U.S. patent number 3,791,880 [Application Number 05/267,973] was granted by the patent office on 1974-02-12 for tear resistant sheet and plate and method for producing.
This patent grant is currently assigned to Aluminum Company of America. Invention is credited to Harold Y. Hunsicker, James T. Staley.
United States Patent |
3,791,880 |
Hunsicker , et al. |
February 12, 1974 |
TEAR RESISTANT SHEET AND PLATE AND METHOD FOR PRODUCING
Abstract
An aluminum base alloy of the
aluminum-zinc-magnesium-copper-chromium type with specially
controlled composition limits is provided as a sheet or plate type
product having the high strength and good resistance to stress
corrosion cracking normally associated with this type of alloy but
also having exceptional resistance to tearing. Certain prescribed
fabrication procedures including thermal treatments are preferably
followed in producing the improved product.
Inventors: |
Hunsicker; Harold Y. (Lower
Burrell, PA), Staley; James T. (Lower Burrell, PA) |
Assignee: |
Aluminum Company of America
(Pittsburgh, PA)
|
Family
ID: |
23020913 |
Appl.
No.: |
05/267,973 |
Filed: |
June 30, 1972 |
Related U.S. Patent Documents
|
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
Issue Date |
|
|
58337 |
Jul 27, 1970 |
|
|
|
|
Current U.S.
Class: |
428/553; 148/417;
148/535; 148/694; 148/701; 428/636; 428/926 |
Current CPC
Class: |
C22F
1/053 (20130101); C22C 21/10 (20130101); Y10T
428/12639 (20150115); Y10T 428/12063 (20150115); Y10S
428/926 (20130101) |
Current International
Class: |
C22C
21/10 (20060101); C22F 1/053 (20060101); C22f
001/04 () |
Field of
Search: |
;148/11.5A,12.7,32,32.5,34 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Stallard; W. W.
Attorney, Agent or Firm: Lippert; Carl R.
Parent Case Text
This is a continuation of application Ser. No. 58,337, filed July
27, 1970, now abandoned.
Claims
What is claimed is:
1. A method of producing an aluminum base alloy sheet or plate
product having high strength and high toughness and resistance to
crack propagation comprising:
1. providing a body of aluminum base alloy consisting essentially
of 5.2 to 6.2% Zn, 1.9 to 2.5% Mg, 1.2 to 1.9% Cu, 0.18 to 0.25%
Cr, the balance being aluminum and not more than the following
amounts of impurities: 0.12% Fe, 0.10% Si, 0.06% Mn, and 0.06%
Ti,
2. homogenizing said body at an elevated temperature not exceeding
its eutectic temperature of about 890.degree.F for a sufficient
period of time to provide a homogeneous distribution of the readily
soluble alloy elements,
3. further heating said body at a rate not exceeding 150.degree.F
per hour to a temperature of at least 940.degree.F for a period of
at least 6 hours,
4. hot rolling said body to reduce its thickness and thereafter
further rolling said body to produce said product, said rolling
operations imparting to said product strain hardening effects
equivalent to a cold rolling reduction of at least 25% in
thickness.
said product, when solution heat treated, quenched and artificially
aged, exhibiting improved toughness together with high
strength.
2. The method according to claim 1 wherein said product is
artificially aged at a temperature of from 200.degree.to
255.degree.F for 10 to 180 hours.
3. The method according to claim 1 wherein said product is
artificially aged by heating to a temperature of 200.degree. to
255.degree.F for 2 to 100 hours and thereafter heating to
300.degree. to 335.degree.F for 2 to 12 hours.
4. The method according to claim 1 wherein said product is
artificially aged by heating to a temperature of 200.degree. to
255.degree.F for 2 to 100 hours and thereafter heating to
315.degree. to 350.degree.F for 6 to 24 hours.
5. The method according to claim 1 wherein, referring to said step
(4), the said product is imparted with the equivalent of a cold
reduction of at least 45%.
6. The method according to claim 1 wherein, referring to said step
(4), the body is cold rolled to a cold reduction of at least 25% in
thickness to produce said product.
7. The method according to claim 1 wherein, referring to said step
(3), the body, after homogenization, is heated to a temperature
between 950.degree. and 1000.degree.F.
8. The method according to claim 1 wherein the product is solution
heat treated at a temperature of at least 940.degree.F.
9. The method according to claim 1 wherein the product is solution
heat treated at a temperature of from 950.degree. to
1000.degree.F.
10. The method according to claim 6 wherein said product ranges in
thickness from 0.020 to 0.250 inches.
11. The method according to claim 1 wherein the further heating of
said step 3 is performed subsequent to a hot rolling operation.
12. A method of producing an aluminum base alloy sheet or plate
product having high strength and high toughness and resistance to
crack propagation comprising:
1. providing a body of aluminum base alloy consisting essentially
of 5.2 to 6.2% Zn, 1.9 to 2.5% Mg, 1.2 to 1.9% Cu, 0.18 to 0.25%
Cr, the balance being aluminum and not more than the following
amounts of impurities: 0.12% Fe, 0.10% Si, 0.06% Mn, and 0.06%
Ti,
2. producing said sheet or plate product from said body including:
(a) rolling operations which impart to said product strain
hardening effects equivalent to a cold rolling reduction of at
least 25% in thickness and (b) a thermal exposure to a temperature
of at least 940.degree.F sufficient to provide in said product E
phase particles having a median size of at least 1400 A.
