US3653980A - Method of obtaining exceptional formability in aluminum bronze alloys - Google Patents

Method of obtaining exceptional formability in aluminum bronze alloys Download PDF

Info

Publication number
US3653980A
US3653980A US45447A US3653980DA US3653980A US 3653980 A US3653980 A US 3653980A US 45447 A US45447 A US 45447A US 3653980D A US3653980D A US 3653980DA US 3653980 A US3653980 A US 3653980A
Authority
US
United States
Prior art keywords
alloy
percent
deforming
per minute
aluminum
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US45447A
Other languages
English (en)
Inventor
George H Eichelman Jr
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Olin Corp
Original Assignee
Olin Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Olin Corp filed Critical Olin Corp
Application granted granted Critical
Publication of US3653980A publication Critical patent/US3653980A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/08—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of copper or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C9/00—Alloys based on copper
    • 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
    • Y10S420/00—Alloys or metallic compositions
    • Y10S420/902—Superplastic

Definitions

  • ABSTRACT The instant disclosure teaches a method of obtaining exceptional formability in aluminum bronze alloys comprising: providing an aluminum bronze alloy containing from 8.0 to 1 1.8 percent aluminum plus 0.5 to 5.0 percent iron, balance essentially copper, cold working said alloy and annealing from l,000 to 1,400 F.
  • the present invention relates to a method for obtaining exceptionally high formability of aluminum bronzes, and the article produced thereby.
  • the aluminum bronze alloys are well-known for good formability at elevated temperatures, i.e., they may be readily hot rolled, forged, or extruded when in the all beta or predominantly all beta phase condition at elevated temperatures.
  • Such alloys are extremely versatile and have a wide variety of uses. exemplicative of which are: corrosion resistance parts, such as condenser tubes or valves; metal bellows and springs where strength and fatigue resistance are important; heat resistance parts in which the resistance to corrosion at high temperatures is required, such as parts for internal combustion engines; wear resistance parts such as guides and ways, and metal and glass forming dies.
  • the method of the present invention provides for super plasticity of the iron containing aluminum bronze alloys at elevated temperatures.
  • Aluminum bronze alloys exhibiting superplasticity would particularly find wide application in vacuum forming processes wherein high tensile properties are desired in the formed part.
  • the process of the present invention is also readily applicable to the manufacture of articles of intricate shapes by forcing the aforementioned alloys into molds or dies while in the super plastic state and thereby taking advantage of the increased plasticity of the alloys.
  • the process of the present invention comprises; (A) providing an aluminum bronze alloy comprising from 8.0 to 11.8 percent aluminum and from 0.5 to 5.0 percent iron, balance essentially copper, (B) cold reducing said alloy and annealing said alloy at a temperature from about l,000 to l,400 F. for at least 2 minutes (C) superplastically deforming said alloy in the temperature range of about l,300 to l,700 F. and preferably in the range of l,400 to l,600 F.
  • step (C) after the deforming of step (C) into the desired shape the formed article may be rapidly cooled to at least below 1,000 F. in order to retain a high proportion of beta phase and to convert the beta phase to martensite as, for example, with a water or oil quench while the formed article is in the mold, or by forming into cold molds.
  • step (B) The purpose of the aforementioned step (B) is to insure optimum refinement of the grain structure of the alloy.
  • the maximum time of annealing is not critical so long as grain growth does not become excessive, but is generally not longer than about 2 hours.
  • Step (B) is preferably repeated at least once, and is preferably repeated a plurality of times, in order to insure obtaining a requisite fine grain size.
  • the grain size is normally less than about 0.065 mm and generally ranges from about 0.005 to 0.020 mm.
  • the percentage cold reduction of step (B) although not critical is preferably at least percent, and more preferably is at least 50 percent, and generally ranges from about 40 to about 90 percent.
  • the alloy after the aforementioned cold reducing step need not be annealed since the alloy will recrystallize to the requisite fine grain structure at the deforming temperature.
  • the alloy provided may be hot reduced at a temperature of from about l,000 to 1,400 rather than cold reducing as in step (B) in order to refine the grain structure of the alloy, thus eliminating the need of annealing.
  • the alloy is preferably hot reduced at least 20 percent and preferably for a plurality of times while in the aforementioned temperature range in order to develop the requisite fine grain structure.
  • the alloy may then be deformed as in step (C)
  • the aforementioned alloying substituent of iron contributes to the development of the requisite fine grain size.
  • Naturally impurities may also be present such as, for example, tin, zinc, lead, nickel, silicon, silver, phosphorus, magnesium, antimony, bismuth, and arsenic.
