US3876474A - Aluminium base alloys - Google Patents

Aluminium base alloys Download PDF

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Publication number
US3876474A
US3876474A US273639A US27363972A US3876474A US 3876474 A US3876474 A US 3876474A US 273639 A US273639 A US 273639A US 27363972 A US27363972 A US 27363972A US 3876474 A US3876474 A US 3876474A
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US
United States
Prior art keywords
aluminium
heat
base alloy
treatable
superplastic
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
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US273639A
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English (en)
Inventor
Brian Michael Watts
Edward Frederick Emley
Michael James Stowell
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.)
Superform Metals Ltd
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British Aluminum Co Ltd
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Filing date
Publication date
Priority claimed from GB3392271A external-priority patent/GB1387586A/en
Application filed by British Aluminum Co Ltd filed Critical British Aluminum Co Ltd
Priority to US05/509,406 priority Critical patent/US3984260A/en
Application granted granted Critical
Publication of US3876474A publication Critical patent/US3876474A/en
Assigned to SUPERFORM METALS LIMITED; reassignment SUPERFORM METALS LIMITED; ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BRITISH ALUMINIUM COMPANY PLC THE, TI (GROUPS SERVICES) LIMITED, TI GROUP PLC
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • 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
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
    • 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

  • aluminium-base alloys consisting of the elements normally present in either non-heat treatable aluminium-base alloys containing at least 5%Mg or at least 1%Zn or heat-treatable aluminium-base alloys containing one or more of the elements Cu, Mg, Zn, Si, Li and Mn in known combinations, and at least one of the elements Zr, Nb, Ta and Ni in a total amount of at least 0.30% substantially all of which is present in solid solution, are superplastically deformable.
  • the remainder of the superplastically deformable alloy may be the normal impurities and incidental elements known to be incorporated in heat-treatable and non-heat treatable aluminium-base alloys.
  • the alloy contains at least 0.30%Zr and preferably at least 0.40%Zr.
  • the alloys of the invention may in some cases be deformed superplastically under isothermal conditions but it has been found advantageous to heat the alloy quickly to the super-plastic forming temperature and- /or allow the temperature to rise whilst the deformation is in progress.
  • a superplastic material will show a strain rate sensitivity (nz-value) of at least 0.3 and a uniaxial tensile elongation at temperature of at least 200%, m-value being defined by the relationship a n 6''" where represents flow stress, 1 a constant, e strain rate and m strain rate sensitivity index.
  • No known aluminium-base alloy can be superplastically deformed other than the Al-Cu entectic composition which contains 33% copper and has neither the low density nor the good corrosion resistance characteristic of aluminium alloys.
  • a superplastically deformable aluminium-base alloy consists of an aluminium-base alloy selected from non'heat treatable aluminium-base alloys containing at least 5%Mg or at least 1%Zn and heat-treatable aluminiumbase alloys containing one or more of the elements Cu, Mg, Zn, Si, Li and Mn in known combinations and quantities, and at least one of the elements Zr, Nb, Ta and Ni in a total amount of at least 0.30% substantially all of which is present in solid solution, the remainder being normal impurities and incidental elements known to be incorporated in the said aluminium-base alloys.
  • a method of making a superplastically deformable aluminium-base alloy semi-fabricated product comprises casting a liquid alloy having a composition according to the immediately preceding paragraph at a temperature of at least 775C to produce a cell size in the cast alloy not exceeding /.LM and subjecting the cast alloy to plastic working at a temperature not substantially in excess of 550C.
  • cell size is meant secondary dendrite arm spacing.
  • the invention also extends to an aricle shaped by the plastic forming of an alloy according to the said one aspect of the invention.