13. An improved aluminum base alloy sheet or plate product composed
of an alloy consisting essentially of 5.2 to 6.2% Zn, 1.9 to 2.5%
Mg, 1.2 to 1.9% Cu, 0.18 to 0.25% Cr, the balance being aluminum
and not more than the following amounts of impurities: 0.12% Fe,
0.10% Si, 0.06% Mn and 0.06% Ti, said product having a fine grain
structure, a median particle size of 1400 A or larger for the E
phase precipitate and low volume fractions of less than 0.45%
iron-bearing phase and less than 0.25% silicon-bearing phase, said
product, when solution heat treated, quenched and artificially
aged, exhibiting a minimum K.sub.c of 100 to 75 ksi .sqroot. in. at
yield strength levels of 60 to 75 ksi.
14. The improved product according to claim 13 which is clad on at
least one side thereof with a layer of an aluminum base alloy which
is anodic thereto.
15. An improved aluminum base alloy sheet or plate product composed
of an alloy consisting essentially of 5.2 to 6.2% Zn, 1.9 to 2.5%
Mg, 1.2 to 1.9% Cu, 0.18 to 0.25% Cr, the balance being aluminum
and not more than the following amounts of impurities: 0.12% Fe,
0.10% Si, 0.06% Mn and 0.06% Ti, said product having a median
particle size of 1400 A or larger for the E phase precipitate and
low volume fractions of less than 0.45% iron-bearing phase and less
than 0.25% silicon-bearing phase, said product, when solution heat
treated, quenched and artificially aged, exhibiting high toughness
at high yield strength levels.
16. A method of producing an aluminum base alloy sheet or plate
product having high strength and high toughness and resistance to
crack propagation comprising:
1. providing a body of aluminum base alloy consisting essentially
of 5.2 to 6.2% Zn, 1.9 to 2.5% Mg, 1.2 to 1.9% Cu, 0.18 to 0.25%
Cr, the balance being aluminum and not more than the following
amounts of impurities: 0.12% Fe, 0.10% Si, 0.06% Mn, and 0.06%
Ti,
2. producing said sheet or plate product from said body and
including a thermal exposure to a temperature of at least
940.degree.F sufficient to provide in said product E phase
particles having a median size of at least 1400 A.
17. In a method of producing an aluminum base alloy rolled sheet or
plate product having high strength and high toughness and
resistance to crack propagation the improvement comprising:
1. providing a body of aluminum base alloy consisting essentially
of 5.2 to 6.2% Zn, 1.9 to 2.5% Mg, 1.2 to 1.9% Cu, 0.18 to 0.25%
Cr, the balance being aluminum and not more than the following
amounts of impurities: 0.12% Fe, 0.10% Si, 0.06% Mn, and 0.06%
Ti,
2. homogenizing said body at an elevated temperature not exceeding
its eutectic temperature of about 890.degree.F for a sufficient
period of time to provide a homogeneous distribution of the readily
soluble alloy elements,
3. heating said body to a temperature of at least 940.degree.F for
a period of at least 6 hours,
said product, when solution heat treated, quenched and artificially
aged, exhibiting improved toughness together with high
strength.
18. The method according to claim 17 wherein in said step (3) said
further heating to at least 940.degree.F is at a rate not exceeding
150.degree.F per hour.
19. The method according to claim 17 wherein rolling procedures are
employed which impart to the rolling stock strain hardening effects
equivalent to a cold reduction of at least 25%.
20. The method according to claim 17 wherein the further heating of
said step (3) is performed subsequent to a hot rolling operation.
Description
This invention relates to the production of improved sheet
including the thermal treatment thereof and to the new sheet
product.
BACKGROUND OF THE INVENTION
Aluminum alloys containing 3.5 to 8% zinc, 1.5 to 4% magnesium,
0.75 to 2.5% copper are known for their high strength to weight
ratio which renders them highly suited for use in applications such
as structural components for aircraft. Alloy 7075 is an example of
this type alloy and has achieved widespread use in aircraft because
of its high strength and other desirable properties. Alloy 7075
contains 5.1 to 6.1% zinc, 2.1 to 2.9% magnesium, 1.2 to 2% copper,
0.18 to 0.40% chromium, the balance being aluminum and, as
impurities, up to 0.7% iron, 0.5% silicon, 0.3% manganese and 0.2%
titanium. In sheet gages, 7075 develops typical tensile and yield
strength levels of, respectively, 83 ksi and 73 ksi in the high
strength, or T6, temper in the unclad condition. Also, both bare
and clad 7075-T6 sheet are resistant to stress corrosion cracking.
For certain fracture-critical applications such as wing or
pressurized fuselage skin, however, the aircraft industry is
desirous of improving the tear resistance and toughness of this
alloy. The tear resistance of 7075 type sheet is improved by the
application of a two-step aging treatment as described in U.S. Pat.
No. 3,198,676, but at a 15% loss in strength, although the extent
of the increase in tear resistance falls short of current
needs.
Other aluminum base alloys have better tear resistance than 7075,
but they have lower strength. For example, alloy 2024-T3 (nominal
4.5% copper, 0.6% manganese and 1.5% magnesium) is used in aircraft
despite its relatively low strength of 65 tensile and 45 ksi yield
because of its very good tear resistance. The aircraft designers,
however, need a material having both high strength and high tear
resistance although, to date, this has been quite elusive on a
commercially repeatable scale.
