US3821841A - Method for fabricating a beryllium fiber reinforced composite having a titanium matrix - Google Patents

Method for fabricating a beryllium fiber reinforced composite having a titanium matrix Download PDF

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US3821841A
US3821841A US00281620A US28162072A US3821841A US 3821841 A US3821841 A US 3821841A US 00281620 A US00281620 A US 00281620A US 28162072 A US28162072 A US 28162072A US 3821841 A US3821841 A US 3821841A
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beryllium
titanium
accordance
powder
composite
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V Goodwin
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Materion Brush Inc
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Materion Brush Inc
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Priority to FR7320383A priority patent/FR2196393A1/fr
Priority to JP48069960A priority patent/JPS4953512A/ja
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/02—Pretreatment of the fibres or filaments
    • C22C47/025—Aligning or orienting the fibres
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/14—Making alloys containing metallic or non-metallic fibres or filaments by powder metallurgy, i.e. by processing mixtures of metal powder and fibres or filaments
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/10—Refractory metals
    • C22C49/11—Titanium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S29/00—Metal working
    • Y10S29/045—Titanium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S29/00—Metal working
    • Y10S29/047—Extruding with other step
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49801—Shaping fiber or fibered material
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12465—All metal or with adjacent metals having magnetic properties, or preformed fiber orientation coordinate with shape

