AMORPHOUS METAL/REINFORCEMENT COMPOSITE MATERIAL

Abstract: A reinforcement-containing metal-matrix composite material (20) is formed by dispersing pieces of reinforcement material (22) throughout a melt of a bulk-solidifying amorphous metal and solidifying the mixture at a sufficiently high rate that the solid metal matrix (24) is amorphous. Dispersing is typically accomplished either by melting the metal and mixing the pieces of reinforcement material (22) into the melt, or by providing a mass of pieces of the reinforcement material (22) and infiltration of the molten amorphous metal into the mass. The metal preferably has a composition of about that of a eutectic composition, and most preferably has a composition, in atomic percent, of from about 45 to about 67 percent total of zirconium plus titanium, from about 10 to about 35 percent beryllium, and from about 10 to about 38 percent total of copper plus nickel.

Description: (1 134 PC17US95/08980 AMORPHOUS METAL/REINFORCEMENT COMPOSITE MATERIAL BACKGROUND OF THE INVENTION This invention relates to a composite material having reinforcement material, desirabl} particles of refractory ceramics or diamond, bonded into an amoφhous metal matrix. Hard materials such as diamond and certain carbides, borides, and nitrides are widely used to cut other, softer materials such as metals. Large single pieces of these hard materials are too brittle and too expensive for many cutting-tool applications. A bonded-tool technology has developed over the years for using smaller pieces of such materials in cutting tools. In this approach, small particles of the hard material are bonded at elevated temperatures into a matrix of a metal such as a nickel or cobalt alloy by liquid phase sintering. Upon cooling, the resulting composite material has the particles of the hard material dispersed throughout the metal matrix. The metal matrix bonds the particles together and also imparts fracture toughness and provides thermal conductivity to the article. As one example of this type of material, tungsten carbide/cobalt alloy cutting tools are widely used commercially. The extended contact between the abrasive material and the molten metal at highly elevated temperatures can lead to chemical interactions between the particles and the molten metal, especially in the presence of reactive alloy additions to the matrix material. The chemical reactions may result in the formation of brittle intermetallic reaction products at the particle/matrix interface or within the matrix. After cooling, the reaction products may adversely affect the properties of the composite material. One solution to the problem is to coat the particles with a reaction-inhibiting coating, but such coatings are typically expensive to apply and often have limited effectiveness. Accordingly, the range of choices for the matrix material is sometimes severely limited to avoid the presence of reactive constituents. The matrix may -9. consequently be relatively soft, weak, and susceptible to corrosion damage. Accordingly, there is a need for an improved bonded composite material of reinforcement particles, particularly diamond or refractory ceramic particles, distributed in a matrix. Such an improved material would find immediate use in cutting tools, and also in other applications such as hard facings and structures having a high strength-to- weight ratio. The present invention fulfills this need, and provides related advantages. SUMMARY OF THE INVENTION This invention provides a metal-matrix composite material having reinforcement materials bonded together by an amorphous-metal matrix, and a method for preparing the composite material. A wide range of types of reinforcement materials can be used. In a preferred approach, a bulk-solidifying amorphous material is employed, permitting the preparation of large, tool-sized pieces of the composite material rather than thin ribbons. In accordance with the invention, a method of forming a remforcement-containing metal-matrix composite material comprises the steps of providing a metal having a capability of retaining the amorphous state when cooled from its melt at a critical cooling rate of no more than about 500°C per second, and providing at least one piece of reinforcement material which is initially separate from the metal. The method further includes melting the metal and dispersing the at least one piece of reinforcement material throughout the melt to form a mixture, and solidifying the mixture at a cooling rate no less than the critical cooling rate. More preferably the method involves the use of a plurality of pieces of the reinforcement material. The reinforcement pieces, also termed particles, can be generally equiaxed or elongated in the manner of fibers. The step of dispersing is desirably accomplished either by preparing a mass of molten metal in a crucible and mixing the pieces of the reinforcement material into the mass of molten metal, or by preparing a mass of pieces of the reinforcement material, melting the metal, and infiltrating the melted metal