DESCRIPTION
In practicing the invention high strength and tear resistance
properties are achieved along with high resistance to stress
corrosion cracking by carefully controlling the composition and the
fabrication of sheet products of an alloy similar to the 7075 type
described. The composition in accordance with the invention is an
aluminum alloy consisting essentially of, by weight, 5.2 to 6.2%
zinc, 1.9 to 2.5% magnesium, 1.2 to 1.9% copper, 0.18 to 0.25%
chromium, the balance being aluminum and incidental elements and
impurities. It is important that impurities be limited such that
the following maxima apply: Fe 0.12%, Si 0.10%, Mn 0.06%, Ti 0.06%,
other elements each 0.05%, combined 0.15%. We have found that in
order to achieve the desired level of toughness the foregoing
composition limits must be carefully followed, for instance,
increasing the magnesium content to a level of only 2.6 to 2.7%
markedly decreases the toughness.
The foregoing special composition limits in combination with
special high temperature thermal treatments where the temperatures
exceed those normally employed in alloys of the 7075 type together
with effective amounts of strain hardening all cooperate in
achieving the desired markedly improved toughness and tear
resistance in a sheet or plate product of very high strength.
Normally 7075 type sheet or plate is not heated above 930.degree.F
for any purpose, although it has now been found that unique
properties are obtained if this previous maximum is exceeded by
heating to at least 940.degree.F, preferably between 950.degree.
and 1000.degree.F. Preferably the fabrication cycle includes two
such exposures, one at the solution heat treating stage and one
somewhat earlier, during or before hot rolling. The improved sheet
product exhibits (1) a low volume fraction of intermetallic phases
containing Fe or Si of less than 0.7 percent total, (2) E phase
Al.sub.12 Mg.sub.2 Cr precipitate particles having a median size of
1400 A or larger together with (3) a fine grain size. These combine
to impart the improvement.
In this description reference is made to the drawings in which:
FIG. 1 is a graph plotting average yield strength versus tear
resistance for the improved and for comparison sheet products;
FIG. 2 is a plan view of one type of tear testing specimen; and
FIG. 3 is a graph plotting gross area stress versus crack length
for the improved and for comparison sheet products as determined
from tear tests using specimens of the type shown in FIG. 2.
Perhaps the best way to appreciate the type of improvement here
described is to refer to FIG. 1 which plots tensile yield strength
versus unit propagation energy for sheet products in 2000 series
alloys, Al-Cu systems, and 7000 series alloys, Al-Zn systems,
together with the improved sheet product. The plots are based on
averages of longitudinal and transverse properties. As explained
later, unit propagation energy is one measure of toughness, the
higher the UPE, the tougher and more tear resistant the material.
The lines in FIG. 1 depict the mean performance levels for the
various sheet alloys for ready comparison and certainly shows
clearly that the improved sheet offers the highest combination of
strength and toughness. For instance 2024 sheet in the T3temper
which has the highest toughness for this alloy, exhibits a UPE
level of over 600 which is considered quite tough as it certainly
exceeds a 400 UPE level which is considered a good indication of a
high toughness material. However note that the yield strength is
only 50 ksi which certainly cannot be considered high by modern
standards. On the other hand alloy 7075 sheet in the T73 temper, a
tough temper for this material, exhibits much better strength but
also a much lower UPE than 2024 sheet. This typifies the problem
facing the art which could provide sheet having high toughness or
high strength but not both. In direct contrast, FIG. 1 shows how
the improved sheet product changes the prior situation and exhibits
very high toughness at the highest strength levels. The improved
sheet can achieve UPE levels exceeding 1000 in-lb/in.sup.2 at yield
strength levels over 70 ksi which has not previously been
considered possible in an aluminum alloy sheet, especially in a
relatively economical and commercially useful sheet product.
In practicing the invention an aluminum alloy body having the above
described composition is provided preferably by continuous direct
chill casting techniques. The body is subjected to an elevated
temperature exposure at a temperature of at least 800.degree.F, and
preferably between 850.degree. to 900.degree.F, for at least 4
hours. This treatment, which is considered a homogenization,
overcomes as-cast dendritic microsegregation and provides an
essentially uniform microstructural distribution of the primary
solute elements Zn, Mg and Cu. However it also causes some
precipitation in situ of Cr as Al.sub.12 Mg.sub.2 Cr particles,
hereinafter E phase particles, which have a median size of 750 A
and a maximum size generally not exceeding 1000 A. After
homogenization the body is subjected to a carefully controlled high
temperature treatment wherein it is heated to a temperature of at
least 940.degree.F and preferably between 950.degree. and
1000.degree.F. It is held at this temperature for a period
generally of 6 to 48 hours. The heating rate to the high
temperature preferably does not exceed 150.degree.F per minute.
This high temperature treatment agglomerates and dissolves
precipitate particles of the Al.sub.12 Mg.sub.2 Cr, E phase, which
precipitated from supersaturated solid solution during the initial
elevated temperature exposure treatment. During the higher
temperature treatment these particles grow to a median size of 1400
A with some reaching up to 3000 A. This type of temperature
exposure is normally not employed on this type of alloy which is
normally subjected to lower treatments not exceeding 870.degree.F
because eutectic melting occurs at 890.degree.F.
