EP0079749A2 - Alliage à base d'aluminium renforcé par dispersion et obtenu par le procédé d'alliage mécanique - Google Patents

Alliage à base d'aluminium renforcé par dispersion et obtenu par le procédé d'alliage mécanique Download PDF

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Publication number
EP0079749A2
EP0079749A2 EP82305956A EP82305956A EP0079749A2 EP 0079749 A2 EP0079749 A2 EP 0079749A2 EP 82305956 A EP82305956 A EP 82305956A EP 82305956 A EP82305956 A EP 82305956A EP 0079749 A2 EP0079749 A2 EP 0079749A2
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Prior art keywords
alloy
aluminium
alloys
content
range
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EP82305956A
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German (de)
English (en)
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EP0079749A3 (fr
Inventor
Stephen James Donachie
Donald Leo Erich
John Herbert Weber
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MPD Technology Corp
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MPD Technology Corp
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
    • C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
    • C22C32/0036—Matrix based on Al, Mg, Be or alloys thereof

Definitions

  • Tensile yield strength is the primary design factor for determining the stress loading for a structural member. Normally, maximum anticipated flight loads for a member are specified as a percentage such as 40% or 60% of the YS. Thus the greater the YS, the smaller the cross sectional area of the structural member may be.
  • Tensile ductility is another important material parameter. It is the practice of the aircraft designers to specify an acceptable elongation, commonly 5% minimum. For conventional aluminium alloys the tensile ductility decreases as the tensile yield strength increases and this lack of ductility may limit the design potential in high strength areas. Notched fatigue resistance is the alloy resistance to cyclic loading in the presence of notches or cracks. Discontinuities in aircraft structures (e.g.
  • SCC stress corrosion cracking resistance
  • Most aluminium alloys are known to fail in tensile loading at stresses well below their normal YS in the presence of a corroding medium. (Normal operating conditions are corrosive to aircraft materials). Only some aluminium alloys with very low YS do not show this phenomenon. The use of an alloy with high YS may thus be prohibited because that alloy might fail in tension at a much lower stress in actual service. It can be seen from the foregoing that advanced Al alloys for the aerospace industry must exhibit a broad range of suitable properties to be successfully applied.
  • UK Patent No. 1 265 343 and UK Patent No. 1 390 857 discloses a process for preparing mechanically-alloyed dispersion-strengthened aluminium-based powders for consolidation to billet having improved combinations of strength and ductility.
  • the materials made by mechanically-alloying are characterised by a fine grain structure which is stabilised by a dispersion of oxide and carbide particles.
  • European Patent Application No. 79 302 232.8 discloses a dispersion-strengthened mechanically-alloyed aluminium-base alloy system having high strength and good corrosion resistance and a method for controlling and/or optimising strength and workability by variations in the thermomechanical processing.
  • the aluminium-base alloys contain up to 7% magnesium, up to 2.5% carbon and 0.3 to 4% oxygen.
  • additives which are disclosed for additional strength in the Al-Mg system are Li, Cr, Si, Zn, Ni, Ti, Zr, Co, Cu and Mn.
  • a dispersion-strengthened mechanically-alloyed aluminium-based alloy having improved resistance to stress corrosion cracking comprises 0.5 to 6% copper, 0.5 to 3% magnesium, 0.1% to 2.5% carbon, an effective amount up to 3% oxygen, up to 1% manganese, up to 0.5% iron, balance apart from impurities and incidental elements being aluminium, and containing oxide and carbide dispersoids in an amount of 1% to 10% by volume. All percentages herein are by weight unless otherwise specifically stated.
  • Alloys of the invention have excellent resistance to stress corrosion cracking and exhibit in the consolidated, forged and heat treated condition a fracture toughness in the transverse direction of at least 33 MN/m 3/2 when the tensile yield strength in the transverse direction is about 551 MN/m 2 and a fracture toughness in the transverse direction of at least 49.5 MN/m 3/2 when the tensile yield strength in the transverse direction is about 448 MN/m 2, and has an elongation in short transverse direction of at least 5% and normally more than 10%.
