0.1092 grams lost, significantly better than previous technologies which report un-diluted (condition resulting in lower wear losses, and not a condition used in the field) 0.12 g lost.
  • the alloys described in this patent are compositionally designed to form a high fraction of finely grained carbide precipitates.
  • the thermodynamics inherent to these alloys allow for excess carbon to be absorbed into the weld without altering the
  • the MIG carbide welds are formed of a soft steel matrix containing large carbide grains.
  • the wear behavior is such that the steel quickly wears a way leaving the sharp carbide particles to gouge away at the casing.
  • the carbide particles are very fine and evenly distributed so as not to cause highly localized regions of wear on the casing.
  • the matrix is a hardened fine-grained structure, which exhibits hardening according to the Hall-Petch relationship.
  • the casing will be in contact with a relatively smooth surface as opposed to a weld bead with sharp hard particles which locally wear and cause casing failure.
  • hardbanding materials comprise alloys falling within the range of alloys defined by the formula (in weight percent): Fc65 3,79 95Cr3. 7 Nio- 6Mno- 6 Nb3.5-7Vo-2.o5Co.5-i.5Bo . 6-i . 7sW 7 .5-i 5.45 Si 0- i . o io-iAl 0- .
  • Particular embodiments comprise alloy defined by the formulae (in weight percent): Fe 65 3-79 gsCrsNio ⁇ Mn () - O-2C0.8-1 . 5B0.8- 1.4W8.5.13.5 Sio.i5Tio.25-l Al 0 _4 ;
  • FIG 19 is a diagram depicting an alloy design process 1900 according to certain aspects of the present disclosure.
  • the alloy design process comprises a 4- component metallic glass modeling technique based on topology, liquidus temperature, chemical short range order and elastic strain to determine an amorphous forming epicenter composition.
  • An amorphous forming composition epicenter 2010 and an associated amorphous forming composition range 2020 are shown in diagram 2000 of Figure 20.
  • Various aspects of such a 4-component metallic glass modeling technique are described above in the present disclosure and also in University of California, San Diego Ph. l > thesis "Modeling the Glass Forming Ability of Metals" by Justin Lee Cheney, which is incorporated by reference herein for all purposes.
  • the modeling technique can be used to maximize the potential for amorphous forming ability for the design of an amorphous material 1920 having a metallic glass epicenter composition.
  • a variant composition having a predetermined change in constituent elements from the amorphous forming epicenter composition is determined, and an alloy having the variant composition is formed and analyzed.
  • a first or second variant technique 1930 or 1 40 may be employed to design a thermal spray material (e.g., glass/crystal composite 1950) for use as a thermal spray wire or a fine-grained crystalline material (e.g., ⁇ im-structured crystalline 1960) for use as a weld overlay material, respectively.
  • a thermal spray material e.g., glass/crystal composite 1950
  • a fine-grained crystalline material e.g., ⁇ im-structured crystalline 1960
  • the first variant technique 1930 for designing a thermal spray material involves vitrification potential determination 1932 and solidification analysis 1934.
  • one or more variant compositions ranging from between about 5 and 10% atomic percent offset in constituent elements from an amorphous forming composition epicenter 2010 are chosen.
  • the term "about” means within normal manufacturing tolerances. This range is termed
  • a variant composition in this nanocrystalling/glass composite zone can include one or more additional components that are not present in the amorphous forming epicenter composition.
  • the variant composition includes between about 0.1 and 10% additional constituent that is not present in the amorphous forming epicenter composition.
  • the solidification analysis 1934 can be performed through a lab-based technique to simulate the cooling rate in thermal spray materials thus determined. In an exemplar)' setup 2108, an homogeneous alloy ingot is melted within an arc melter such as the one shown in Figure 21 in a water cooled copper cavity 2107.
  • the liquid alloy ingot 2106 When a fully molten copper plate 2105, termed the splat block, is dropped onto the liquid alloy ingot 2106, the liquid alloy ingot is rapidly cooled in the form of a thin sheet (between about 0.25 and lmm) in thickness.
  • nanocrystal line/glass mierostructure can be evaluated using any known structural analysis methods including, but not limited to, XR1 ) and SEM analysis. Those variant compositions that satisfy certain conditions (e.g., hardness and structural integrity) are selected. Variant compositions designed and selected through the processes described above can be produced as thermal spray wires, for instance.
  • the second variant technique 1940 for designing a fine-grained crystalline material can involve a phase diagram prediction 1942 and a phase chemistry prediction 1944.
  • phase diagram prediction 1942 specific alloying elements are either added or subtracted to encourage an evolution of desired crystalline phases in the mierostructure as illustrated by phase diagram 2200 shown in Figure 22.