After the elevated temperature exposure, the alloy body is
typically hot rolled, preferably at a temperature of 650.degree.F
to 850.degree.F to produce a slab which is then further rolled to
produce a plate. The special elevated temperature exposure need not
be applied at the ingot stage and can be applied after the alloy
body is rolled to slab, plate, or the like, but the use of this
treatment at the ingot stage is often the most practical. The hot
rolled plate is then typically further rolled employing hot, warm
or one or more continuous rolling operations which preferably end
with a cold rolling step. It is significant that these final
rolling operations impart to the sheet product an amount of strain
hardening and grain fragmentation equivalent to that which would be
developed in a cold rolling cross sectional reduction of at least
25% and preferably at least 45%. As just mentioned it is preferred
that some if not all of the hardening effect be imparted directly
by a cold rolling reduction as such in which case the hot, warm, or
continuously rolled product may, if desired, be annealed by heating
at 600.degree. to 800.degree.F prior to cold reduction especially
where the latter is rather severe, for example over 35 percent cold
reductions are especially useful in producing thin gauge sheet, for
instance sheet under 0.150 inch thick.
The sheet product is subjected to a high temperature solution heat
treatment at a temperature of 940.degree.F to 1000.degree.F, and
preferably 960.degree.F or higher. This treatment is important
because it dissolves fine Al.sub.12 Mg.sub.2 Cr particles, E phase
particles, which precipitate during the thermo-mechanical
treatments which followed the initial high temperature thermal
treatment. It is noteworthy that solution heat treatment as
contemplated by the improved method involves temperatures somewhat
above those conventionally used which usually range from
860.degree. to 920.degree.F. For instance MIL Spec H-6088D,
Amendment 2, prohibits temperatures over 930.degree.F for solution
treatment of 7075 sheet and over 880.degree.F for 7075 alloy in
other forms. The total time at temperature during the solution heat
treatment should be at least one-quarter hour, and preferably 2
hours or longer, although as described in more detail later,
circumstances may arise where it is advisable to provide some of
the solution heat treatment just prior to the cold reduction, in
which case the duration of the solution heat treatment after cold
rolling can be reduced to as low as about 3 minutes. After the
solution heat treatment, the sheet is quenched, preferably by spray
quenching or by immersion in water at a temperature not in excess
of 100.degree.F.
The quenched sheet is then artificially aged to fully develop its
properties. The aging treatment may consist of 10 to 180 hours at a
temperature of from 200 to 255.degree.F to produce the alloy sheet
in what may be called an isothermal T6 type temper in which the
sheet exhibits the optimum combination of strength and resistance
to tearing. While material in this temper may be preferred in some
instances, it is worth noting that it is not as resistant to stress
corrosion cracking as would be the case if the sheet were imparted
with what might be called a step T6 type temper where it is heated
in stages, the first stage being a 2 to 100 hour treatment at a
temperature of 200.degree. to 255.degree.F and the second being a 2
to 12 hour treatment at a temperature of 300.degree. to
335.degree.F. This increased resistance to stress corrosion
cracking is obtained with no sacrifice in strength and a small
sacrifice in tear resistance relative to that attained using the
isothermal T6type temper. The sheet will develop yet another
combination of properties if it is aged to what might be called a
T7 type temper where it is also heated in stages and where the
second stage is a 6 to 24 hour treatment at 315.degree.F to
350.degree.F. Sheet treated in this way develops slightly lower
strength, higher resistance to stress corrosion cracking, and
higher toughness relative to that of material treated by an
isothermal or a step T6 type treatment. In either two step
treatment (T6 type or T7 type) the time in the second step is
generally inverse to the temperature to avoid excessive aging
effects.
One embodiment of the invention contemplates the improved sheet as
a core layer in a clad sheet wherein a protective outer layer
serves to prevent corrosion of the core. The protective cladding is
in an alloy more anodic than the core to provide the desired
protection. These composites are well known in the aircraft
industry for their usefulness although such would be greatly
enhanced if the core would be imparted with improved toughness. The
clad sheet is produced in a manner very similar to that described
earlier for the bare sheet. In the primary ingot breakdown the
cladding is hot roll-bonded to the previously thermally treated
ingot and the fabrication proceeds as with the bare sheet. Suitable
cladding alloys include the nominal compositions listed below in
Table I.
TABLE I
A Al, 1% Zn
B Al, 2% Zn, 0.5% Mg
C Al, 5% Zn, 1.25% Mg
D Al, 5% Zn, 1.25% Mg, 0.75% Si
Some of the cladding compositions listed above are themselves
considered as contributing to the strength of the clad composite.
For instance, compositions B, C and D are heat treatable thus
imparting to the clad product a higher composite strength. Although
excessive diffusion is generally not observed in the improved clad
sheet more diffusion of core elements to the cladding occurs than
is usual in conventionally heat treated clad 7075 type sheet. This
increase is attributed to the 960.degree.F solution heat treatment.