  • the stress corrosion cracking resistance has been found to be better than that of the conventional aluminium alloy 2024 in the T4 temper by more than 50%, and in some instances by more than 500%.
  • the alloy contains 1 to 10% by volume, preferably 2 to 7%, of finely divided,uniformly distributed dispersoid materials consisting of oxides and carbides, and may include other refractory dispersoids such as nitrides and borides.
  • the alloy powder is made by the mechanically alloying technique in the presence of a process control agent and the powder is hot consolidated to a substantially dense body, worked at an elevated temperature, such as 200 to 550°C, and subjected to a solution treatment for a period of 1/4 to 10 hours at a temperature of 350 to 550°C, preferably 480 to 510°C.
  • a process control agent such as 200 to 550°C
  • a solution treatment for a period of 1/4 to 10 hours at a temperature of 350 to 550°C, preferably 480 to 510°C.
  • Preferred alloys of the invention contain 2 to 5% copper, 0.5 to 2.5% magnesium, oxygen in the range 0 .4 to 1% and carbon 0.6 to 1.25%. More preferably the copper range is 3 to 4.5% and magnesium 1 to 2.5%, or even 1.25 to 2%. Preferably the manganese content does not exceed 0.4%, or more preferably 0.2%, and the iron content is preferably below 0.2%.
  • the alloy may also contain other minor amounts of other elements normally present as trace elements in aluminium.
  • One embodiment of the invention consisting essentially of 4% copper, 1.5% magnesium, 0 .8% oxygen, 1.1% carbon and by volume 5.5 to 7% of dispersed oxide and carbide refractory phase, exhibits in the forged, heat-treated state a transverse yield strength of at least 551 MN/m 2 , a fracture toughness of at least 34.6 MN/ m 3/2 normally 37.4 and elongation in the short transverse direction of 10% or more.
  • Alloys of the invention are produced and processed into consolidated form by the processes disclosed in UK patent 1 390 857 and European Patent application 79 302 232.8. However the present alloys receive an additional solution treatment in order to strengthen them and may further benefit from an age hardening treatment.
  • Alloy A was purchased as a cast billet of 15.2 cm x 30.5 cm, and was prepared for forging by extrusion to 4.45 cm diameter round bar at a temperature of about 316°C and ram speed of 0.25 cm/sec. The extrusion was cut into 63.5 cm lengths, and each length hot upset at one end to a length of 48.3 cm using a forging temperature of 371°C. The upset forging stock was then reheated to about 316°C and forged in a two step combined die process to the longeron end tie configuration shown as (a) in Figure 1.
  • Figure 1 shows schematically the various test specimen orientations which are considered.
  • the forging consists of web b, and flange c; tensile specimens d, and fatigue specimens e, are shown together with fracture toughness specimen f, stress corrosion cracking specimen g and fatigue crack propogation specimen h.
  • Alloys B and C were prepared by mechanically alloying in a 378.5 litre attritor.at a 17:1 ball-to-powder weight ratio (B/P).
  • the processing time was approximately 16 hours for Alloy B and approximately 14 hours for Alloy C, at approximately 87 rpm with a ball charge of 0.95- cm diameter, 52100 steel balls.
  • the process control agent (PCA) was about 1.5% stearic acid, added incrementally throughout the run.
  • the dynamic process atmosphere was nitrogen.
  • the powder batches were made from elemental powders to produce compositions of Alloys B and C of Table I. The powders were heated at about 427°C under vacuum to remove the volatile elements of the stearic acid.
  • the powders were then loaded into cans, evacuated and maintained for about 6 hours at about 454°C and 482°C under vacuum for Alloys B and C, respectively. Consolidation was effected . at about 399°C in an extrusion press at a pressure of about 345 MN/m 2 . After removal of the cans, the alloys were extruded to 4.4 cm diameter round bars at approximately 260°C with a ram speed of 0.51 cm/min. The extrusion was cut into 63.5 cm lengths and forged by the same practice and temperature as used for Alloy A. The forged products were heat treated under the conditions shown in Table I.
  • Alloy A i.e. the 7075 alloy
  • Alloys B and C were prepared in the F(as-forged) and T4 (naturally aged) tempers, respectively.