  • the phase chemistry prediction 1944 can be used to model any shi ts in elemental concentration of the liquid as primary crystallites nucleate.
  • FIG 23 illustrates an exemplary alloy formation and analysis procedure.
  • an homogeneous alloy ingot is melted, e.g., within an arc melter in a water cooled copper cavity. Size of the homogenous alloy ingot being melted (“melt") is preferably between about 10 and 20g to ensure that the cooling rate closely matches that experienced in MIG welding.
  • Figure 24 is a diagram 2400 depicting liquid composition versus cooling curves for various constituent compositions. Certain variant compositions designed, analyzed and selected through the processes described above can be produced as welding wires, for instance.
  • Figures 25-38 illustrate the results of experiments performed on various additional embodiments of the invention.
  • Exemplary alloy chemistries of these embodiments are listed in Table 2 below. Some of these alloys may have chemistries defined by the following formula: a balance of Fe; between 0-5.75 wt.% Cr; between 0-1.15 wt.% Mn; between 4-7 wt.% Nb; between 0-2.78 wt.% V; between 0.5- 1.1 wt. % C; between 0.82 -3 wt.% B; between 0-3.5 wt.% Mo; between 0-1 1.45 wt.% W; between 0-0.3 wt.% Ti; and between 0-5 wt.% Si.
  • a balance of Fe between 0-5.75 wt.% Cr; between 0-1.15 wt.% Mn; between 4-7 wt.% Nb; between 0-2.78 wt.% V; between 0.5- 1.1 wt. % C; between 0.82 -3 wt.% B; between 0-3.5 wt.% Mo;
  • some of these alloys may have chemistries defined by the following formula: a balance of Fe; between 0- 5.75 wt.% Cr; between 0-1.15 wt.% Mn; between 4-7 wt.% Nb; between 0-2.78 wt.% V; between 0.5-1.1 wt. % C; between 0.82 -3 wt.% B; between 0-3.5 wt.% Mo;
  • the alloys may have chemistries defined by the following formula: a balance of Fe;
  • alloy chemistries may be used in the production of welding wires for hardbanding applications or other welding applications. The chemistries may also be present in the final welds.
  • the alloy compositions provided in Table 2 where created in the form of 10-20g alloy ingots using a small bell jar (ABJ-338) arc melter.
  • compositions were produced by mixing together pure elemental granules, powders, and other feedstock and then melted completely in the arc melter under an argon atmosphere. To ensure complete mixing, the ingots were flipped and re-melted at least four times. No indication of incomplete melting was seen in any ingot micro structures.
  • Table 2 Exemplary alloy chemistries (in weight percent).
  • Alloy Group CF-1 - CFl-9 As understood in the art, because of production variances, the final composition amounts of a welding wire or other material can differ from the exact desired chemistry.
  • the alloys from Table 2 denoted CF-1 , CFl-7, CFl-8, and CFl-9 represent four alloys produced with a similar chemistry as alloy CF-1 from Table 1, illustrating an example of possible ranges that may be obtained because of unavoidable production variation.
  • compositions having the following elemental ranges: a balance of Fe; between 4-5.75 wt.% Cr; between 0.5-1.15 wt.% Mn; between 4-6 wt.% Nb; between 2-2.78 wt.% V; between 0.6- 1 .1 wt. % C; between 0.7 -0.9 wt.% B; between 7-8 wt.% W; between 0.1 -0.3 wt.% Ti; and between 0.25-0.75 wt.% Si.
  • the compositions may be welding wires, welds, or any metal alloy.
  • embodiments may comprise welding wires operable to create alloys having these ranges when used on various substrates.
  • CFEXP- 1 Based on hardness measurements and microsctural analyses, several alloy chemistries (CFEXP- 1, CFEXP-2, CFEXP-4, CFEXP-5, CFEXP-6, CFEXP-7,
  • CFEXP-11, CFEXP-12, CFEXP-13, CFEXP-14, CFEXP-15) were manufactured in the form of 1/16" cored welding wire.
  • the CFEXP alloys were welded onto 4137 tool joints using welding parameters typical of the hardbanding process.
  • Some embodiments of invention comprise a composition of matter having the following compositional range: a balance of Fe; between 0-5 wt.% ( r between 0-1.15 wt.% Mn; between 3-5 wt.% Nb; between 0.4-1 .75 wt.% V; between 0.7-0.9 wt.
  • compositions may be welds, welding wires, or alloys. Additionally, some embodiments may comprise welding wires having compositions operable to produce welds having these alloy compositional ranges, or any other alloy composition disclosed herein
  • CFEXP-1 1 alloys were produced and are indicated in this disclosure as CFEXP-1 la, CFEXP- 1 l b (6). and CFEXP-1 1 b (7). These alloy variations represent slight chemistry variations due to being produced in ditTerent manufacturing lots.
  • the intended chemistry is CFEXP-1 la.
  • the difference between CFEXP-1 l b (6) and CFEXP-1 lb (7) are the arc stabilizers used, which is intended to improve weldability and likely has a minimal effect on the weld overlay mechanical performance (i.e. hardness and ASTM G65 testing).
  • FIGs 25 A and 25 B illustrate the result of welding the CFEXP-1 alloy onto a 6 5/8" 4137 steel tool joint with a single pass.
  • Figure 25 A illustrates a single bead and Figure 25B illustrates four beads. In both cases, the weld was crack free.
  • Figures 26A and 26B illustrate single passes of as-welded CFEXP-2 alloy on 6 5/8" 4137 steel tool joint.