into the mass of pieces of the reinforcement material. The reinforcements are most preferably diamond or refractory ceramics having melting points at least about 600°C above the melting point of the amorphous metal matrix and also having excellent stability, strength, and hardness. The metal-matrix material is a bulk-solidifying amoφhous material in which the amoφhous state can be retained in cooling from the melt at a rate of no greater than about 500°C per second. The metal-matrix material should have a melting point at least about 600°C, preferably more, below the melting point of the refractory material. Due to the high surface energy and low melting point of the bulk amoφhous alloy, the various types of reinforcements are readily wet by the molten amoφhous alloy. The composite is thus formed at a relatively low temperature without significant degradation of the reinforcement and, surprisingly, without substantial crystallization of the matrix alloy. In the composite material of the invention, the amoφhous-metal matrix bonds the reinforcement particles together. The particles are not degraded during fabrication due to the low melting point and composition of the matrix material and therefore can attain their full potential in a cutting tool. Moreover, the amoφhous matrix itself is hard and strong so that it does not degrade or rapidly wear away during service, yet is reasonably ductile and fracture resistant. The composite material is therefore operable as a cutting tool that is hard yet resistant to failure. The amoφhous material is also highly corrosion resistant, because it has no internal grain boundaries to serve as preferential sites for the initiation of corrosion. Corrosion resistance is desirable, because it may be expected that the composite materials of the invention may be exposed to corrosive environments during service. For example, cutting tools are often used with coolants and lubricants that may cause corrosion. Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the invention. BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a drawing of the microstructure of the material of the invention; Figure 2 is an elevational view of a first type of cutting tool made using the material of the invention; Figure 3 is an elevational view of a second type of cutting tool made using the material of the invention; Figure 4 is a flow diagram for a preferred approach to preparing the material of Figure 1; and Figure 5 is a graph of thermal expansion coefficient as a function of temperature for metals, ceramics, and the preferred bulk-solidifying matrix alloy. DETAILED DESCRIPTION OF THE INVENTION Figure 1 illustrates an idealized microstructure of a composite material 20 made by the present approach. The composite material 20 is a mixture of two phases, a reinforcement phase 22 and a metal-matrix phase 24 that surrounds and bonds the reinforcement phase 22. In an embodiment of the invention wherein a substantially uniform array of reinforcement particle phase within the metal-matrix phase is attained, the reinforcement phase 22 desirably occupies from about 50 to about 90 volume percent of the total of the reinforcement phase and the metal-matrix phase, although phase percentages outside this range are operable. If the reinforcement phase is present in a smaller volume percent, it becomes progressively more difficult, as the amount of reinforcement phase is reduced, to prepare a uniform dispersion of the reinforcement phase within the metal-matrix phase using the preferred melt-fabrication technique. The composite also will have insufficient hardness for cutting tool applications. If the reinforcement phase is present in a higher volume percent, it is difficult to form a homogeneous mixture with matrix phase surrounding and wetting the reinforcement particles. Additionally, the composite material will have an unacceptably low fracture resistance. In a most preferred form of this embodiment, the reinforcement phase occupies from about 70 to about 85 volume percent of the total material. This embodiment is desirably used for cutting tools and the like. In another embodiment, a smaller volume percent of reinforcement is present in a composite material in which the reinforcement phase is concentrated at the surface of the material. It has been observed that, for low volume percentages of reinforcement present in the composite material, the reinforcement particles preferentially segregate to the surface of the composite material as the matrix phase is cooled and becomes increasingly viscous. This form of the invention can utilize much smaller volume percentages of reinforcement in the composite material, and is particularly valuable when the final material is to be used for applications such as surface finishing or polishing. Figures 2 and 3 illustrate cutting tools made of the material of the invention, as shown in Figure 1. These depicted cutting tools are presented as illustrations, and other geometries can be prepared, such as drills, milling cutters, cutting blades, and cutting