  • the surprising super plasticity found when the aforementioned alloys are processed in accordance with the present invention appears to be associated with thecombination of the relatively small grain size of the alloy and the proportions of the alpha and beta phases in the alloy at the forming temperature of about 1,300 to l,700 F.
  • the proportion of the beta phase in the alloy may range from nil up to substantially percent, depending upon the aluminum content in the alloy and the temperature, i.e., the aluminum content within the range of 8.0 to l 1.8 percent. Optimumly, however, the beta phase content ranges from about 40.0 to 70.0 percent which corresponds to an aluminum content of about 9.0 to 10.0 percent over the given temperature range.
  • the optimum beta content of about 40.0 to 70.0 percent allows a higher strain rate to be employed for a given elongation in the forming of step (C) and is thus of practical importance as, for example, in providing for increased production of formed articles.
  • the deformation or forming is such as to provide for superplasticity and normally conforms to a strain rate of less than about 3.0 per minute and preferably about 0.5 perminute or less for applications where a particularly high elongation is desired.
  • the strain rate of the present invention ranges from about 0.03 per minute to about 0.5 per minute for practical considerations.
  • the strain rate of the present invention is defined as the cross head speed in inches per minute divided by the initial gage length of 2 inches, conforming to the test conditions employed with tensile specimens, which equals a numerical value.
  • the formed article may be tempered if desired, at a temperature range of from about 500 to 900 F. for at least 5 minutes and preferably from 600 to 750 F. and preferably not longer than 4 hours in order to avoid coarsing of the structure, in order to develop a higher tensile strength and a particularly higher yield strength.
  • the formed article may be reheated to the temperature range of l,l00 to l,800 F., and then rapidly cooled and tempered.
  • the present invention is applicable to an aluminum bronze having a fine grain size and containing the beta phase with preferred beta phase content ranging from about 40.0 to 70.0 percent, and provides formed articles characterized by high tensile properties.
  • EXAMPLE I An aluminum bronze alloy containing 9.8 percent aluminum, 4 percent iron the balance essentially copper was chill cast in the form of l X l X 4 V2 inch bar and processed to 0.050 inch gage by hot rolling and cold rolling and annealing at l,l50 F. a plurality of times resulting in a grain size of 0.010 mm in diameter. The alloy was then pulled in tension at a cross head speed of 1.0 inch per minute (05 min. after reheating to l,450 F. The samples tested were of 0.050 inch strip with a gage length of 2.0 inch and a gage width of one half inch and tested at a cross head speed of l inch per minute. The elongation was found to be uniform and about 400 percent. This elongation was essentially free of local necking in the fracture characteristics of super plasticity.
  • Example II The alloy of Example I was subsequently water quenched after a forming operation and then tempered at 650 F. for 1 hour.
  • Tensile testing showed an ultimate tensile strength of the alloy of about 150,000 psi and a yield strength of 1 10,000 psi.
  • FIG. I shows the elongation properties of a series of copperaluminum alloys containing about 4.0 percent iron when tested at various temperatures and having varying beta contains at a cross head speed of 1 inch per minute (0.5 min. It is seen that the percent elongation increases as the proportion of the beta phase changes to within the range of about 40.0 to 70.0 percent.
  • FIG. 11 shows the elongation properties of a copper aluminum alloy containing 9.8 percent aluminum and 4.0 percent iron, balance essentially copper at a cross head speed of 1.0 inch per minute and 6 inch per minute (0.5 min. and 3.0 min. at varying temperatures. This figure clearly shows the increase of plasticity of the alloy as the strain rate decreases. It is to be noted that due to limited cross head travel 370 percent elongation is the upper value of testing, and thus higher elongation values for the 9.8 percent aluminum, 4 percent iron alloy at a cross head speed of l inch/min. is anticipated. The reported higher value resulted from elongation of the sample during removal from the furnace.
  • FIG. 111 shows the elongation properties of the alloy of Example lll versus beta content of the alloy when pulled in tension at a cross head speed of 0.1 and 1 inch per minute (0.05 min. and 0.5 min.
  • a method of obtaining exceptional formability in aluminum bronze alloys which comprises:
  • steps B and C are repeated at least once and said reducing is at least 10 percent.
  • step (D) said alloy is rapidly cooled and then reheated to the temperature range of from 500 to 900 F. for at least 5 minutes.
  • a method for obtaining exceptional formability in aluminum bronze alloys which comprises:

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Forging (AREA)
US45447A 1970-06-11 1970-06-11 Method of obtaining exceptional formability in aluminum bronze alloys Expired - Lifetime US3653980A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US4544770A 1970-06-11 1970-06-11

Publications (1)