Definitions

  • ABSTRACT A process for forming fibrous beryllium/titanium composites from separate beryllium and titanium materials wherein the resultant composite consists of continuous Be fibers of selective size, array, placement, and geometry in a matrix of continuous Ti or Ti alloy phase.
  • the process is characterized by surrounding discrete preformed Be shapes or fiber precursor bodies with either powdered or preformed Ti material and extruding a cannister containing this assembled body at a temperature of from 1,350 to 1,525F. to a reduction ratio of from 6/1 to 100/ 1 or greater to form a consolidated Be/Ti composite having a very limited but discernible intermetallic reaction zone of titanium beryllide formed in situ.
  • the yield strength of the composite can, if desired, be substantially improved by cold working at 70% to 80% of the ultimate tensile strength.
  • Composite beryllium titanium bodies so fabricated have tensile properties superior to those of Be/Ti composites fabricated up to 1,300F. and superior ductility, toughness and strength to those of Be/Ti composites made from blended Be and Ti powders hot extruded at 1,350F. to 1,525F.
  • These materials may be fabricated by known techniques into aircraft engine parts, e.g., gas turbine compressor blades, vanes and shafts. They would also be useful in other shaft applications requiring high modulus and low weight such as high speed machinery.
  • Be and titanium materials can be bonded together and mutually reinforced by permitting a limited interaction between contacting areas of adjacent Be-Ti material to form an amount of titanium beryllide sufficient to join strongly together, but insufficient to interfere with the desirable individually contributed properties of the Be and Ti and render the product brittle.
  • Fabrication of Be/Ti composites has already been investigated and reported by Abkowitz in US. Pat. No. 3,475,142. Schmidt in US. Pat. No. 3,609,855 describes a method of hot rolling assemblies of Be/Ti into composite ribbon.
  • Abkowitz limited the temperature of processing treatment to 1,300F. and below in order to ensure against the formation of titanium beryllide interaction products between beryllium and titanium particles.
  • Such intermetallic structures are recognized as being brittle and causing nonductile bonds leading to premature failure under stressing.
  • a Be/Ti composite with an E 29 X 10 psi and p 0.10 lbs./cu.in. would have a 75% higher natural resonant frequency than steel, all other things being equal.
  • the Be/T i composite can thus safely operate at approximately 75% higher speeds and have the further advantage of weighing about one-third less than that of an equally sized shaft of steel.
  • a fibrous Be/Ti composite fabricated by this invented process would be the customized array of Be fibers in the cross section. For instance: if a composite beam were to be desired which was subjected to bending in use, then a high population of continuous Be fibers could be placed in the outer area of the cross section so as to increase theelastic modulus selectively. Thus, the beam could very beneficially be stiffened by selective fiber placement in areas of maximum bending strain by selective concentrated use of Be fibers there. In less critical areas where bendpresent work has found in processing from l,375F.
  • the present work departs from that of Schmidt in that he uses exclusively the process of hot rolling and is concerned with fabricating composite ribbon only.
  • One purpose of the present invention is to provide a beryllium/titanium composite material having a modulus of elasticity substantially greater than that of titanium (16 X 10 psi), a density similar to or slightly greater than that of aluminum (0.100 to 0.135 lb. per cubic inch), a tensile ductility in the longitudinal direction of 2% or greater combined with a transverse direction elongation of 1.0% or greater, and a notched Charpy impact strength of 5 foot pounds or greater at room temperature.
  • These characteristics are considered by aircraft manufacturers to be worthy properties ing strains were low less volume per cent of Be and more of Ti material could be employed to improve the ductility, toughness, impact strength and tensile strength in this area as well as lower overall cost.
  • the present process eliminates many of the steps taught by the prior art, enables the utilization of commercial beryllium and commercial titanium materials without sacrificing raw material and processing savings.
  • the present process further enables the use of higher hot working temperatures at which extrusion can be effected more readily allowing greater reductions, lower loads on tooling or fabrication of more complex shapes.
  • the present process produces fibrous composite material of mechanical properties and ductility especially in the direction transverse to working higher than attained by a powder-powder composite process.
  • the fibers of beryllium are continuous, that is, they extend in an axial direction, and preferably from end-toend of the extruded member.
  • the term fiber precursor body is intended to identify the form the beryllium component takes prior to extrusion after which it assumes a more nearly fibrous form than being of relatively small cross-sectional area, but very much elongated as well as fully densified due to the extrusion.
  • the fiber precursors may be shaped as rods, bars, wires, etc. of varying degrees of density ranging from loose powder to fully densified beryllium.
  • beryllium/titanium composite containing from 40 to 60 volume percent beryllium, balance titanium or titanium alloy.
  • present invention is also applicable to fibrous composites of beryllium and titanium outside of the 40 to 60% by volume beryllium for which uses may be contemplated in aircraft structures and elsewhere.
  • the present invention is in a process for producing and a product produced by forming an extrudable beryllium/titanium assembly of discrete beryllium fiber precusor bodies extending from end-to-end of said assembly; filling the balance of the assembly with titanium or titanium alloy to form a continuous matrix surrounding said bodies; encasing the assembly in an extrusion cannister and extruding the cannister at a temperature of from l,350 to l,525F at a reduction ratio of from 6:1 to 100:1 or greater to form a solid fibrous beryllium/titanium composite.
