U.S. patent application number 12/560000 was filed with the patent office on 2011-03-17 for direct extrusion of shapes with l12 aluminum alloys.
This patent application is currently assigned to UNITED TECHNOLOGIES CORPORATION. Invention is credited to Awadh B. Pandey.
Application Number | 20110064599 12/560000 |
Document ID | / |
Family ID | 43413921 |
Filed Date | 2011-03-17 |
United States Patent
Application |
20110064599 |
Kind Code |
A1 |
Pandey; Awadh B. |
March 17, 2011 |
DIRECT EXTRUSION OF SHAPES WITH L12 ALUMINUM ALLOYS
Abstract
A method for producing a high strength aluminum alloy brackets,
cases, tubes, ducts, beams, spars and other parts containing
L1.sub.2 dispersoids from an aluminum alloy powder containing the
L1.sub.2 dispersoids. The powder is consolidated into a billet
having a density of about 100 percent. The billet is extruded using
an extrusion die shaped to produce the component.
Inventors: |
Pandey; Awadh B.; (Jupiter,
FL) |
Assignee: |
UNITED TECHNOLOGIES
CORPORATION
Hartford
CT
|
Family ID: |
43413921 |
Appl. No.: |
12/560000 |
Filed: |
September 15, 2009 |
Current U.S.
Class: |
419/12 ; 419/13;
419/14; 419/19; 419/23; 419/28; 420/528; 420/529; 420/540; 420/542;
420/543; 420/548; 420/550; 420/551; 420/552; 420/553; 75/235;
75/236; 75/244 |
Current CPC
Class: |
B22F 3/20 20130101; B22F
2998/10 20130101; C22C 21/00 20130101; B22F 2999/00 20130101; C22C
21/02 20130101; C22C 1/0416 20130101; C22C 21/06 20130101; C22C
21/10 20130101; B22F 2998/10 20130101; B22F 2999/00 20130101; C22C
21/12 20130101; B22F 3/1216 20130101; B22F 3/14 20130101; B22F
2201/20 20130101; B22F 3/1216 20130101; B22F 3/20 20130101; B22F
9/082 20130101; B22F 2003/145 20130101 |
Class at
Publication: |
419/12 ; 419/28;
419/19; 419/14; 419/13; 420/528; 420/552; 75/235; 75/236; 75/244;
420/548; 420/542; 420/543; 420/553; 420/529; 420/540; 420/550;
420/551; 419/23 |
International
Class: |
B22F 3/20 20060101
B22F003/20; B22F 3/24 20060101 B22F003/24; C22C 21/00 20060101
C22C021/00; C22C 32/00 20060101 C22C032/00; C22C 21/02 20060101
C22C021/02; C22C 21/06 20060101 C22C021/06; C22C 21/12 20060101
C22C021/12; C22C 21/10 20060101 C22C021/10 |
Claims
1. A method for forming a high strength aluminum alloy component
containing L1.sub.2 dispersoids, comprising the steps of: placing
in a container a quantity of an aluminum alloy powder containing an
L1.sub.2 dispersoid L1.sub.2 comprising Al.sub.3X dispersoids
wherein X is at least one first element selected from the group
comprising: about 0.1 to about 4.0 weight percent scandium, about
0.1 to about 20.0 weight percent erbium, about 0.1 to about 15.0
weight percent thulium, about 0.1 to about 25.0 weight percent
ytterbium, and about 0.1 to about 25.0 weight percent lutetium; at
least one second element selected from the group comprising about
0.1 to about 20.0 weight percent gadolinium, about 0.1 to about
20.0 weight percent yttrium, about 0.05 to about 4.0 weight percent
zirconium, about 0.05 to about 10.0 weight percent titanium, about
0.05 to about 10.0 weight percent hafnium, and about 0.05 to about
5.0 weight percent niobium; and the balance substantially aluminum;
the alloy powder having a mesh size of less than 450 mesh in a
container, vacuum degassing the powder at a temperature of about
300.degree. F. (149.degree. C.) to about 900.degree. F.
(482.degree. C.) for about 0.5 hours to about 8 days; sealing the
degassed powder in the container under vacuum; heating the sealed
container at about 300.degree. F. (149.degree. C.) to about
900.degree. F. (482.degree. C.) for about 15 minutes to eight
hours; vacuum hot pressing the heated container to form a billet;
removing the container from the formed billet; and extruding the
billet into a component using an extrusion die shaped to form the
component.
2. The method of claim 1, wherein the aluminum alloy powder
contains at least one ceramic selected from the group comprising:
about 5 to about 40 volume percent aluminum oxide, about 5 to about
40 volume percent silicon carbide, about 5 to about 40 volume
percent aluminum nitride, about 5 to about 40 volume percent
titanium diboride, about 5 to about 40 volume percent titanium
boride, about 5 to about 40 volume percent boron carbide and about
5 to about 40 volume percent titanium carbide.