To insure that the extent of any diffusion is not excessive, that
is, that the solution potential of the cladding surface would not
approach that of the core, care to avoid excessive exposure time is
warranted. One approach is to expose the sheet prior to cold
rolling to a 1-hour treatment at 960.degree.F, cool to room
temperature, cold roll and then final solution heat treat the sheet
briefly, around 3 to 20 minutes, at 960.degree.F after which it is
quenched. The second exposure at 960.degree.F may be in a
continuous furnace. This approach offers the advantage of the
prolonged exposure to solution temperature being performed while
the cladding is much thicker, prior to the final cold reduction, so
that the diffusion path to the cladding surface is longer.
As already suggested a property of great importance in the aircraft
industry is resistance to stress corrosion cracking which, as
described in U.S. Pat. No. 3,198,676, can be improved in
Al-Zn-Mg-Cu type alloys by employing a two-step aging treatment. As
indicated in that patent, good resistance to stress corrosion
cracking correlates well with an accelerated test where stress is
applied in a specimen amounting to 75 percent of the specimen's
yield strength and exposing the specimen so stressed to alternate
immersion in an aqueous solution containing 3.5 percent sodium
chloride. In that patent the type of product of primary concern
exhibited rather thick cross section such that the short transverse
properties become significant. In stress corrosion testing the
short transverse property is of most interest since it is the most
sensitive. In the alternate immersion test, survival of the
specimen for 84 days, approximately 3 months, correlates well with
substantial immunity to stress corrosion cracking effects in normal
environments. However, in a sheet product the short transverse
properties are not readily utilized and are not measured or tested.
Accordingly, stress corrosion test specimens are taken in the long
transverse direction, the direction in the plane of the sheet but
normal to the direction of rolling. Here a meaningful test requires
6 months to complete. Where the sheet is clad the test period has
to be extended to one year in order for the results to be
considered reliable for use in high performance applications such
as aircraft. That is, while shorter duration tests such as a
3-month test are useful in sheet products on a preliminary basis,
reliable testing requires much longer periods of 6 months for bare
sheet and one year for clad sheet. Because sheet is often formed
after it has been precipitation heat treated, the resistance to
stress corrosion cracking of plastically deformed sheet must also
be determined. The specimens used to evaluate the stress corrosion
performance of sheet are referred to as "preform" specimens and are
described in the Proceedings of the ASTM, Volume 65, 1965 on pages
182-197. Repeated tests of the type just outlined establish that
the improved sheet, clad or unclad, possesses the same order of
resistance to stress corrosion cracking as 7075 type alloys in the
various tempers. That is, the described improvements are realized
without any sacrifice in this important property.
In order to further illustrate the invention and the advantages
derived therefrom, the following illustrative examples 1 through 3
proceed.
EXAMPLE 1
Three ingots containing 5.72-5.84% Zn, 2.42-2.49% Mg, 1.37-1.53%
Cu, 0.19-0.20% Cr, 0.07-0.08% Fe, 0.07% Si, 0.02% Ti, 0.01-0.03%
Mn, the balance being aluminum were prepared by continuous casting.
The ingots were exposed for 6 hours at 860.degree.F and then heated
at not more than 150.degree.F per hour up to a 980.degree.F hold
temperature and held for 24 hours. The ingots were air cooled to
room temperature and thereafter clad with alloy A in Table I and
hot rolled during which their temperature did not fall below
750.degree.F to produce slabs about 4 inches in thickness. The
slabs were then reheated to a temperature of about 860.degree.F,
and then hot rolled to provide plate approximately three-fourths
inch in thickness. This plate was rolled on a continuous
multi-stand mill to produce sheet which was about 0.18 inch in
thickness. At this point the 0.18 inch sheet was annealed at a
temperature of 775.degree.F to soften it for cold rolling. The
sheet was then cold rolled to produce sheet about 0.090 inch in
thickness, a cold reduction of just about 50 percent. This sheet
was solution heat treated for 1 hour at 960.degree.F and quenched
by spraying with water maintained at a temperature
<100.degree.F. At this point the material was stretched to
flatten, then divided into three portions each of which was
subjected to a different aging treatment to provide material: (1)
in an isothermal T6 type temper (24 hours at 250.degree.F), (2) in
a step T6 type temper (3 hours at 245.degree.F, plus 3 hours at
315.degree.F) and (3) in a T7 type temper (3 hours at 250.degree.F
plus 12 hours at 325.degree.F). The average transverse properties,
which are those of prime importance in sheet products, for the
sheets from the three ingots are shown in Table II along with like
properties of comparison sheets of 7075 sheet with the same
cladding and in the two step T6 temper. The comparison 7075 sheet
was fabricated in the same manner as the improved sheet except for
the omission of the high temperature thermal treatment after
homogenization and the use of a solution heat treatment temperature
of only 870.degree.F. The aging treatment for the 7075 was the
standard step T6, 3 hours at 245.degree.F plus 3 hours at
315.degree.F. Tear resistance was measured by the Kahn tear test as
described in The Welding Journal published by the American Welding
Society, Volume 27, page 169 (1968). In this test an autographic
load-deformation curve is obtained while a crack is initiated in
and propagated across a test specimen. The total area under the
load-deformation curve is a measure of the energy required to
initiate and propagate a crack, conveniently expressed as
inch-pounds per square inch. That portion of the area following the
maximum load application determines the energy required to
propagate the crack, and when completed on a unit basis in
inch-pounds per square inch is defined as unit propagation energy,
abbreviated UPE. The tear strength is also determined, and the
ratio of the tear strength to the tensile yield strength is also
usually calculated because it gives a measure of the ability of the
material to deform plastically in the presence of a stress
raiser.