wheels, for example. The cutting tool 26 of Figure 2 is made entirely of the composite material 20. Alternatively, the cutting tool 28 of Figure 3 has only a cutting insert 30 made of the composite material 20. The cutting insert 30 is bonded or affixed to a tool support 32 made of steel or other inexpensive material. Figure 4 illustrates a method for fabricating pieces of the composite material 20 and/or articles made of the composite material 20. Reinforcement particles are first provided, numeral 40. The reinforcement particles are preferably of a size of from about 20 to about 160 mesh for use in cutting, drilling, grinding, and comparable applications. The reinforcement particles are preferably smaller than this range for use in polishing applications. For cutting and polishing applications, the reinforcement particles are typically not perfectly regular in shape, but are generally equiaxed and irregularly shaped, as shown in Figure 1. The indicated dimension is an approximate maximum dimension of the particles. Most preferably, the reinforcement particles are from about 20 to about 80 mesh in size for cutting applications. The reinforcement phase can also be elongated in one dimension as a fiber or in two dimensions as a platelet. Where diamond particles are used, blocky diamonds are most preferred for cutting applications involving impact forces. Other shapes of diamond particles are acceptable, however. Any type of diamond is acceptable for use with the invention. Diamonds range in quality from gem quality to industrial quality and to very low-grade quality that may not be suitable for many industrial applications such as cutting tools. Diamonds can be either natural or artificial. The pertinent indicators of quality in respect to the present invention are chemical composition, inclusion content, and crystal perfection, not physical appearance (although physical appearance may be related to these factors). All diamonds are made primarily of carbon arranged in the diamond-cubic crystal structure. However, artificial and natural diamonds typically have various types and amounts of impurities present. Both natural and artificial diamonds often exhibit a form containing grain boundaries and other imperfections, primarily impurity inclusions. These factors affect the usability of diamonds in conventional bonded cutting tool materials. Low-grade diamonds that have large amounts of impurities and substantial densities of imperfections are not suitable for use in conventional bonded cutting tools because they chemically and/or physically degrade during the high temperature exposure required in the bonding operation. As used herein, "low-grade diamond" is defined as diamond which experiences damage, for example in the form of a loss of toughness and wear resistance, when exposed for 10 minutes or more at a temperature of 800°C or more. The use of low-grade diamonds is preferred in the present approach. Low-grade diamonds have properties that may be slightly inferior to higher grade diamonds, but their price is significantly lower because of their lesser desirability for either gem or industrial applications. A major virtue of the present invention is the ability to use such low-grade diamonds in a bonded material suitable for use in cutting tools. The reinforcement can also be a refractory ceramic, preferably of the same particle size and shape as discussed in relation to diamond particles. Examples of suitable reinforcements include stable oxides such as alumina, zirconia, beryllia, and silica; stable carbides such as carbides of tantalum, titanium, niobium, zirconium, tungsten, chromium, and silicon; and stable nitrides such as cubic boron nitride and the nitrides of silicon, aluminum, zirconium, and titanium. This listing is not exhaustive, and is presented by way of example. The refractory ceramic reinforcement should have a melting point (which term includes "softening point" where applicable) at least about 600°C above the melting point of the matrix alloy. If the melting point of the reinforcement is less than about 600°C above the melting point of the matrix alloy, there is a much greater likelihood of chemical reactions between the reinforcement and the matrix alloy, and also that the matrix alloy will crystallize upon cooling of the composite material. The matrix material is provided, numeral 42. The matrix material is a metal alloy, termed herein a "bulk solidifying amoφhous metal", that can be cooled from the melt to retain the amoφhous form in the solid state at relatively low cooling rates, on the order of 500°C per second or less. This ability to retain an amoφhous structure even with a relatively slow cooling rate is to be contrasted with the behavior of other types of amoφhous metals that require cooling rates of at least about 10 4 -10 6 °C per second from the melt to retain the amoφhous structure upon cooling. Such metals can only be fabricated in amoφhous form as thin ribbons or particles. The preparation of thin strips of such prior amoφhous metals with reinforcements embedded