US3637441A

US3637441A - Aluminum-copper-magnesium-zinc powder metallurgy alloys

Info

Publication number: US3637441A
Application number: US18781A
Authority: US
Inventors: John P Lyle Jr; Raymond J Towner
Original assignee: Aluminum Company of America
Current assignee: Howmet Aerospace Inc
Priority date: 1968-04-08
Filing date: 1970-03-02
Publication date: 1972-01-25
Anticipated expiration: 1989-01-25

Abstract

Aluminum base powder metallurgy alloy article having an improved combination of high-transverse yield strength and high-stress corrosion cracking resistance. The alloy contains the basic precipitation hardening elements zinc, magnesium and copper plus dispersion strengthening elements iron and nickel. It may additionally contain chromium and/or manganese. The alloy is prepared by atomization of a melt of the elements, hot-working, solution heat treating, quenching and artificial aging. Components of the alloy in percent by weight are, in addition to the aluminum, from at least 6.5 to 13 zinc, 1.75 to 6 magnesium, 0.25 to 2.5 copper, 0.75 to 4.25 iron and 0.75 to 6 nickel, up to 3 manganese and up to 0.75 chromium. The iron to nickel ratio is from 0.2:1 to 2.0:1.

Description

73 w. i M 11 W i.

we 5 es ie 1. [151 3,37A1 Lyle, Jr. et a1. [4 Jan. 25, 1972 54] ALUMINUM-(IOPPER-MAGNESHJM- 3,198,676 8/1965 Sprowls 148/325 ZINC PGWDER METALLURGY 3,265,493 8/ 1966 Foerster ALLOYS 3,291,654 12/1966 Foerster 3,307,978 3/1967 Foerster ..148/l2.7 ['72] Inventors: John P. Lyle, Jr., New Kensington, Pa.;

Raymond Town, Lima Ohio Primary Examiner-L. Dewayne Rutledge Assistant ExaminerW. W. Stallard [73] Assigneez Aluminum Company of America, Pitt- Hatcher sburgh, PA

22 Filed: Mar. 2, 1970 [57] ABSTRACT [211 App]. NOJ 18,781 Aluminum base powder metallurgy alloy article having an improved combmatlon of high-transverse yield strength and Related [1.8, Application D m high-stress corrosion cracking resistance. The alloy contains the basic precipitation hardening elements zinc, magnesium [62] Dmslon of 719,752 1968 and copper plus dispersion strengihening elements iron and 3,544,394' nickel. It may additionally contain chromium and/or manganese. The alloy is prepared by atomization of a melt of the [52] US. Cl ..l48/32.5 demerits hobworkingy solution heat treating quenching and [51] Int. Cl. ..C22c 21/00, C22f l/O4 artificial aging cnmponems of the alloy i percent b weight [58] Fleld of Search ..l48/32.5, 12.7; 75/141, 142, are in addition 0 the aluminum, from at least 5 to 13 zinc, 75/144 05 B 1.75 to 6 magnesium, 0.25 to 2.5 copper, 0.75 to 4.25 iron and 0.75 to 6 nickel, up to 3 manganese and up to 0.75 chromium. [56] References cued The iron to nickel ratio is from 0.2:] to 20:].

UNITED STATES PATENTS 5 Clams, No Drawings 0 5/ ALUMINUM-COPPER-MAGNESIUM-ZINC POWDER METALLURGY ALLOYS This application is a division of parent application Ser. No. 719,752, filed Apr. 8, 1968 now U.S. Pat. No. 3,544,394.

BACKGROUND OF THE INVENTION This invention relates to aluminum-copper-magnesium-zinc alloys prepared by powder metallurgy techniques. More particularly, it pertains to improving tensile and stress corrosion properties of articles prepared from aluminum-copper-magnesium-zinc alloys by the addition of certain dispersion strengthening elements to the melt from which the alloys are prepared by atomization. By powder metallurgy techniques we mean those processes in which the molten alloy is atomized to make fine powder, the powders are compacted, and the compact is fabricated into the desired form by hot working.