TABLE II - Transverse Properties for Clad Sheet
______________________________________ Material T.S. ksi Y.S. ksi %
El. in 2" UPE in.- lb./in..sup.2 Tear Strength to Y.S.
______________________________________ Ratio A-Improved T6 iso. 77
66 14 810 1.44 B-Improved T6 step 76 67 12 690 1.41 C-Improved T7
74 65 11 825 1.44 D-7075-T6 step 78 67 11 225 0.97
______________________________________
From the table it becomes apparent that the improved clad sheet
composite has tensile (T.S.), yield strength (Y.S.) and elongation
levels readily comparable to those of clad 7075 alloy and others of
this type. However, the UPE and tear strength to yield strength
ratio (a measure of ability to deform plastically in the presence
of a stress raiser) of the improved sheet are much higher than
those of 7075 alloy. Also the toughness of the improved sheet is
higher than for other alloys of the 7075 type, for instance,
referring to U.S. Pat. No. 3,198,676, it can be seen that 0.064
inch sheet of other 7000 type alloys cannot be depended upon to
exhibit transverse UPE levels much above 200. The improved sheet
obviously represents a marked improvement.
EXAMPLE 2
In addition to tear test data (UPE) of the type presented in
Example 1, another measure of toughness and tear resistance in
sheet well known in the fracture mechanics field is that of the
sheet's critical stress intensity factor K.sub.c. In this approach
to testing, large sheet samples typically 44 inches in length and
16 inches in width are tested to determine crack propagation
effects. The long dimension corresponds to stress direction; where
the transverse properties are being tested, the long dimension
corresponds to the direction in the plane of the sheet that is
perpendicular to the principal rolling direction. The sheet
thickness is not critical in the test although it should be
representative of the product contemplated. The sample, shown in
FIG. 2, is prepared for testing by having a hole machined or
drilled in its center. Slots are provided parallel to the short
dimension of the sample. The sheet is gripped at each end and a
tension load is applied along the length of the sample. This force
is applied until a crack is just initiated at each end of the slot.
Once the cracks are initiated the meaningful part of the test
commences. A constantly increasing load is applied until the crack
growth becomes unstable, that is, a crack propagates at an
instantaneous or almost explosive rate. This would be symbolic of a
catastrophic instantaneous tear failure which could possibly occur
in aircraft skin with disastrous results. K.sub.c is calculated
from gross area stress (load divided by original cross section
area, 16" .times. thickness), and from crack length at the onset of
rapid crack propagation. Consequently, K.sub.c is a measure of a
material's ability to tolerate a crack under stress without failing
catastrophically. The higher the K.sub.c value, the greater the
tolerance for the sheet material to sustain a crack of greater
length without failing catastrophically. Once K.sub.c is obtained,
the residual strength of cracked panels can be calculated. This
concept is described further in the Special ASTM Committee Report
"Fracture Testing of High Strength Sheet Materials", ASTM Bulletin
No. 243, January 1960, pages 29-40. A comparison of the improved
sheet in both of the two-step aging tempers with 2024-T3 and
7075-T6 sheet is shown in the curves of FIG. 3 where curve I-1
represents the improved material in the two-step T7 type temper and
curve I-2 applies to the two-step T6 type temper. In viewing FIG.
3, it can be seen that the improved material is somewhat superior
to alloy 2024-T3 which is considered to be a high tear resistant
material although its lower tensile and yield strengths require use
of thicker sections and consequently necessitates an appreciable
weight penalty in aircraft and other weight-critical applications.
Alloy 7075 is clearly inferior in tear resistance to both 2024 and
the even more favorable improved alloy sheet, curves I-1 and I-2.
In viewing FIG. 3 it can be seen that for each sheet the length of
the crack can be increased without affecting the gross area stress
at failure GS up to some point after which lengthening the crack
drastically reduces GS. Comparing the improved sheet versus 7075
alloy sheet, it can be seen at a GS of 30 ksi 7075 sheet will fail
if the crack reaches about 2 1/2 inches in length whereas the
improved sheet will sustain crack lengths of over 5 and over 6
inches depending on the aging treatment, that is, the crack length
can be twice or even three times the crack length where the 7075
sheet failed. Another comparison might be to consider a 6 inch
crack and FIG. 3 indicates that 7075 alloy sheet fails at less than
20 ksi GS whereas the improved sheet approaches and exceeds 30 ksi
GS. This type of test is perhaps the most important to the aircraft
industry since such determines the actual extent to which a
material can sustain cracks. A material which appears favorable in
this test inherently provides for greater safety and greater
periods between inspection of an aircraft's skin for cracks.
In addition to the data shown in FIG. 3, the comparison set forth
in Example 1 and Table II is presented in the terms of K.sub.c in
Table III below. In the table the sheet material designations refer
to Table II as does the UPE data.
TABLE III - Transverse Tear Data
______________________________________ Sheet Material UPE K.sub.c
______________________________________ A 810 118 B 690 105 C 825
120 D 225 63 ______________________________________
From the foregoing table and FIG. 3, it is quite apparent that the
improved material, curves I-1 and I-2 in FIG. 3 and materials A, B
and C in Table III, represents a marked improvement in toughness
and tear resistance over alloy 7075 sheet.