in the top surface of the strip has been suggested previously, see US Patent 4,268,564. Such a form has limited usefulness in the preparation of cutting tools and the like, both because of the fabrication difficulties and also because the reinforcements are not dispersed throughout the volume of the article. A preferred type of bulk-soUdifying amoφhous alloy has a composition of about that of a deep eutectic composition. Such a deep eutectic composition has a relatively low melting point and a steep Uquidus. The composition of the bulk-solidifying amoφhous alloy is therefore desirably selected such that the Uquidus temperature of the amoφhous aUoy is no more than about 50°C higher than the eutectic temperature, so as not to lose the advantages of the low 4134 PC17US95/08980 -8- eutectic melting point. Because of this low melting point, the melt-fabrication processing of the invention can be accomplished at a sufficiently low temperature that degradation of the reinforcement particles is minimized. A preferred type of bulk-soUdifying amoφhous alloy has a composition near a eutectic composition, such as a deep eutectic composition with a eutectic temperature on the order of 660°C. This material has a composition, in atom percent, of from about 45 to about 67 percent total of zirconium plus titanium, from about 10 to about 35 percent beryUium, and from about 10 to about 38 percent total of copper plus nickel. Surprisingly, this high zirconium and titanium content reacts with typical reinforcement materials very slowly, probably because of the low temperatures that are used in the fabrication processing, and there is substantiaUy no crystalUzation of the matrix alloy as it cools. A substantial amount of hafnium can be substituted for some of the zirconium and titanium, aluminum can be substituted for the beryUium in an amount up to about half of the beryUium present, and up to a few percent of iron, chromium, molybdenum, or cobalt can be substituted for some of the copper and nickel. A most preferred such metal-matrix material has a composition, in atomic percent, of about 41.2 percent zirconium, 13.8 percent titanium, 10 percent nickel, 12.5 percent copper, and 22.5 percent berylUum, and a melting point of about 670°C. This bulk-solidifying alloy is known and is described in US Patent 5,288,344. Another important advantage to using a bulk-soUdifying amoφhous material as the matrix of the composite material is iUustrated in Figure 5 for the case of the preferred amoφhous matrix material. It is desirable to use a metal having a low melting point as the matrix of the composite material, so that melt fabrication can be accomplished at a relatively low temperature to avoid excessive chemical reaction with the reinforcement material. Conventional crystalline-soUd metals which have a low melting point tend to have a high coefficient of thermal expansion, as shown in the curve of Figure 5. Ceramic reinforcement materials of interest, on the other hand, tend to have a low coefficient of thermal expansion. The large difference in thermal expansion between conventional crystaUine metals and ceramics leads to large and undesirable internal strains and stresses which result as the composite is cooled from the melting point. The inventors have recognized that the bulk-soUdifying amoφhous metals have a much lower coefficient of thermal expansion for their melting points than do the crystaUine-soUd metals. The coefficients of thermal expansion of the bulk-soUdifying amoφhous metals are much closer to those of the ceramics than are the coefficients of thermal expansion of the crystaUine metals, resulting in much lower thermaUy induced strains and stresses in a composite material upon cooling to ambient temperature. These bulk-solidifying amoφhous aUoys are therefore desirably used as the matrix in composite materials. Additionally, the total accumulated thermal strains and stresses depend upon the temperature change from the initiation of strain and stress buildup, in addition to the difference in thermal expansion coefficient of the components. For the case of a conventional crystalline-solid matrix, thermal strains and stresses begin buUding at just below the melting point of the metal as the composite is cooled. For the case of the bulk-solidifying amoφhous metal matrix, thermal strains and stresses begin building at the glass transition temperature as the composite is cooled, because the metal exhibits glassy flow at higher temperatures to negate the thermal strains and stresses. In the case of the preferred matrix material, the melting point is about 670°C but the glass transition temperature is about 350°C, over 300°C lower. Thus, the thermal strains and stresses induced in the composite material having a matrix of a bulk-soUdifying amoφhous material are much lower than those of a composite material having a conventional crystaUine metal matrix for several reasons. One is that the difference in the coefficient of thermal expansion of the bulk-soUdifying amoφhous alloy is close to that of the ceramic