One way in which to improve tensile properties, that is, in general, to strengthen aluminum base alloys is by precipitation hardening. This occurs when a supersaturated solid solution precipitates its excess solute. The process is favored in alloy systems with appreciably greater solubility for the solute at elevated temperatures than at lower or ambient temperatures. The precipitate effects strengthening of the structure by setting up coherency strains in the matrix by the precipitated particles. Zinc, magnesium and copper are well known as elements which contribute substantially to precipitation hardening. It is also known that strengthening may be improved by adding to the alloy system one or more elements which form compounds having low solubilities and low diffusibilities in the solid state at elevated temperatures to impart a strengthening effect which lasts even after extensive heat treatment. This type of reaction is commonly referred to as dispersion strengthening or interference hardening.

Copper, magnesium and zinc have been disclosed to be useful precipitation hardening elements for use in aluminum base alloys. Individual dispersion strengthening elements which have been suggested for use in improving the properties of aluminum base alloys include manganese, iron, nickel, chromium, titanium, vanadium, zirconium, cobalt, molybdenum and tungsten. Thus far it has not proved too difficult to add precipitation hardening elements because of their characteristic high-liquid solubilities, high-solid solubilities at high temperatures, and high-solid diffusibilities at high temperatures. However, for addition of dispersion strengthening elements, standard ingot casting procedures have been of limited use when it was desired to modify the alloy composition by addition of considerable amounts of these elements. This has been due to the fact that dispersion strengthening elements are characterized by low-liquid solubilities near the solidification temperatures and low-solid solubilities and low-solid diffusibilities at elevated temperatures. It has been proposed to combine the strengthening characteristics of both precipitation hardening and dispersion strengthening elements by using atomization of alloys from the melt to permit use of higher concentrations of elements than is possible in ingot metallurgy where the casting solidification rates are slow relative to atomizing solidification rates. Use of atomized alloy powders has helped improve the strength properties of aluminum base alloys by resulting in a structure which is several orders of magnitude finer than standard ingot metallurgy alloy structures.

While considerable improvement in strength has been possible by the aforementioned combination of dispersion strengthening and precipitation hardening, particularly with the improved results obtained by atomization of a melt of the alloy containing the dispersion strengthening elements, improvements in stress corrosion cracking resistance, one of the main features desired for lightweight rocket motor and aircraft parts, have thus far been rather limited, probably partly because of the fact that, in increasing stress corrosion resistance by standard age hardening procedures, the strength properties of the alloys have been somewhat impaired, making them not entirely satisfactory for some high-stress applications.

OUTLINE OF THE INVENTION Accordingly, it is an object of this invention to provide a novel hot-worked powder metallurgy alloy article which combines a transverse yield strength which is equal to or superior to that of presently known aluminum base ingot metallurgy alloy articles containing the precipitation hardening elements copper, magnesium and zinc with a stress corrosion cracking resistance which is greater than that of such known ingot metallurgy alloy articles. Another object is to provide a method for production of novel powder metallurgy alloys which have a transverse yield strength comparable to that of known aluminum-copper-magnesium-zinc ingot metallurgy alloys plus a higher resistance to stress corrosion cracking. These and other objects of the invention will be apparent from the description and claims which follow.

in accordance with this invention a hot-worked powder metallurgy alloy article is prepared in which the alloy contains in percent by weight from at least 65-13 zinc, l.756 magnesium, 0.25-2.5 copper, 0.75-4.25 iron and 0.75-6 nickel. The alloy may additionally contain up to 3 manganese, (preferably 0.25-2) and up to 0.75 chromium. It may also contain up to 1.5 percent by weight A1 0, and up to a total of about 1 percent by weight of other elements such as titanium, silicon, vanadium or the like, generally as impurities. The Fe:Ni ratio should be from 0.2:] to 2.0: 1.