  • Figure 26A illustrates a single bead and Figure 26B illustrates four beads. In both cases, the weld was crack free.
  • Figure 27 illustrates a single pass of as- welded CFEXP-5 alloy on 6 5/8" 4137 steel tool joint.
  • Figures 28 ⁇ and 28B illustrate single passes of as-welded CFKXP-6 alloy on 6 5/8" 4137 steel tool joint.
  • Figure 28A illustrates a single bead while Figure 28B illustrates four beads, in both cases, the welds were found to be crack free.
  • FIGS. 2 A and 29B illustrate as- welded CFEXP- 1 1 a on 6 5/8'" 4137 steel tool joint.
  • Figure 29A illustrates a single pass three bead weld
  • Figure 29B illustrates a double pass three bead weld. In both cases, the welds were crack free.
  • the grain size of the ferritic (matrix) phase of the CFEXP-1 lb alloy when deposited onto a tool joint according to the described parameters above was determined via X-ray diffraction.
  • X-ray diffraction is a standard method to determine the average grain size of materials.
  • Figure 35 shows the X-ray diffraction spectrum for the alloy and Table 3 shows the quantified peak parameters for the diffraction spectrum.
  • the X-ray diffraction technique was performed on the as- welded CFEXP- 1 l b alloy sectioned from the single pass tool joint illustrated in Figure 5 A.
  • Figures 36A-36B are backscatter-mode scanning electron micrographs ( SEMs) of the microstructure of the CFEXP- l 1 alloys.
  • the microstructure is representative of all the Mo-containing alloys disclosed herein. Additionally, the microstructure is structurally similar to the W-containing alloys disclosed herein.
  • Figure 37 is a SEM of the microstructure of an example W-containing alloy - Fe (balance), Cr (5%), B (0.8%), C(0.97%), V(2%) Nb (4%), W(l 1.45%), Si (0.15%), Ti(0.25%) (in weight percent.)
  • This phase either possess a relatively higher concentration of Molybdenum or Tungsten in addition to chromium (similar to all CFEXP alloys).
  • the energy dispersive spectroscopy for an alloy containing Mo and one containing W is shown in Table 4 and Table 5, respectively.
  • both alloys are composed of a ferritic matrix with Niobium-rich phases, which have been identified as Niobium carbide particles via X-ray diffraction.
  • the third phase which is relatively richer in chromium and either Mo or W, has been characterized as ferritic iron in both alloy types via X-ray diffraction.
  • additional hard precipitates such as complex W-borocarbides can precipitate.
  • the formation of these Mo and/or W borocarbides is advantageous for increasing wear resistance. This may be desirable for single pass application but is considered undesirable in elevated volume fractions tor a crack resistant alloy capable of double layer crack resistance on tool joints.
  • the weld overlays were veri fied as crack-free initially through visual examination and then through either magnetic particle inspection or fluid dye penetrant testing. Coupons were sectioned from these samples (single pass) for use in hardness and ASTM G65 testing, and thus represent properties experienced in the field. In all cases, a second weld overlay pass made directly over the previous 3 band layer was attempted. Only a slight wire brush was used to clean the previous hardband layer from dust, no actual weld metal was removed in a significant way.
  • FIGS 3 OA and 30B illustrate as-welded CFEXP-12 alloy on 65/8" steel pipe indicating.
  • Figure 3 A illustrates a single pass and
  • Figure 30B illustrates a double pass. In both cases, the weld was crack free.
  • CFEXP-13 CFEXP-13
  • Figures 31 A and 3 IB illustrate as welded CFEXP-13 alloy on 65/8" steel pipe.
  • Figure 31 A illustrates a single pass and
  • Figure 3 IB illustrates a double pass. In both cases, the weld was crack free.
  • Figures 32A-C illustrate as- welded CFEXP- 14 alloy on 6 5/8" 4137 steel tool joint.
  • Figure 32A illustrates a single pass weld overlay and was found to be crack free.
  • Figure 32B illustrates a double pass weld overlay and was found to contain a crack 3200, illustrated in Figure 32C.
  • Figure 33 illustrates as-welded CFEXP-15 alloy on 6 5/8" 4137 steel tool joint indicating no cracks.
  • Some embodiments of the invention comprises a composition of matter in the following range:: a balance of Fe; between 3-5 wt.% Nb; between 0-2 wt.% V;
  • these compositions can be alloys, welds, or welding wires. In some applications it is desirable to have alloys which do not have any chromium content. One reason for this desired metallurgy is to prevent the production of hexavalent chromium fumes, a known carcinogen, during welding.
  • the alloys disclosed here do not rely on the formation of chromium containing carbides or borides to exhibit the desired properties such as high hardness or wear resistance.
  • module does not imply that the components or functionality described or claimed as part of the module are all configured in a common package. Indeed, any or all of the various components of a module, whether control logic or other components, can be combined in a single package or separately maintained and can further be distributed in multiple groupings or packages or across multiple locations.