  • heat-treatable alloys are meant those classes of alloys in which the mechanical properties can be improved by precipitation hardening treatments, for example alloys of the Al-Cu, Al-Cu-Mg, Al-Mg-Si and A]- Zn-Mg systems.
  • non-heat-treatable alloys are meant those classes of alloys in which the mechanical properties cannot be significantly improved by precipitation hardening treatments, for example alloys of the Al-Mn, Al-Mg and Al-Zn systems.
  • zirconium (Zr) in the alloy according to the invention as niobium (Nb), tantalum (Ta) and nickel (Ni) have been found to be less effective than zirconium in inducing superplastic behaviour in the alloy. These four elements have low solubility, high temperature coefficient of solubility and diffuse only very slowly in aluminium even at temperatures as high as 500C. When zirconium only is used in the alloy it is used in a quantity of at least 0.30% and preferably of at least 0.40%.
  • the alloys according to the invention owe their superplastic properties to the presence of a supersaturated solid solution of one or more of the elements Zr, Nb, Ta and Ni in a sufficient quatity physically to restrict aluminium grain growth by giving rise at the temperatures employed for hot forming to a fine sub-optical precipitate capable of restricting grain boundary movements.
  • the formation of such a fine sub-optical precipitate has been verified in alloys containing each ofthe elements Zr, Nb, Ta or Ni, but it was not found with Cr. or Mn.
  • Zirconium is already known to confer on certain aluminium-base alloys both grain refinement of the cast alloys and to restrict grain coarsening of the worked alloys.
  • the maximum liquid solubility of zirconium in aluminium at the peritectic temperature is approximately 0.11% and additions of zirconium to aluminium alloys do not normally exceed 0.20%.
  • These additional elements include Cu, Mg, Zn, Li and Si in such combinations and in such quantitites as are commonly used in heat treatable aluminium alloys and Mg and Cu in such combinations and quantities as may be used to produce non-heat treatable alloys of Al-Mg or Al-Zn systems containing at least 5% Mg or at least 1% Zn respectively.
  • the alloys according to the invention may in some h yet f H W cases be deformed superplastically under isothermal 0 8 pie l0 conditions following prolonged soaking at superplastic C to .5 forming temperaure but it has been found advantao 8 (Z prefcmbii geous to heat the alloy quickly to the superplastic forming temperature and/or allow the temperature to rise whilst the deformation is in progress.
  • Alloys containing the additional ferences i h lt bt i ed by the two forming elements lz may need a higher forming temperature techniques on four other alloy compositions together range for best results e.g. up to 550C. with isothermal data on two further compositions.
  • the alloy according to the invention may contain the impurities normally to be found in heat treatable and non-heat-treatable aluminum-base alloys and one or more of the incidental elements known to be added to such aluminium-base alloys. These incidental elements include in percentages by weight:
  • the alloy of the present invention is cast by temperatures in the range 775C to 925C and preferaably above 800C. For best results a casting temperature in the range 825C to 900C is preferred.
  • the solidification rates of the alloys according to the invention are designed to be such that the average cell size does not exceed 30 uM, and preferably does not exceed 25 uM. In this way the miniumum dissolved zirconium content required, believed to be 0.25% represents 0.2% in excess of the equilib rium solubility of zirconium at 500C.
  • the approximate proportion of dissolved zirconium in an alloy of known total zirconium content can be determined by microprobe analysis; alernatively optical microscopy can be used to provide a rapid check as to whether or not there is a substantial proportion of the zirconium not in solution, the phase ZrAl being easily recoognisable.
  • the alloy conains Nb or Ta in place of Zr, a high casting temperature and fine cell size are required; with Ni in place of Zr a high casting temperature is not essential.
  • the alloys of the present invention may be prepared by splat cooling or spray casting in known manner or by compacting blown powder.