  • Be preforms Ti powder
  • Be preform fiber precursor bodies made from wrought Be or some form of rigidized or consolidated powders are maintained in a desired array by mechanical means or adhesive fixturing.
  • the Be preforms are then surrounded by a material of Ti powder poured in around the preforms and the powder vibrated or tamped to as high a density as possible. Additional powder may be placed in the ends of the extrusion billet to supply additional volume of the low density powder which will flow in place during hot extrusion. (See FIG. 2.)
  • the Ti material component may be a solid cast or wrought body processed commercially into which holes have been machined or otherwise prepared to receive the Be component. These holes can be filled with Be powder as the fiber precursor body which can be at least partially consolidated by vibration, tamping or cold pressing.
  • Be powderTi powder Another alternative is that both the titanium and beryllium be in powder form.
  • a thin separator such as plastic tubing or paper of the proper diameter is held in the desired way by mechanical means. Ti powder is poured around the thin wall plastic tubing and Be powder is placed inside the thin wall plastic tubing. The assembly is then vibrated or tamped to as high a density as possible. The thin-wall separator is then mechanically removed.
  • Aluminum or Ti or Ti alloy thin-walled tubing can also be used as separators.
  • the separators may remain in place and alloy with either the Ti or Be during subsequent processing.
  • the canned extrusion billet assembly having the desired array of Be and a Ti matrix may then be outgassed at 600 to 1,300F. in the presence of a suitable vacuum of approximately 0.1 micron of Hg absolute pressure (optional).
  • the extrusion billet assembly may be cold pressed or isopressed at 5,000 60,000 psi before extrusion. lsostatic pressing may so distort the can as to necessitate the removal of the compacted body, machining to desired size and recanning (optional).
  • the canned or re-canned billet is heated uniformly up to the desired extrusion temperature of l,350 to 1,525F. and held for a minimal time period.
  • the heated billet is then extruded to at least a 6/1 reduction ratio and up to approximately 50/1 reduction ratio using commercial hot extrusion techniques.
  • the extruded solid Be/Ti composite is cooled to room temperature and stripped from its steel jacket by mechanical means or pickling in nitric acid.
  • Resultant extruded beryllium/titanium composite material after cooling to room temperature may be cold worked at to of ultimate tensile strength in order to remove normal residual tensile stresses present in the beryllium phase due to incompatibilities in contraction and modulus of elasticity and to impose a new residual compressive stress on the beryllium phase.
  • the material With such prestressing, the material then elastically deforms in tension according to its true modulus of elasticity which is in the range of from 26 to 32 X 10 pounds per square inch up to high stress levels.
  • the 0.2% offset yield strength an important engineering design parameter, has then been substantially raised.
  • the processing temperatures of the present invention are generally higher than those previously used for the reason that hot working processes such as extrusion are facilitated.
  • pressures required to extrude decrease with higher temperature, and greater reduction of cross section can be effected for equivalent pressures at 1,350 1,525F as compared to 900 1 ,300F used in prior art.
  • lower pressures are required, resulting in longer tool life.
  • beryllium/titanium composites hot extruded at l,350 1,525F exhibit a tensile strength comparable to or greater than those extruded at lower temperatures, but greater ductility than those extruded at 1,300F and below.
  • a titanium beryllide structure has been metallographically identified between contacting beryllium and titanium particles when the compositie is extruded at 1,350F and higher. Development of this phase may result in a stronger bond providing greater strength and ductility. Material extruded at 1,525F and above exhibits lower strength and ductility perhaps because the interparticle titanium beryllide structure has grown excessively thick.
  • FIG. 1 is a diagrammatic and schematic crosssectional view of an array of beryllium rods of two different diameters arranged on and supported on a mild steel disc. The interstices will be filled with titanium alloy powder to form the extrusion assembly.
  • FIG. 2 is a diagrammatic and schematic crosssectional view of a canister prior to extrusion.
  • FIG. 3 shows diagrammatically and schmatically an array useful in making a hollow fibrous beryllium reinforced titanium composite shaft.
  • FIG. 4 shows diagrammatically and schematically a cross-sectional view of a cannister for a hollow shaft prior to extrusion.
  • FIG. 5 shows diagrammatically and schematically a cross-sectional view of an extrusion assembly of beryllium bars in a titanium matrix, the bars being arranged in a star pattern.
  • the beryllium used in accordance with this work is commercially available and comes from a vacuum-cast metal source.
  • Beryllium powder is comminuted by chipping vacuum-cast billets and grinding by known procedures.
  • Solid beryllium preform shapes useful as fiber precursors are fabricated from powders, preferably containing from 0.2% to 6% by weight BeO, usually by the widely used commercial process of vacuum hot processing, and resultant dense bodies are then machined into desired Be preform shapes.
  • preform shapes from beryllium powder can be fabricated by either cold pressing alone, or by cold pressing and sintering in vacuum at l,l50 1,250C or by cold pressing, sintering and coining at from room temperature up to 1,200F. (and optionally resintering).
  • preform shapes from beryllium powder can be made by mixing with common binders to achieve porous but handleable fiber precursor bodies.
  • Preform shapes can also be obtained from commercially available wrought forms of Be including extrusions, sheet metal or forgings. It is such preform shapes, e.g. rods, bars, wire, etc., which are preferably used as beryllium fiber precursors in fabricating the composites of the present invention.