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  • Mechanical Engineering (AREA)
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  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Powder Metallurgy (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)

Abstract

L'invention concerne des alliages à base de fer ayant une microstructure comprenant une matrice ferritique à grains fins et ayant une surface C 60 +-Rockwell, dans laquelle la matrice ferritique comprend des précipités de carbure < 10 μm. L'invention concerne Également des procédés de soudage consistant à former un revêtement de recouvrement de soudure de rechargement sans fissure avec un tel alliage à base de fer. L'invention concerne Également des familles d'alliages capables de formation des recouvrements de soudure exempte de fissures après de multiples passes de soudage.
PCT/US2013/025982 2012-03-06 2013-02-13 Alliages pour recouvrements de soudure de renforcement WO2013133944A1 (fr)

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CN201380023661.XA CN104271788B (zh) 2012-03-06 2013-02-13 用于环形加硬焊接覆盖层的合金
CA2871851A CA2871851A1 (fr) 2012-03-06 2013-02-13 Alliages pour recouvrements de soudure de renforcement

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US13/413,583 US8647449B2 (en) 2009-09-17 2012-03-06 Alloys for hardbanding weld overlays
US13/413,583 2012-03-06

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US10100388B2 (en) 2011-12-30 2018-10-16 Scoperta, Inc. Coating compositions
US9738959B2 (en) 2012-10-11 2017-08-22 Scoperta, Inc. Non-magnetic metal alloy compositions and applications
US10345252B2 (en) 2013-10-10 2019-07-09 Scoperta, Inc. Methods of selecting material compositions and designing materials having a target property
US10495590B2 (en) 2013-10-10 2019-12-03 Scoperta, Inc. Methods of selecting material compositions and designing materials having a target property
US11175250B2 (en) 2013-10-10 2021-11-16 Oerlikon Metco (Us) Inc. Methods of selecting material compositions and designing materials having a target property
US9802387B2 (en) 2013-11-26 2017-10-31 Scoperta, Inc. Corrosion resistant hardfacing alloy
US10173290B2 (en) 2014-06-09 2019-01-08 Scoperta, Inc. Crack resistant hardfacing alloys
US11111912B2 (en) 2014-06-09 2021-09-07 Oerlikon Metco (Us) Inc. Crack resistant hardfacing alloys
US11130205B2 (en) 2014-06-09 2021-09-28 Oerlikon Metco (Us) Inc. Crack resistant hardfacing alloys
US10465269B2 (en) 2014-07-24 2019-11-05 Scoperta, Inc. Impact resistant hardfacing and alloys and methods for making the same
US10465267B2 (en) 2014-07-24 2019-11-05 Scoperta, Inc. Hardfacing alloys resistant to hot tearing and cracking
US10329647B2 (en) 2014-12-16 2019-06-25 Scoperta, Inc. Tough and wear resistant ferrous alloys containing multiple hardphases

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CA2871851A1 (fr) 2013-09-12
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