  • aluminium-base alloys containing copper as an essential alloying element are now described by way of example.
  • the copper content is in the range 2.5% to 7% and particularly in the range 3.5% to 6.5%.
  • a copper content of 5.75% to 6.25% may be used.
  • a substantially higher copper content than 7% can be tolerated where the alloy is to be extruded rather than rolled or can be pre-extruded prior to rolling, for example up to 10%.
  • Magnesium may be added in amounts up to about 0.5%; manganese and cadmium may each be added in amounts preferably not exceeding 0.25%, whilst small amounts ranging from 0 to 0.2% of one or more grain refining elements Ti, Ta and Sc may be added to assist in obtaining a fine grained cast structure.
  • Germanium may also be added in quantities up to 0.5% to control ageing behaviour.
  • the alloy when cast it appears to be necessary for the alloy when cast to contain a minimum level of zirconium in supersaturated solid solution so that the zirconium is then available to precipitate in such a manner during the hot forming operation as will assist in the production or maintenance of a very fine grained structure of average grain size below uM similar to that observed in other superplastic materials.
  • This minimum content of dissolved zirconium will not be achieved unless the total zirconium content of the metal is at least 0.30%, and preferably at least 0.40%.
  • the copper content should desirably exceed the solid solubility level at the hot forming temperature.
  • the miniumum copper content is desirably about 2%.
  • Hot forming will generally be carried out in the temperature range 300500C and preferentially in the range 350-475C.
  • the slow diffusion rate of zirconium in aluminium allows the cast alloy to be hot worked by rolling or extrusion to a considerable degree without excessive precipitation from the alloy of the zirconium in excess of saturation (it being on the presence of excess zirconium that the capability for subsequent superplastic forming depends) it is clearly desirable to avoid excessivee pre-heating of the alloy prior to hot working and to carry out the working operations at tempera tures below those at which the precipitation of zirconium is rapid, e.g. in the range 300C to 500C. If desired the cast metal may be held for some time at temperatures in the range 300C to 400C prior to hot working without detriment and sometimes with benefit to the final superplastic forming properties.
  • the hot formed objects may be heat treated to develop maximum tensile properties, e.g. the components may be solution heat treated for 40 min at 535C, rapidly cooled and then artificially aged (precipitation heat treated) for 6 hr at C. Alternatively, though at some sacrifice in their final properties, the objects may be rapidly cooled after hot forming and then artificially aged.
  • the alloys are fusion weldable provided they have a magnesium content not materially exceeding about 0.25%.
  • the alloys may be chemically brightened and anodised or subjected to other forms of decorative anodising treatment.
  • the copper content may usefully be about 2.5%, and the combined content of iron and silicon should not exceed 0.2%.
  • the alloys may be clad, e.g. with pure aluminium, to improve their corrosion resistance.
  • the alloys may be formed into complex shapes with sharp angles by applying air pressure for a few minutes to the alloy heated to a temperature in the range 300C to 500C.
  • an alloy of the present invention is capable of being superplastically deformed and subsequently heat treated to give very attractive tensile properties.
  • By modification of the ageing cycle LII even higher tensile properties can be obtained at some sacrifice of elongation.
  • the alloy moreover has high resistance to both creep and fatigue.
  • a superplastically deformable wrought aluminumbase alloy consisting of 1. an aluminium-base alloy selected from the group consisting of (l-a) non-heat-treatable aluminium-base alloys of aluminium and one of the elements selected from the group consisting of Mg and Zn, the quantity of Mg being from 5% to 10% with zero to 0.5% Cu, and the quantity of Zn being from 1% to 15% with zero to 0.5% Mg and zero to 0.5% Cu, and
  • a superplastic aluminium-base alloy according to claim 1 containing at least one of the following incidental elements, in a total amount not exceeding 1.25