  • Alloys B and C The fracture toughness of Alloys B and C was - determined using compact tension specimens taken from the flange of the forgings and tested in the TL orientation. A value for Alloy A reported by an independent source was used to compare toughness values of the mechanically alloyed materials with the Alloy A. Typical test results for Alloys B and C are given in Table III. These results show that Alloy B has slightly lower toughness than the value reported for the Alloy A forging. However, the average fracture toughness value exhibited by Alloy C shows an improvement over both the average values for Alloy B and the value reported for the Alloy A forging. In fact, the combination of toughness and strength for Alloy C forgings is believed to exceed that reported for any other aluminium alloy.
  • Figure 2 compares fracture toughness vs. yield strength for various aluminium alloys in the forged condition, and gives a further comparison with a 2000 series alloy designated Alloy X, the information for which was obtained from Figure 1 of U.S. Patent No. 3,826,688. Projection of the Alloy C-T4 data into the Alloy X line, clearly reveals the superiority of the alloy of this invention over that of Alloy X. According to Figure 2, if Alloy X were brought to the same strength as Alloy C-T4, the toughness of Alloy X would be ohly about 20.9 MN/m 3/2 compared to the value of about 37 . 4 MN/m3/2 exhibited by Alloy C-T4.
  • the fatigue crack growth behaviour of the forged alloys of Table I was determined from compact tension specimens in the LT orientation. Tests were conducted in dessicated air at a frequency of 20 Hz and an R ratio of 0.1. Linear regression analysis was used to reduce the data, as only steady state (stage II) crack growth was observed. It was found, as shown in Figure 3, that the slowest rate of fatigue crack growth (da/dn) is exhibited by Alloy C with the rate of crack growth increasing in order with Alloy A followed by Alloy B.
  • alloy C has an improved combination of properties over alloy B, both of these having more attractive properties than Alloy A.
  • the chemical compositions of the four alloys are given in Table VII.
  • the oxygen and carbon levels are similar for the four heats. Assuming A1 2 0 3 and Al 4 C 3 are the dispersed species, the volume % dispersoid ranges between 6.3 and 6.6%.
  • the mechanically alloyed powder was placed in mild steel cans which were subsequently degassed. Vacuum degassing was performed in three stages: room temperature evacuation followed by heating to 315°C for 4 hours under vacuum and finally evacuation for 2 hours. The steel cans were then sealed. Compaction was performed in the extrusion press against a blank die after a soak of 2 hours at 427°C. The steel cans were then stripped from the aluminium billets producing a 7.6 cm dia. billet. Extrusion was performed at 343°C in a 8.9 cm dia. liner after 2.5 h. soak. A 1.6 cm diameter extruded bar was produced using a 20% throttle setting. Extrusion ram speeds were typically 1.3 to 1.8 cm per sec. ,
  • the four alloys were heat treated using three sequence which can be described using conventional aluminium alloy temper designations: The heat treatment was not optimized for these studies.
  • Tensile properties were determined at room temperature, 121°C, 204°C and-316°C.
  • the effect of heat treatment was essentially the same for all of the alloys of the invention.
  • the F temper exhibits the lowest strength and lowest elongation.
  • the T4 temper shows an improvement in strength and elongation and the T6 temper exhibits the highest strength and ductility.
  • Additions of magnesium to the Al-4Cu composition result in quite significant property changes. Strength is significantly increased in all tempers as magnesium content increases from 0 to 1.5%, while Mg additions .have only minimal effect on ductility in the T4 and T6 tempers. The addition of 0.5% Mn to the Al-4Cu-lMg alloy provides little benefit to room temperature properties except in the F temper.
  • Elevated temperature tensile properties for the T4 condition are listed in Table IX..
  • Fatigue crack propagation data for other aluminium based alloys including powder metallurgically produced alloys X7090 and X7091 has been tabulated from reported data and is compared with experimentally obtained results on the mechanically alloyed materials having nominal compositions Al4Cu - 1.5 Mg and Al-4Mg in Table XII.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Parts Printed On Printed Circuit Boards (AREA)
  • Insulated Metal Substrates For Printed Circuits (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
EP82305956A 1981-11-12 1982-11-09 Alliage à base d'aluminium renforcé par dispersion et obtenu par le procédé d'alliage mécanique Withdrawn EP0079749A3 (fr)