reinforcement. A second is that the thermal strains and stresses do not begin to build until the composite cools below the glass transition temperature of the matrix alloy. A third is that the amoφhous metals do not exhibit an abrupt phase change at the melting point. The buLk-soUdifying alloy is melted, and the reinforcement particles are dispersed in the melt, numeral 44. In this context, "dispersed" can mean either that the reinforcement particles are mixed into a volume of the molten metal or that the melt is infiltrated into a mass of the reinforcement particles. In either case, the final composite has reinforcement particles distributed throughout the volume of the matrix material. When the volume percent of reinforcement particles is relatively smaller compared to the volume percent of metal, the reinforcements can be stirred into the melt. When the volume percent of reinforcement particles is relatively larger compared to the volume percent of metal or the reinforcement particles are fibrous with a high aspect ratio or are woven together, the melt is aUowed to flow into, or is forced into, the mass of reinforcement particles by infiltration. The mixing of particles into a melt and the infiltration of a melt into a packed mass of particles are known fabrication technologies for use in other contexts. The most preferred bulk-soUdifying aUoy discussed above has a melting point of about 670°C. In the first of the fabrication procedures, a mass of this matrix aUoy in a crucible is heated somewhat above that temperature, preferably to a temperature of from about 700°C to about 850°C, most preferably to a temperature of about 750°C, in an atmosphere of pure argon. The reinforcement particles are added and dispersed within the melt by stirring. The mixture of molten metal and reinforcement particles, which are not melted, is retained at the melting temperature for a short time of about one minute. The melt is then allowed to cool, causing the molten metal to soUdify, numeral 46. In the infiltration approach, a mass of the reinforcement particles is placed into a container such as a metal or ceramic tube. The tube and particles are heated to the infiltration temperature, in the preferred case preferably to a temperature of from about 700°C to about 850°C, most preferably to a temperature of about 750°C, in an atmosphere of pure argon. The matrix material is heated to this same temperature and allowed to flow into the mass of reinforcement particles, or, alternatively, forced into the mass of reinforcement particles under pressure. The particles and metal are then allowed to cool, causing the molten metal to solidify, numeral 46. The mixture is cooled at a sufficiently high solidification rate to cause the molten metal to remain in the amoφhous state, but not greater than about 500°C per second, to produce a composite material. If higher cooling rates are needed and used, it is difficult to obtain sufficiently thick pieces for most applications. When the method is practiced properly, the resulting structure is Uke that depicted in Figure 1, with reinforcement particles 22 dispersed throughout a substantiaUy completely amoφhous metal-matrix phase 24. A minor degree of crystallization is sometimes noted around the reinforcement particles, which are thought to induce such crystaUization. Such a minor degree of crystaUization is acceptable within the context of the limitation of a substantially completely amoφhous metal-matrix phase. The process steps 40, 42, 44, and 46 are sufficient to perform one embodiment of the method of the invention. In another embodiment, the mixture may be cooled at any cooling rate in step 46, without regard to whether the structure of the soUd metal is amoφhous. The soUdified mixture is thereafter heated to remelt the mixture, numeral 48. The mixture is solidified, numeral 50, by cooling it at a cooling rate sufficiently high that the amoφhous state of the metalUc aUoy is retained, but in no event at a rate greater than about 500°C per second. This latter embodiment employing steps 40, 42, 44, 46, 48, and 50 may be used, for example, in remelt operations wherein an ingot of the composite material is prepared at a central location and provided to users who remelt and recast the composite material into desired shapes. The foUowing examples iUustrate aspects of the invention, but should not be taken as limiting the invention in any respect. Example 1 A quantity of titanium carbide (TiC), having a size of 100-120 mesh, was infiltrated with molten metal of the preferred composition discussed previously. Infiltration was accompUshed in an atmosphere of clean, gettered argon at a temperature of about 750°C. The metal wetted the TiC particles well, and the resulting mass was cooled to ambient temperature at a rate of from about 10°C to about 120°C per second. The time of contact between the TiC and the molten metal at the infiltration temperature was less than one minute. The mixture of titanium carbide and metaUic alloy was reheated to a temperature of about 900°C for about two