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  • 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)
  • Forging (AREA)
  • Heat Treatment Of Nonferrous Metals Or Alloys (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
US273639A 1971-07-20 1972-07-20 Aluminium base alloys Expired - Lifetime US3876474A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US05/509,406 US3984260A (en) 1971-07-20 1974-09-26 Aluminium base alloys

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB3392271A GB1387586A (en) 1971-07-20 1971-07-20 Aluminium based alloys
GB3392272 1972-06-27

Related Child Applications (1)

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US05/509,406 Division US3984260A (en) 1971-07-20 1974-09-26 Aluminium base alloys

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US (1) US3876474A (enrdf_load_stackoverflow)
JP (1) JPS5630392B2 (enrdf_load_stackoverflow)
CA (1) CA1006014A (enrdf_load_stackoverflow)
IT (1) IT962986B (enrdf_load_stackoverflow)
SE (1) SE398130B (enrdf_load_stackoverflow)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063936A (en) * 1974-01-14 1977-12-20 Alloy Trading Co., Ltd. Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack
US4130500A (en) * 1977-12-14 1978-12-19 The United States Of America As Represented By The United States Department Of Energy Lithium-aluminum-magnesium electrode composition
US4172181A (en) * 1977-05-10 1979-10-23 Furukawa Aluminum Co., Ltd. Composite material for vacuum brazing
US4571272A (en) * 1982-08-27 1986-02-18 Alcan International Limited Light metal alloys, product and method of fabrication
US4603029A (en) * 1983-12-30 1986-07-29 The Boeing Company Aluminum-lithium alloy
US4629505A (en) * 1985-04-02 1986-12-16 Aluminum Company Of America Aluminum base alloy powder metallurgy process and product
US4787943A (en) * 1987-04-30 1988-11-29 The United States Of America As Represented By The Secretary Of The Air Force Dispersion strengthened aluminum-base alloy
US4874440A (en) * 1986-03-20 1989-10-17 Aluminum Company Of America Superplastic aluminum products and alloys
US5032359A (en) * 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5055257A (en) * 1986-03-20 1991-10-08 Aluminum Company Of America Superplastic aluminum products and alloys
US5085830A (en) * 1989-03-24 1992-02-04 Comalco Aluminum Limited Process for making aluminum-lithium alloys of high toughness
US5122339A (en) * 1987-08-10 1992-06-16 Martin Marietta Corporation Aluminum-lithium welding alloys
US5133931A (en) * 1990-08-28 1992-07-28 Reynolds Metals Company Lithium aluminum alloy system
US5198045A (en) * 1991-05-14 1993-03-30 Reynolds Metals Company Low density high strength al-li alloy
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
US6056835A (en) * 1993-01-27 2000-05-02 Toyota Jidosha Kabushiki Kaisha Superplastic aluminum alloy and process for producing same
US6322646B1 (en) 1997-08-28 2001-11-27 Alcoa Inc. Method for making a superplastically-formable AL-Mg product
US20090142222A1 (en) * 2007-12-04 2009-06-04 Alcoa Inc. Aluminum-copper-lithium alloys
RU2491365C2 (ru) * 2011-08-09 2013-08-27 Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Национальный исследовательский технологический университет "МИСиС" Сверхпластичный сплав на основе алюминия

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5030984B1 (enrdf_load_stackoverflow) * 1970-01-29 1975-10-06
BE786507A (fr) * 1971-07-20 1973-01-22 British Aluminium Co Ltd Alliage superplastique
JPS5910987B2 (ja) * 1975-07-02 1984-03-13 株式会社神戸製鋼所 成形性にすぐれたアルミニウム合金およびその薄板製造方法
JPS5943538B2 (ja) * 1975-09-08 1984-10-23 株式会社神戸製鋼所 成形性にすぐれたアルミニウム合金およびその薄板製造法
JPS5294376U (enrdf_load_stackoverflow) * 1976-01-08 1977-07-14
JPS5539455A (en) * 1978-09-13 1980-03-19 Kubota Ltd Double integration type analog-digital converter
JPS5911651B2 (ja) * 1980-10-29 1984-03-16 三井アルミニウム工業株式会社 超塑性アルミニウム合金及びその製造方法
US4405832A (en) * 1981-05-29 1983-09-20 Peavey Electronics Corp. Circuit for distorting an audio signal
JPS5822363A (ja) * 1981-07-30 1983-02-09 Mitsubishi Keikinzoku Kogyo Kk 超塑性アルミニウム合金板の製造方法
JPS5836009A (ja) * 1981-08-28 1983-03-02 Hitachi Ltd 振幅制限回路
JPS5842749A (ja) * 1981-09-09 1983-03-12 Mitsubishi Alum Co Ltd 成形加工後の表面性状が良好な中強度押出用Ａｌ合金
JPS6047900B2 (ja) * 1981-11-10 1985-10-24 株式会社化成直江津 超塑性アルミニウム合金およびその製造法
JPS5928554A (ja) * 1982-08-05 1984-02-15 Mitsubishi Keikinzoku Kogyo Kk 超塑性アルミニウム合金およびその製法
JPS59159961A (ja) * 1983-02-28 1984-09-10 Mitsubishi Alum Co Ltd 超塑性Ａｌ合金
JPS60128238A (ja) * 1983-12-15 1985-07-09 Mitsubishi Chem Ind Ltd 超塑性アルミニウム合金及びその製造法
US4661172A (en) * 1984-02-29 1987-04-28 Allied Corporation Low density aluminum alloys and method
JPS6152345A (ja) * 1984-08-22 1986-03-15 Mitsubishi Alum Co Ltd 超塑性Ａｌ合金
JPS6296643A (ja) * 1985-10-24 1987-05-06 Sumitomo Light Metal Ind Ltd 超塑性アルミニウム合金
US4809336A (en) * 1987-03-23 1989-02-28 Pritchard Eric K Semiconductor amplifier with tube amplifier characteristics