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US32047981A 1981-11-12 1981-11-12
US320479 1981-11-12

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EP0079749A3 EP0079749A3 (fr) 1984-04-25

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0194700A2 (fr) * 1985-03-15 1986-09-17 Inco Alloys International, Inc. Alliages d'aluminium
GB2267912A (en) * 1992-06-15 1993-12-22 Secr Defence Metal matrix for composite materials
WO2011023059A1 (fr) * 2009-08-27 2011-03-03 贵州华科铝材料工程技术研究有限公司 Matériau en alliage multiélément d'aluminium résistant à la chaleur, doté d'une résistance mécanique élevée, et procédé d'élaboration correspondant
CN102021418B (zh) * 2009-09-18 2012-10-03 贵州华科铝材料工程技术研究有限公司 以C变质的Sc-Cr-RE高强耐热铝合金材料及其制备方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6365046A (ja) * 1986-09-04 1988-03-23 Showa Alum Corp 粒子分散形Ａｌ基複合材の製造方法
JPS6365045A (ja) * 1986-09-04 1988-03-23 Showa Alum Corp 粒子分散形Ａｌ基複合材
JPS6376904A (ja) * 1986-09-19 1988-04-07 Showa Alum Corp コネクテイングロツド
JPS63227735A (ja) * 1987-03-17 1988-09-22 Showa Alum Corp 耐摩耗性に優れた複合材料及びその製造方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2038523A5 (en) * 1969-03-18 1971-01-08 Kovrizhnykh Vitaly Heat-resistant, aluminium-base powder alloy
DE2253282B1 (de) * 1972-10-31 1973-08-16 Mahle Gmbh, 7000 Stuttgart Warmfeste Aluminium Sinterlegierung
DE2431646A1 (de) * 1974-07-02 1976-01-22 Mahle Gmbh Warmfeste aluminium-sinterlegierung

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2038523A5 (en) * 1969-03-18 1971-01-08 Kovrizhnykh Vitaly Heat-resistant, aluminium-base powder alloy
DE2253282B1 (de) * 1972-10-31 1973-08-16 Mahle Gmbh, 7000 Stuttgart Warmfeste Aluminium Sinterlegierung
DE2431646A1 (de) * 1974-07-02 1976-01-22 Mahle Gmbh Warmfeste aluminium-sinterlegierung

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0194700A2 (fr) * 1985-03-15 1986-09-17 Inco Alloys International, Inc. Alliages d'aluminium
EP0194700A3 (fr) * 1985-03-15 1988-01-07 Inco Alloys International, Inc. Alliages d'aluminium
GB2267912A (en) * 1992-06-15 1993-12-22 Secr Defence Metal matrix for composite materials
WO2011023059A1 (fr) * 2009-08-27 2011-03-03 贵州华科铝材料工程技术研究有限公司 Matériau en alliage multiélément d'aluminium résistant à la chaleur, doté d'une résistance mécanique élevée, et procédé d'élaboration correspondant
US8728256B2 (en) 2009-08-27 2014-05-20 Guizhou Hua-Ke Aluminum-Materials Engineering Research Co., Ltd. Multi-element heat-resistant aluminum alloy material with high strength and preparation method thereof
CN102021418B (zh) * 2009-09-18 2012-10-03 贵州华科铝材料工程技术研究有限公司 以C变质的Sc-Cr-RE高强耐热铝合金材料及其制备方法

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JPS58136738A (ja) 1983-08-13
EP0079749A3 (fr) 1984-04-25

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