3. The method of claim 1, wherein the aluminum alloy powder
contains at least one third element selected from the group
consisting of silicon, magnesium, manganese, lithium, copper, zinc,
and nickel.
4. The method of claim 3, wherein the third element comprises at
least one of about 4 to about 25 weight percent silicon, about 1 to
about 8 weight percent magnesium, about 0.1 to about 3 weight
percent manganese, about 0.5 to about 3 weight percent lithium,
about 0.2 to about 6 weight percent copper, about 3 to about 12
weight percent zinc, about 1 to about 12 weight percent nickel.
5. The method of claim 1, wherein the extrusion is carried out at a
temperature of from about 300.degree. F. (148.9.degree. C.) to
about 900.degree. F. (482.2.degree. C.).
6. The method of claim 1, wherein the extrusion is carried out at
rate of about 0.1 inch per minute to about 20 inch per minute.
7. The method of claim 1, the billet temperature ranges from about
300.degree. F. (148.9.degree. C.) to about 900.degree. F.
(482.2.degree. C.).
8. The method of claim 1, wherein billet has a soak time ranging
from about 0.5 hours to about 8 hours.
9. The method of claim 1, wherein the extrusion is carried out at
ratios of about 2:1 to 40:1.
10. The method of claim 1, wherein the extrusion die temperature
ranges from about 300.degree. F. (148.9.degree. C.) to about
900.degree. F. (482.2.degree. C.).
11. The method of claim 1, wherein consolidating the powders
comprises: sieving the powders to achieve a particle size of less
than about -325 mesh; placing the powders in a container with a
rectangular cross-section; vacuum degassing the powder; sealing the
container; and hot pressing the container to achieve a powder
density of about 100 percent.
12. The method of claim 1, wherein the high strength aluminum alloy
component is selected from brackets, cases, tubes, ducts, beams,
spars and other components for gas turbine engines, rocket engines
and other aerospace applications.
13. A high strength aluminum alloy component, comprising: an
extruded aluminum alloy billet containing an L1.sub.2 dispersoid
comprising Al.sub.3X dispersoids wherein X is at least one first
element selected from the group comprising: about 0.1 to about 4.0
weight percent scandium, about 0.1 to about 20.0 weight percent
erbium, about 0.1 to about 15.0 weight percent thulium, about 0.1
to about 25.0 weight percent ytterbium, and about 0.1 to about 25.0
weight percent lutetium; at least one second element selected from
the group comprising about 0.1 to about 20.0 weight percent
gadolinium, about 0.1 to about 20.0 weight percent yttrium, about
0.05 to about 4.0 weight percent zirconium, about 0.05 to about
10.0 weight percent titanium, about 0.05 to about 10.0 weight
percent hafnium, and about 0.05 to about 5.0 weight percent
niobium; and the balance substantially aluminum; the billet being
extruded into a component using an extrusion die shaped to form the
component.
14. The alloy component of claim 11, wherein the aluminum alloy
component powder contains at least one ceramic selected from the
group comprising: about 5 to about 40 volume percent aluminum
oxide, about 5 to about 40 volume percent silicon carbide, about 5
to about 40 volume percent aluminum nitride, about 5 to about 40
volume percent titanium diboride, about 5 to about 40 volume
percent titanium boride, about 5 to about 40 volume percent boron
carbide and about 5 to about 40 volume percent titanium
carbide.
15. The method of claim 13, wherein the aluminum alloy powder
contains at least one third element selected from the group
consisting of silicon, magnesium, manganese, lithium, copper, zinc,
and nickel.
16. The method of claim 15, wherein the third element comprises at
least one of about 4 to about 25 weight percent silicon, about 1 to
about 8 weight percent magnesium, about 0.1 to about 3 weight
percent manganese, about 0.5 to about 3 weight percent lithium,
about 0.2 to about 6 weight percent copper, about 3 to about 12
weight percent zinc, about 1 to about 12 weight percent nickel.
17. The alloy component of claim 13, wherein the extrusion is
carried out at a temperature of from about 300.degree. F.
(148.9.degree. C.) to about 900.degree. F. (482.2.degree. C.).
18. The alloy component of claim 13, wherein the extrusion is
carried out at about 0.1 inch per minute to about 20 inch per
minute.
19. The alloy component of claim 13, the billet temperature ranges
from about 300.degree. F. (148.9.degree. C.) to about 900.degree.
F. (482.2.degree. C.).
20. The alloy component of claim 13 wherein billet has a soak time
ranging from about 0.5 hours to about 8 hours.