minutes and cooled to ambient temperature at a rate of from about 10°C to about 120°C per second. Microscopic examination revealed that the TiC was weU wetted and that the matrix was amoφhous with substantially no crystalUzation present. Example 2 Example 1 was repeated, using siUcon carbide paniculate having a size of -80+120 mesh. The results were substantiaUy the same. Example 3 Example 1 was repeated, using tungsten carbide particulate having a size of -80+120 mesh. The results were substantiaUy the same. Example 4 Example 1 was repeated, using alumina particulate having a size of -120+325 mesh. The results were substantially the same. Example 5 Example 1 was repeated, using cubic boron nitride particulate having a size of -100+120 mesh. The results were substantiaUy the same. Example 6 The sizes of indenter impressions of specimens of the composite material produced in Examples 1-5 and the matrix aUoy were measured using a conical diamond indenter with a 60 kilogram load in a Rockwell type hardness testing machine. The results are as foUows, with the impression size indicated in micrometers: Example 1, 380; Example 2, 340, Example 3, 290; Example 4, 330; Example 5, 350; matrix alloy alone, 720. These hardness measurements demonstrate that the presence of the particles increases the strength of the composite material above that of the matrix alloy alone, inasmuch as the strength generally varies inversely with the square of the diameter of the impression. Example 7 A quantity of intermeshed siUcon carbide fibers, each fiber being about 25 micrometers in diameter and 1/2 inch long, was infiltrated with molten metal of the preferred composition. Infiltration was accompUshed in an atmosphere of clean, gettered argon at a temperature of about 800°C. The metal wetted the fibrous siUcon carbide sufficiently weU to show spreading of the Uquid alloy, and the resulting mass was cooled to ambient temperature at a rate of from about 10°C to about 120°C per second. The time of contact between the siUcon carbide and the molten metal at the infiltration temperature was about two minutes. Microscopic examination of the composite material demonstrated that the matrix aUoy had not crystaUized. Example 8 A quantity of General Electric MBG-T artificial diamond particulate material, exhibiting a Ught green color and having a size of 100-120 mesh, was infiltrated with molten metal of the preferred composition discussed previously . Infiltration was accomplished in an atmosphere of clean, gettered argon at a temperature of about 750°C. The metal wetted the diamond particles well, and the resulting mass was cooled to ambient temperature at a rate of from about 10°C to about 120°C per second. The time of contact between the diamond and the molten metal at the infiltration temperature was less than one minute. Upon metallographic inspection, the metalUc matrix of a specimen of the diamond/metal composite material was seen to be primarily amoφhous, but to have some crystalUzation evident adjacent to the diamond particles. The remainder of the material was reheated to a temperature of about 900°C for about two minutes and cooled to ambient temperature at a rate of from about 10°C to about 120°C per second. The matrix was again inspected and found to be entirely amoφhous, with no crystalline material present. Example 9 A quantity of General Electric RVG artificial diamond particulate material, exhibiting a black color and having a size of 100-120 mesh, was infiltrated with molten metal of the preferred composition discussed previously. Infiltration was accomplished in an atmosphere of clean, gettered argon at a temperature of about 800°C. The metal wetted the diamond particles well, and the resulting mass was cooled to ambient temperature at a rate of from about 10°C to about 120°C per second. The time of contact between the diamond and the molten metal at the infiltration temperature was about two minutes. Metallographic inspection revealed that the metal matrix was entirely amoφhous. The present invention provides an approach for preparing a hard, abrasive composite material useful as a cutting tool or as a wear-resistant structure. The reinforcement material embedded in the matrix provides the primary cutting and wear-resistance function. The amoφhous matrix effectively bonds the reinforcement, and is itself a relatively hard, tough, abrasion-resistant material. Thus, the matrix does not readily wear away or crack during service, resulting in puU-out of the reinforcement particles from the wearing surface. The amoφhous matrix " material and the composite structure itself impart fracture resistance to the composite material, another important attribute for cutting tools, abrasion-resistant surfaces, and similar articles. Although a particular embodiment of the invention has been described in detaU for purposes of iUustration, various modifications and enhancements may be made without departing from the spirit and scope of the invention. Accordingly, the invention is not to be limited except as by the appended claims.