  • Titanium materials may consist of up to 100% Ti or a commercially available powdered titanium alloy. These powders may be produced commercially by the conventional hydridedehydride process which is well known, or by other commercial processes. Generally, these powders have a particle size in, or particle size distribution over, the range of from mesh to +325 mesh, and preferably no more than 3 X 10 inch.
  • the solid Ti material also used in the present process can be up to Ti or of commercial Ti alloy composition. Such solid Ti material is commercially available in a vacuum are cast and wrought form in a wide variety of shapes and sizes adaptable to use in this process.
  • Example No. 1 (50 Be/50 Ti by volume Fibrous Composite) 1. Material Input Be-Vacuum hot pressed Be powders of full density extruded and machined into inch dia. (10 each) and inch dia.(6l each) rods.
  • Ti-6AI-4V alloy powder of hydride derivation and of 50 +325 mesh size Ti-6AI-4V alloy powder of hydride derivation and of 50 +325 mesh size.
  • FIG. 1 Array Configuration in Extrusion Billet. See FIG. 1. There is here shown a plurality of beryllium rods held in a drilled circular mild steel disc 0.5 inch thick and 4.480 inches in diameter, the larger diameter rods being arranged at the apices of equilateral triangles. The free space is ultimately filled with the titanium alloy powder.
  • the canister is composed of a plug 10 having integral therewith a drilled plate 12 into which the prefabricated beryllium rods 14 are inserted as indicated in FIG. 1.
  • a steel tubular body 16 having a wall thickness of approximately 0.25 inch and, in the specific example involved, being 5 inches in outside diameter. This is made of mild steel.
  • the titanium alloy powder fills the spaces between the beryllium rods 14 and, because of its powder condition, extends beyond the extremities of the beryllium rods.
  • the canister is sealed with a plug 18 drilled to provide an exit bore 20 and having a stainless steel evacuation tube 22 welded thereto. The evacuation tube is to enable removal of gases from the interior of the canister after which it is sealed.
  • Ti Ti 6A1 4V alloy powder of hydride deviation and of 50 +325 mesh size Ti Ti 6A1 4V alloy powder of hydride deviation and of 50 +325 mesh size.
  • Example No. 3 (50 Be/SO Ti by volume fibrous composite) 1. Comment Example No. 3 is the re-extruded product of Example No. l.
  • beryllium rods 24 are mounted in a base 26 formed of mild steel in a circular pattern.
  • the outside radius of the plug portion 26 is 2.25 inch
  • the inner radius is 1.625 inches
  • the centers of the beryllium rods 24 are disposed on a radius of 1.937 inch.
  • Extrusion billet assembly C With reference to FIG. 4, there is provided a nose plug 26 which carries the beryllium rods 24 as indicated in FIG. 3.
  • the canister generally indicated at 28 is provided with a tubular body 30 and carries a center core 32.
  • the interstices between the beryllium rods and the center core 32 are filled with titanium alloy powder 34 as above indicated.
  • a tail plug 36 encloses the canister and includes a tubular member 38 extending therethrough for evacuating the system and ultimate sealing.
  • the extrusion canister of FIG. 4 is approximately 22.5 inches long and the elements are formed except Where indicated of hot rolled steel.
  • the canister is 5 inches in diameter and the walls 025 inch thick.
  • Extrusion Cannister outgassing 5. Extrusion temperature 6. Extrusion ratio 7. Extruded properties Prestressed to Property As Extruded I00 ksi (tension) Long. Transv. Long.
  • Be powder of 50 +l00 mesh was cold pressed at 10,000 psi into 0.30 X 0.22 inch cross-section retangular bars. These bars were assembled into a can and surrounded by Ti-6Al-4V powder as shown in the FIG. 5:
  • FIG. 5 there is shown diagrammatically and schematically another arrangement for beryllium bars 40 having the spaces therebetween filled with titanium powder 42.
  • the structure of the canister is essentially the same as shown in FIGS. 2 and 4.
  • the can was outgassed and extruded at 1,450F. 20:1
  • the impact resistance of Be/Ti fibrous composites is markedly superior to monolithic Be when both are measured by the well known Charpy test.
  • the exact extent to which these composites resist impact is dependent on the final size of the fibers in the composite. For instance, in Example 1 the fiber size was coarse and Charpy was 5.9 foot-pounds. The re-extruded product of Example 1 in which the fibers were of 1/10 of Example 1 was also tested. The Charpy impact in this case increased to 8.8 foot-pounds.
  • alloy powders of hydride derivation 20 mesh particle size or smaller and fractions thereof.
  • Primary densification data is listed below Array configuration varied Extrusion billet assembly varied Extrusion cannister outgassing varied Extrusion ratio 6:1 to 50:1 Extrusion temperature 1,350 1,525F Properties
  • the type of Be material and Ti material or its form used had little significance in respect to the longitudinal properties measured in the direction of extrusion of the extruded fibrous composite product. That is to say, whether dense Combinations of Be and Ti Material Forms Used to Assembly Extrusion Billet for Composites Ti & Ti Ti & Ti Alloy Alloy Powder Powder Vibrated Cold 7 Solid or Pressed Ti & Ti
  • the resultant extruded fibrous composite had similar longitudinal mechanical properties provided the final composite had an identical array and full densification of the beryllium as well as the titanium was accomplished.
  • an extrudable beryllium/titanium assembly of: l. discrete elongated beryllium fiber precursor bodies extending axially of said assembly; 2. filling the balance of the assembly with. titanium to form a continuous titanium matrix surrounding said bodies; 1 b. encasing said assembly in an extrusion canister;
  • beryllium fiber precursor is formed from beryllium powder having a particle size no greater than 3 X 10 inch.
  • beryllium fiber precursors are composed of beryllium powder rigidized with a binder.
  • titanium alloy is Ti-6Al-4V alloy.
  • a process in accordance with claim 1 which also includes the step of degassing the extrusion canister to less than 10 microns of mercury.
  • a process in accordance with claim 1 which includes the step of isopressing the extrudable assembly at a pressure of 30 ksi prior to extrusion.