Publication Number Publication Date
US3653980A true US3653980A (en) 1972-04-04

Family

ID=21937919

Family Applications (1)

Application Number Title Priority Date Filing Date
US45447A Expired - Lifetime US3653980A (en) 1970-06-11 1970-06-11 Method of obtaining exceptional formability in aluminum bronze alloys

Country Status (5)

Country Link
US (1) US3653980A (fr)
AU (1) AU2992571A (fr)
DE (1) DE2129125A1 (fr)
FR (1) FR2096196A5 (fr)
IT (1) IT939299B (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3997369A (en) * 1974-05-13 1976-12-14 The British Aluminium Company Limited Production of metallic articles
US4793876A (en) * 1984-11-21 1988-12-27 Sumitomo Electric Industries, Ltd. Sound-deadening and vibration-absorbing β'-martensite type aluminum-bronze alloy

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3788902A (en) * 1972-11-24 1974-01-29 Olin Corp Process for improving the elongation of grain refined copper base alloys
DE3065931D1 (en) * 1980-03-03 1984-01-26 Bbc Brown Boveri & Cie Process for making a memory alloy

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3176410A (en) * 1958-02-12 1965-04-06 Ampco Metal Inc Aluminum bronze cylindrical shell
US3287180A (en) * 1963-12-05 1966-11-22 Olin Mathieson Method of fabricating copper base alloy
US3290182A (en) * 1965-05-25 1966-12-06 Olin Mathieson Method of making aluminum bronze articles
US3347717A (en) * 1966-10-04 1967-10-17 Olin Mathieson High strength aluminum-bronze alloy
US3399084A (en) * 1965-10-11 1968-08-27 Olin Mathieson Method of making aluminum bronze articles
US3464865A (en) * 1967-04-11 1969-09-02 Olin Mathieson Process for treating copper base alloys

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3176410A (en) * 1958-02-12 1965-04-06 Ampco Metal Inc Aluminum bronze cylindrical shell
US3287180A (en) * 1963-12-05 1966-11-22 Olin Mathieson Method of fabricating copper base alloy
US3290182A (en) * 1965-05-25 1966-12-06 Olin Mathieson Method of making aluminum bronze articles
US3399084A (en) * 1965-10-11 1968-08-27 Olin Mathieson Method of making aluminum bronze articles
US3347717A (en) * 1966-10-04 1967-10-17 Olin Mathieson High strength aluminum-bronze alloy
US3464865A (en) * 1967-04-11 1969-09-02 Olin Mathieson Process for treating copper base alloys

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3997369A (en) * 1974-05-13 1976-12-14 The British Aluminium Company Limited Production of metallic articles
US4793876A (en) * 1984-11-21 1988-12-27 Sumitomo Electric Industries, Ltd. Sound-deadening and vibration-absorbing β'-martensite type aluminum-bronze alloy

Also Published As

Publication number Publication date
IT939299B (it) 1973-02-10
DE2129125A1 (de) 1971-12-16
FR2096196A5 (fr) 1972-02-11
AU2992571A (en) 1972-12-14

Similar Documents

Publication Publication Date Title
US4055445A (en) Method for fabrication of brass alloy
US2249349A (en) Method of hot working an aluminum base alloy and product thereof
US3232796A (en) Treatment of aluminum-magnesium alloy
CH682326A5 (fr)
US3645800A (en) Method for producing wrought zirconium alloys
US3420717A (en) Metal softening process and product thereof
JP7157158B2 (ja) マグネシウム合金板材およびその製造方法
US3841919A (en) Aluminum-silicon-magnesium ternary superplastic alloy and method for manufacture thereof
US2257708A (en) Method of working and heat treating cu-be alloys
US2506788A (en) Method of enhancing physical properties of aluminum base alloys containing zinc and magnesium
US3653980A (en) Method of obtaining exceptional formability in aluminum bronze alloys
US2381714A (en) Method of thermally treating aluminum base alloy ingots and product thereof
US3333989A (en) Aluminum base alloy plate
US2365208A (en) Manufacture of copper base alloy products
US2249353A (en) Method of working aluminum and product thereof
US2126827A (en) Copper-cobalt-zinc alloy
US2670309A (en) Metal-working process and product
US3923555A (en) Processing copper base alloys
US3287180A (en) Method of fabricating copper base alloy
US4007039A (en) Copper base alloys with high strength and high electrical conductivity
US2804408A (en) Process of treating tin bronze
US2275188A (en) Double aged copper base alloys
US3580747A (en) Production of aluminum zinc magnesium alloy articles
US3366477A (en) Copper base alloys
US3880679A (en) Method of forming zinc-aluminum alloys with good machinability