One feature of the alloy article of this invention is its combination of high resistance to stress corrosion cracking with high-transverse yield strength as great as or superior to that of prior art conventional ingot metallurgy aluminum-zinccopper-magnesium alloy articles which contain less zinc and no combination of iron and nickel. By high-transverse yield strength we mean at least about 60-67 k.s.i. (thousands of pounds per square inch), which is the transverse yield strength of conventional 2-inch diameter ingot metallurgy extruded rods of aiuminum-zinc-copper-magnesium alloys containing less than 6.5 percent by weight zinc and not having a combination of iron and nickel. By high resistance to stress corrosion cracking we mean an absence of cracking or breaking apart of a solution heat treated and artificially aged 2-inch diameter extruded rod after at least 84 days under a stress in a transverse direction of 50 percent of its transverse yield strength in the standard stress corrosion test of alternate immersion in a 3.5 percent by weight sodium chloride solution. [ASTM ST? 425 (1967), pp. 8 and 188]. The aforementioned conventional rods fail, that is, crack or break apart, in this test in less than 84 days.

To obtain this combination of high-stress corrosion resistance and high-transverse yield strength, the aging is preferably at a temperature of from about 225 to 350 F. for from about 3 to about hours. According to another embodiment, a two-stage aging procedure may be used in which the first stage is at from about 225 to about 275 F. for from about 6 to about 96 hours and the second at from about 315 to about 350 F. for from about 3 to about 40 hours. The solution heat treatment is preferably at a temperature of from about 750 to l,000 F. The solution heat treatment and aging procedures described in Sprowls et al. US. Pat. No. 3,198,676 may be used according to this invention.

One method for preparation of the alloy articles of our invention is as follows:

I. melting and alloying,

2. atomizing, collecting and screening (for example, to l00 mesh powder with a Sharples Micromerograph mass median diameter (MMD) of 5-60 microns),

3. compacting to less than 100 percent density e.g., in a tapered or split die,

4. degassing by heating in a flowing nonoxidizing atmosphere,

5. hot compacting to substantially 100 percent density and then 6. hot working.

The hot working may be by conventional extnrsion, forging, impact extrusion or rolling.

United States Patent 1151 3,637,444

Bonyata et al. [4 1 Jan. 25, 1972 [54] PROCESS OF MAKING DETERRENT. ;,g9(8),'8/8$0 951321 Woodbridge ..149/9 0 9 71 35 Wagner ....149/10 COATED AND GRAPHITE GLAZED 2,113,418 4/1938 Woodbridge ..l49/ 10 SMOKELESS PQWDER 2,152,509 3/1939 Troxler ..149/10 [72] Inventors: John O. Bonyata, Mountain Lakes; Lynn 2,179,312 11/1939 Whig/10 Rohrbaugh, Lake Hopatcong, both of 2,346,125 4/1944 GoOdyeal'.... ...l49/1O Ni 2,440,267 4/1948 Hale I 2,407,967 9/1946 Thomson ..l49/9 Asslgnw Herculeslncorpormd,Wflmmgwn, 2,865,728 12/1958 Cook ....149/10 [22] Filed, AP 141969 3,506,505 4 1970 Herzog et a1 ..149/9 [21] Appl.No.: 816,023 Primary Examiner--Car1D.Quarforth Assistant ExaminerStephen .I. Lechert, Jr. 52 us. c1 ..149/10,149 9,149/11,

511 1111.01. ..C06b 19/02 [57] ABSTRACT Fidd Search An improved process for manufacture of deterrent-coated 3 and graphite-glazed smokeless powder is provided with deter- 1 rent coating and graphite glazing being done in an aqueous [56] References Cited slurry at elevated temperatures.

UNITED STATES PATENTS 20 Claims, No Drawings 1,393,621} 10 1921 Henning 149/9

Claims

2. The article of claim 1 wherein the aged condition results from heating at from about 225* to about 350* F. for from about 3 hours to about 100 hours.
3. The article of claim 1 wherein the aged condition results from heating first at from about 225* to about 275* F. for from about 6 to about 96 hours and then heating at from about 315* to about 350* F. for from about 3 to about 40 hours.
4. The article of claim 1 in which the Fe:Ni ratio of the alloy is from 0.2:1 to 2.0:1.
5. The article of claim 1 wherein the alloy also contains up to about 1.5 percent by weight Al2O3.