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1782300A (en) * 1928-12-18 1930-11-18 Rolls Royce Aluminum alloy
US2245167A (en) * 1939-08-23 1941-06-10 Aluminum Co Of America Wrought aluminum base alloy and method of producing it
US3020154A (en) * 1958-04-24 1962-02-06 Martin Marietta Corp Aluminum alloy
US3236632A (en) * 1964-12-01 1966-02-22 Dow Chemical Co High strength aluminum alloy for pellet extrusion and product
US3666451A (en) * 1970-08-13 1972-05-30 Atomic Energy Commission Aluminum alloy

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1782300A (en) * 1928-12-18 1930-11-18 Rolls Royce Aluminum alloy
US2245167A (en) * 1939-08-23 1941-06-10 Aluminum Co Of America Wrought aluminum base alloy and method of producing it
US3020154A (en) * 1958-04-24 1962-02-06 Martin Marietta Corp Aluminum alloy
US3236632A (en) * 1964-12-01 1966-02-22 Dow Chemical Co High strength aluminum alloy for pellet extrusion and product
US3666451A (en) * 1970-08-13 1972-05-30 Atomic Energy Commission Aluminum alloy

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063936A (en) * 1974-01-14 1977-12-20 Alloy Trading Co., Ltd. Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack
US4172181A (en) * 1977-05-10 1979-10-23 Furukawa Aluminum Co., Ltd. Composite material for vacuum brazing
US4130500A (en) * 1977-12-14 1978-12-19 The United States Of America As Represented By The United States Department Of Energy Lithium-aluminum-magnesium electrode composition
US4571272A (en) * 1982-08-27 1986-02-18 Alcan International Limited Light metal alloys, product and method of fabrication
US4603029A (en) * 1983-12-30 1986-07-29 The Boeing Company Aluminum-lithium alloy
US4629505A (en) * 1985-04-02 1986-12-16 Aluminum Company Of America Aluminum base alloy powder metallurgy process and product
US4874440A (en) * 1986-03-20 1989-10-17 Aluminum Company Of America Superplastic aluminum products and alloys
US5055257A (en) * 1986-03-20 1991-10-08 Aluminum Company Of America Superplastic aluminum products and alloys
US4787943A (en) * 1987-04-30 1988-11-29 The United States Of America As Represented By The Secretary Of The Air Force Dispersion strengthened aluminum-base alloy
US5122339A (en) * 1987-08-10 1992-06-16 Martin Marietta Corporation Aluminum-lithium welding alloys
US5032359A (en) * 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5085830A (en) * 1989-03-24 1992-02-04 Comalco Aluminum Limited Process for making aluminum-lithium alloys of high toughness
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
US5133931A (en) * 1990-08-28 1992-07-28 Reynolds Metals Company Lithium aluminum alloy system
US5198045A (en) * 1991-05-14 1993-03-30 Reynolds Metals Company Low density high strength al-li alloy
US6056835A (en) * 1993-01-27 2000-05-02 Toyota Jidosha Kabushiki Kaisha Superplastic aluminum alloy and process for producing same
US6322646B1 (en) 1997-08-28 2001-11-27 Alcoa Inc. Method for making a superplastically-formable AL-Mg product
US20090142222A1 (en) * 2007-12-04 2009-06-04 Alcoa Inc. Aluminum-copper-lithium alloys
US8118950B2 (en) 2007-12-04 2012-02-21 Alcoa Inc. Aluminum-copper-lithium alloys
US9587294B2 (en) 2007-12-04 2017-03-07 Arconic Inc. Aluminum-copper-lithium alloys
RU2491365C2 (ru) * 2011-08-09 2013-08-27 Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Национальный исследовательский технологический университет "МИСиС" Сверхпластичный сплав на основе алюминия

Also Published As

Publication number Publication date
JPS4828310A (enrdf_load_stackoverflow) 1973-04-14
IT962986B (it) 1973-12-31
CA1006014A (en) 1977-03-01
JPS5630392B2 (enrdf_load_stackoverflow) 1981-07-14
SE398130B (sv) 1977-12-05

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Owner name: SUPERFORM METALS LIMITED; P.O. BOX 150, WORCESTER,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:TI (GROUPS SERVICES) LIMITED;BRITISH ALUMINIUM COMPANY PLC THE;TI GROUP PLC;REEL/FRAME:004097/0594

Effective date: 19821126