EXAMPLE 3
In addition to the very important aspect of catastrophic or
unstable cracking, the area of stable crack propagation in fatigue
is also of great importance in sheet applications. In fatigue
testing a sample of the general configuration described in Example
2 but about 4 .times. 14 3/4 inches in size is prepared and a crack
initiated along the lines of Example 2. However, the applied load
in this case is rather low but is of a cyclic nature. The
meaningful part of the test commences after cracks initiate from
both ends of the hole and propagate to a total length, including
the starter hole, of 0.50 inch. To determine the rate of fatigue
crack propagation, cyclic axial tension loads of varying levels are
applied to specimens and the rate of crack growth in terms of
microinches per cycle is measured. The stress intensity factor K,
as described above, is proportioned to the stress at the tip of a
propagating crack. The longer the crack becomes, the greater
becomes the stress intensity factor K for a given gross area stress
GS. Table IV below lists a comparison between the improved sheet
and 7075 sheet both clad with alloy A from Table I and 0.090 inch
in thickness at varying levels of the stress intensity factor
K.
TABLE IV - Crack Growth Per Cycle
______________________________________ K (ksi .sqroot. in.)
Improved 7075 ______________________________________ 10 6 7 20 35
50 30 90 300 40 260 1000 ______________________________________
It can be seen in the table that at the relatively low levels of K,
for instance 10 or 20 ksi .sqroot. in., the performance of the
improved sheet is not strikingly different from that of 7075 sheet.
However, at the higher and more critical K levels, for example K=30
or 40, the fatigue crack propagation rate in 7075 sheet becomes
approximately four times that of the improved sheet. This again
verifies that the improved sheet provides greater safety and
extends the periods required between inspections for cracks in
aircraft skin and similar critical applications.
From the foregoing and the further illustrative examples which
follow it can be seen that the improved sheet product exhibits a
unique combination of strength and toughness or resistance to
tearing. The improved sheet has consistently demonstrated a typical
K.sub.c of 85 ksi .sqroot. in. or more at yield strength levels up
to 70 ksi and even higher in the transverse direction which is the
critical direction in sheet type products. This property is
conspicuously peculiar to the improved sheet. For instance, while
2024 alloy sheet also exceeds 7075 sheet in tear resistance, its
use is limited by its lower strength. The yield strength for the
improved sheet is substantially the same as that associated with
7075 sheet products and generally ranges from 60 to 75 ksi
depending largely on the aging treatment. The minimum critical
stress intensity K.sub.c ranges, generally inversely with yield
strength, from about 75 to about 85 or even 100 and higher ksi
.sqroot. in. Nonetheless, a yield strength of 70 ksi and a K.sub.c
level of 85 ksi .sqroot. in. or more certainly typifies the
improved material which can be contrasted with 7075 sheet material
having a yield strength of 70 ksi but a typical K.sub.c of only 60.
The markedly improved properties of the improved sheet appear to be
associated with certain features which are revealed on examination.
The improved sheet exhibits: (1) a pattern of fine grains, from 300
to 10,000 or more grains per cubic millimeter, (2) an E phase
Al.sub.12 Mg.sub.2 Cr precipitate, particle size median of at least
1400 angstroms and (3) a low volume fraction of iron-bearing phase,
less than 0.45%, and of silicon-bearing phase, less than 0.25%.
These characteristics can be contrasted with conventional 7075
sheet which may or may not have fine grains and wherein the E phase
particle size rarely exceeds 1,000 A with the median size being
about 750 A. The volume fraction in 7075 sheet for iron-bearing
phase is up to 2.4% and typically about 1.4%, and for the
silicon-bearing phase up to 1.7% and typically about 1%. The above
described characteristics of the improved sheet appear to result in
the markedly and surprisingly improved properties in that
conventional 7075 sheet, without these characteristics, exhibits
comparatively low tear resistance.
To illustrate the importance of the limits described in connection
with the invention, the following further examples proceed.
EXAMPLE 4
Clad sheet, 0.090 inch thick, was fabricated in a sequence
substantially identical with that of Example 1. The core contained
5.8% Zn, 2.6% Mg, 1.8% Cu, 0.19% Cr, balance essentially aluminum
and 0.07% Fe and 0.04% Si as impurities. The cladding contained
5.3% Zn, 1.1% Mg, 0.03% Cu, 0.21% Cr, balance aluminum and
impurities. The fabrication sequence included the high temperature
thermal treatments, including solution heat treatment, in
accordance with the invention and the sheet was aged for three
hours at 245.degree.F plus three hours at 315.degree.F, a two-step
T6 type treatment. The long transverse properties of the composite
and of specimens from the core are shown below in Table V.
TABLE V ______________________________________ T.S. ksi Y.S. ksi %
El. in 2" UPE in.-lb/in..sup.2 Tear Str. Y.S.
______________________________________ Composite 81 74 12 220 0.86
Core 86 79 12 120 0.85 ______________________________________
From the foregoing table it becomes immediately clear that the UPE
of this sheet is drastically reduced in comparison with the
improved clad sheet described in Example 1. This together with
several other tests have verified that increasing the magnesium
content from the herein described maximum of 2.5% up to a mere 2.6%
results in a marked deterioration of tear resistance. That is,
controlling Mg within the herein prescribed limits of 1.9 to 2.5%
surprisingly enables achieving both high strength and very high
toughness.