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  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
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  • Extrusion Of Metal (AREA)
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US00281620A 1972-08-18 1972-08-18 Method for fabricating a beryllium fiber reinforced composite having a titanium matrix Expired - Lifetime US3821841A (en)

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US00281620A US3821841A (en) 1972-08-18 1972-08-18 Method for fabricating a beryllium fiber reinforced composite having a titanium matrix
GB1827673A GB1382972A (en) 1972-08-18 1973-04-16 Process for making fibrous beryllium titanium composites and product produced thereby
FR7320383A FR2196393A1 (enrdf_load_stackoverflow) 1972-08-18 1973-06-05
JP48069960A JPS4953512A (enrdf_load_stackoverflow) 1972-08-18 1973-06-22

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3918141A (en) * 1974-04-12 1975-11-11 Fiber Materials Method of producing a graphite-fiber-reinforced metal composite
US3932936A (en) * 1973-07-21 1976-01-20 Dr. Eugene Durrwachter Doduco Method of manufacturing a ductile silver metallic oxide semi-finished product contacts
US4782992A (en) * 1986-11-21 1988-11-08 Textron Inc. Method of forming articles
US4900599A (en) * 1986-11-21 1990-02-13 Airfoil Textron Inc. Filament reinforced article
US4907736A (en) * 1986-06-27 1990-03-13 Airfoil Textron Inc. Method of forming articles
RU2184011C2 (ru) * 2000-04-19 2002-06-27 Государственное предприятие Всероссийский научно-исследовательский институт авиационных материалов Способ получения полуфабрикатов из титановых сплавов с интерметаллидным упрочнением
USD529057S1 (en) * 2004-08-16 2006-09-26 Williams Advanced Materials, Inc. Sputtering target

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS516160A (en) * 1974-07-05 1976-01-19 Suzuki Metal Industry Co Ltd Saajinguo boshisuru bane zairyo
US4209122A (en) * 1978-12-18 1980-06-24 Polymet Corporation Manufacture of high performance alloy in elongated form
US4933141A (en) * 1988-03-28 1990-06-12 Inco Alloys International, Inc. Method for making a clad metal product

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2940163A (en) * 1954-08-05 1960-06-14 Clevite Corp Alloy clad titanium and method of producing same
US3390985A (en) * 1966-08-10 1968-07-02 Us Interior Consolidation and forming by high-energy-rate extrusion of powder material
US3475142A (en) * 1966-05-13 1969-10-28 Stanley Abkowitz Titanium alloy beryllium composites
US3510275A (en) * 1967-09-18 1970-05-05 Arthur D Schwope Metal fiber composites
US3609855A (en) * 1969-04-25 1971-10-05 Us Navy Production of beryllium ribbon reinforced composites
US3667108A (en) * 1970-04-17 1972-06-06 Us Navy Method of making a beryllium titanium composite
US3681037A (en) * 1969-04-21 1972-08-01 Nuclear Components Inc Titanium-beryllium composites and methods of making

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2940163A (en) * 1954-08-05 1960-06-14 Clevite Corp Alloy clad titanium and method of producing same
US3475142A (en) * 1966-05-13 1969-10-28 Stanley Abkowitz Titanium alloy beryllium composites
US3390985A (en) * 1966-08-10 1968-07-02 Us Interior Consolidation and forming by high-energy-rate extrusion of powder material
US3510275A (en) * 1967-09-18 1970-05-05 Arthur D Schwope Metal fiber composites
US3681037A (en) * 1969-04-21 1972-08-01 Nuclear Components Inc Titanium-beryllium composites and methods of making
US3609855A (en) * 1969-04-25 1971-10-05 Us Navy Production of beryllium ribbon reinforced composites
US3667108A (en) * 1970-04-17 1972-06-06 Us Navy Method of making a beryllium titanium composite

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3932936A (en) * 1973-07-21 1976-01-20 Dr. Eugene Durrwachter Doduco Method of manufacturing a ductile silver metallic oxide semi-finished product contacts
US3918141A (en) * 1974-04-12 1975-11-11 Fiber Materials Method of producing a graphite-fiber-reinforced metal composite
US4907736A (en) * 1986-06-27 1990-03-13 Airfoil Textron Inc. Method of forming articles
US4782992A (en) * 1986-11-21 1988-11-08 Textron Inc. Method of forming articles
US4900599A (en) * 1986-11-21 1990-02-13 Airfoil Textron Inc. Filament reinforced article
RU2184011C2 (ru) * 2000-04-19 2002-06-27 Государственное предприятие Всероссийский научно-исследовательский институт авиационных материалов Способ получения полуфабрикатов из титановых сплавов с интерметаллидным упрочнением
USD529057S1 (en) * 2004-08-16 2006-09-26 Williams Advanced Materials, Inc. Sputtering target

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GB1382972A (en) 1975-02-05
FR2196393A1 (enrdf_load_stackoverflow) 1974-03-15
JPS4953512A (enrdf_load_stackoverflow) 1974-05-24

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