Claims: CLAIMS What is claimed is: 1. A method of forming a reinforcement-containing metal -matrix composite material, comprising the steps of: providing a metal having a capabiUty of retaining the amoφhous state when cooled from its melt at a critical cooling rate of no more than about 500°C per second; providing at least one piece of reinforcement material, separate from the metal; melting the metal and dispersing the at least one piece of reinforcement material throughout the melt to form a mixture; and solidifying the mixture at a cooling rate no less than the critical cooling rate. 2. The method of claim 1, wherein the step of providing at least one piece of reinforcement material includes the step of providing a pluraUty of pieces of reinforcement material. 3. The method of claim 2, wherein the step of providing a pluraUty of pieces of reinforcement material includes the step of providing a plurality of pieces of reinforcement material having a size of from about 20 mesh to about 160 mesh. 4. The method of claim 1 or claim 2, wherein the step of providing includes the step of providing a reinforcement material selected from the group consisting of diamond, a stable oxide, a stable carbide, and a stable nitride. 5. The method of claim 4, wherein the diamond is low-grade diamond. 6. The method of any of claims 1-5, wherein the step of providing a metal includes the step of providing a metal having a composition of about that of a eutectic composition. 7. The method of any of claims 1-5, wherein the step of providing a metal includes the step of providing a metal having a composition, in atom percent, of from about 45 to about 67 percent total of zirconium plus titanium, from about 10 to about 35 percent berylUum, and from about 10 to about 38 percent total of copper plus nickel. 8. The method of claim 1 or claim 2, wherein the step of melting the metal and dispersing the at least one piece of reinforcement material throughout the melt includes the steps of: preparing a mass of molten metal in a crucible, and mixing the at least one piece of reinforcement material into the mass of molten metal. 9. The method of claim 1 or claim 2, wherein the step of melting the metal and dispersing the at least one piece of reinforcement material throughout the melt includes the steps of: preparing a mass of pieces of the reinforcement material, melting the metal, and infiltrating the melted metal into the mass of pieces of the reinforcement material. 10. The method of claim 1, wherein the cooling rate in the step of solidifying is no higher than about 500°C per second. 11. A reinforcement-containing metal-matrix composite material, comprising a mass of a bulk-solidifying amoφhous metal; and a plurality of reinforcement pieces dispersed throughout the mass of amoφhous metal. 4134 PCI7US95/08980 -17- 12. The composite material of claim 1 1, wherein the amoφhous metal has a composition, in atom percent, of from about 45 to about 67 percent total of zirconium plus titanium, from about 10 to about 35 percent beryllium, and from about 10 to about 38 percent total of copper plus nickel. 13. The composite material of claim 12, wherein there is a substitution selected from the group consisting of hafnium for some of the zirconium plus titanium, aluminum for some of the beryUium, and an element selected from the group consisting of iron, chromium, molybdenum, and cobalt for some of the copper plus nickel. 14. The composite material of claim 11, wherein the bulk-solidifying amoφhous metal is characterized by the abUity to retain an amoφhous state when cooled from its melt at a critical cooling rate of no more than about 500°C per second. 15. The composite material of claim 11, wherein the reinforcement pieces are selected from the group consisting of diamond, a stable oxide, a stable carbide, and a stable nitride. 16. The composite material of claim 15, wherein the diamond is low- grade diamond.

Inventors: JOHNSON WILLIAM L, PEKER ATAKAN, SCHAFER ROBERT, SCRUGGS DAVID M, JOHNSON, WILLIAM, L., PEKER, ATAKAN, SCHAFER, ROBERT, SCRUGGS, DAVID, M.
Applicants: AMORPHUS ALLOYS CORP, AMORPHUS ALLOYS CORP.
Application year: 1995
Main classification: B32B15
IPC codes: B22D19, C22C1, C22C14, C22C16, C22C45