EXAMPLE 5
Sheet containing 5.8% Zn, 2.3% Mg, 1.6% Cu, 0.20% Cr, balance
aluminum and 0.01% Fe and 0.01% Si as impurities was produced
without cladding but otherwise substantially as described in
Example 1 except that some of the sheet included a 50% cold rolling
reduction and some included no cold rolling reduction. All the
sheet was aged 24 hours at 250.degree.F, an isothermal T6 type
treatment. The long transverse properties of both sheets are shown
below in Table VI.
TABLE VI ______________________________________ % Cold Roll T.S.
ksi Y.S. ksi % El. in 2" UPE in.-lb/in..sup.2 Tear Str. to Y.S.
______________________________________ Ratio 0 80 73 15 395 1.35
50% 80 71 15 1005 1.44 ______________________________________
From Table VI it becomes clear that material in accordance with the
improved composition which has received the improved thermal
treatments is sensitive to cold rolling which can be employed to
optimize tear resistance in that the sheet which received a 50%
cold reduction exhibits greatly improved tear resistance over that
which received no cold reduction.
EXAMPLE 6
Sheet containing 5.5% Zn, 2.5% Mg, 1.65% Cu, 0.25% Cr, balance
essentially aluminum and 0.07% Fe and 0.08% Si as impurities was
produced by hot rolling followed by cold rolling to the final gauge
of 0.064 inch. The cold rolling reduction amounted to over 50% but
the ingot included only a 16 hour homogenization treatment at
860.degree.F and no high temperature treatment in accordance with
the invention. The sheet was solution heat treated at a temperature
of only 860.degree.F. These thermal treatments are in accordance
with current practices for 7075 type alloy sheet. The unit
propagation energy for this sheet was only 340
in.-lb/in..sup.2.
In comparing Examples 5 and 6 it becomes clear that to dependably
achieve high tear resistance of over 400 UPE the improved thermal
treatments should be employed along with substantial strain
hardening effects. In Example 6 where the sheet composition was in
accordance with the invention but there was no thermal treatment in
accordance with the improved method, a cold reduction of over 50%
failed to bring the tear resistance up to the desired level. In
Example 5 it can be seen that a 50% cold reduction markedly
improves tear resistance on sheet otherwise in accordance with the
invention.
EXAMPLE 7
To illustrate further the influence of cold rolling on the improved
sheet and that the improvement derived therefrom is progressive, an
ingot containing 5.7% Zn, 2.4% Mg, 1.3% Cu, 0.2% Cr, balance
aluminum and impurities in accordance with the invention was
fabricated into 0.180 inch thick sheet generally according to the
practice described in Example 1. The sheet was annealed and divided
into several portions which were cold rolled to various reductions
after which they were solution heat treated one hour at
960.degree.F, quenched and then aged 24 hours at 250.degree.F, an
isothermal T6 type treatment. The yield strength of all the sheet
was approximately 72 ksi and the unit propagation energy levels for
the various sheet portions are listed below in Table VII.
TABLE VII ______________________________________ Percent Cold
Rolling UPE in.-lb/in..sup.2 ______________________________________
0 430 25 555 30 590 35 640 40 625 45 690 50 805
______________________________________
From table VII it can be seen that cold rolling prior to solution
heat treatment has a significant influence on the tear resistance
developed in the improved sheet. By way of comparison sheet having
the same composition as that described in Example 5 was fabricated
in accordance with the invention, including a 50% cold rolling
reduction, except that the solution heat treatment temperature was
reduced to only 915.degree.F. The UPE for this sheet was only 285
in.-lb/in..sup.2 which again underscores the cooperation of the
thermal treatment with the other factors described herein for the
improved method.
The method described above including two separate high temperature
thermal treatments is preferred since it dependably results in the
desired improved sheet product. This is especially so where the
initial metal form is an ingot or other body or slab of substantial
thickness, over eight inches, which is reduced to produce the sheet
product. In this case we have found it highly preferable that both
high temperature thermal treatments be employed, that is, at the
ingot or other thick slab stage and at the solution heat treatment
stage. However, especially where the starting material is a
relatively thin body, for example, a cast plate 1 or 2 inches
thick, or where exposure of rather extended duration can be
tolerated in solution treatment, a substantial amount of the
benefits of the invention can be achieved by a single exposure to a
metal temperature of at least 940.degree.F. Accordingly, in its
broadest aspect, the invention contemplates a single high
temperature treatment although on a somewhat less preferred basis.
That is, in its broadest aspect the invention contemplates
sufficient exposure to temperature over 940.degree.F, and
preferably between 950.degree. and 1000.degree. F, to provide the
desired 1400A or larger E phase median particle size.
While this description emphasizes sheet and its production, it is
to be understood that such refers to a rolled product which can
range in thickness up to about 0.25 inch and even more. It is not
intended that the term "sheet" necessarily refer to arbitrary
numerical restrictions often employed to separate sheet from plate,
and the like, type products. Nonetheless a preferred embodiment of
the invention contemplates sheet ranging in thickness from about
0.020 inch to about 0.250 inch since such is most useful in the
aircraft industry where the highest possible strength and tear
resistance is needed for skin covering.
* * * * *