21. The alloy component of claim 13, wherein the extrusion is
carried out ratios of about 2:1 to about 40:1.
22. The alloy component of claim 13, wherein the extrusion die
temperature ranges from about 300.degree. (148.9.degree. C. to
about 900.degree. F. (482.2.degree. C.).
23. The alloy component of claim 13, wherein consolidating the
powders comprises: sieving the powders to achieve a particle size
of less than about -325 mesh; placing the powders in a container
with a rectangular cross-section; vacuum degassing the powder;
sealing the container; and hot pressing the container to achieve a
powder density of about 100 percent.
24. The alloy component of claim 13, wherein the high strength
aluminum alloy component is selected from brackets, cases, tubes,
ducts, beam, spars and other components for gas turbine engines,
rocket engines and other aerospace applications.
Description
CROSS-REFERENCE TO RELATED APPLICATION(S)
[0001] This application is related to the following co-pending
applications that were filed on Dec. 9, 2008 herewith and are
assigned to the same assignee: CONVERSION PROCESS FOR HEAT
TREATABLE L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/316,020; A METHOD
FOR FORMING HIGH STRENGTH ALUMINUM ALLOYS CONTAINING L1.sub.2
INTERMETALLIC DISPERSOIDS, Ser. No. 12/316,046; and A METHOD FOR
PRODUCING HIGH STRENGTH ALUMINUM ALLOY POWDER CONTAINING L1.sub.2
INTERMETALLIC DISPERSOIDS, Ser. No. 12/316,047.
[0002] This application is also related to the following co-pending
applications that were filed on Apr. 18, 2008, and are assigned to
the same assignee: L1.sub.2 ALUMINUM ALLOYS WITH BIMODAL AND
TRIMODAL DISTRIBUTION, Ser. No. 12/148,395; DISPERSION STRENGTHENED
L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,432; HEAT TREATABLE
L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,383; HIGH STRENGTH
L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,394; HIGH STRENGTH
L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,382; HEAT TREATABLE
L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,396; HIGH STRENGTH
L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,387; HIGH STRENGTH
ALUMINUM ALLOYS WITH L1.sub.2 PRECIPITATES, Ser. No. 12/148,426;
HIGH STRENGTH L1.sub.2 ALUMINUM ALLOYS, Ser. No. 12/148,459; and
L1.sub.2 STRENGTHENED AMORPHOUS ALUMINUM ALLOYS, Ser. No.
12/148,458.
BACKGROUND
[0003] The present invention relates generally to aluminum alloys
and more specifically to a method for forming high strength
aluminum ally powder having L1.sub.2 dispersoids therein into
aluminum parts such as brackets, cases and other components of
turbine engines as well as other products fabricated from aluminum
alloys.
[0004] The combination of high strength, ductility, and fracture
toughness, as well as low density, make aluminum alloys natural
candidates for as variety of applications. Because of its low
weight high strength, ductility and fracture toughness, aluminum
alloys are of interest in the manufacture and use for many
applications.
[0005] The development of aluminum alloys with improved elevated
temperature mechanical properties is a continuing process. Some
attempts have included aluminum-iron and aluminum-chromium based
alloys such as Al--Fe--Ce, Al--Fe--V--Si, Al--Fe--Ce--W, and
Al--Cr--Zr--Mn that contain incoherent dispersoids. These alloys,
however, also lose strength at elevated temperatures due to
particle coarsening. In addition, these alloys exhibit ductility
and fracture toughness values lower than other commercially
available aluminum alloys.
[0006] Other attempts have included the development of mechanically
alloyed Al--Mg and Al--Ti alloys containing ceramic dispersoids.
These alloys exhibit improved high temperature strength due to the
particle dispersion, but the ductility and fracture toughness are
not improved.
[0007] U.S. Pat. No. 6,248,453 discloses aluminum alloys
strengthened by dispersed Al.sub.3X L1.sub.2 intermetallic phases
where X is selected from the group consisting of Sc, Er, Lu, Yb,
Tm, and Lu. The Al.sub.3X particles are coherent with the aluminum
alloy matrix and are resistant to coarsening at elevated
temperatures. The improved mechanical properties of the disclosed
dispersion strengthened L1.sub.2 aluminum alloys are stable up to
572.degree. F. (300.degree. C.). U.S. Patent Application
Publication No. 2006/0269437 A1 discloses a high strength aluminum
alloy that contains scandium and other elements that is
strengthened by L1.sub.2 dispersoids.
[0008] L1.sub.2 strengthened aluminum alloys have high strength and
improved fatigue properties compared to commercial aluminum alloys.
Fine grain size results in improved mechanical properties of
materials. Hall-Petch strengthening has been known for decades
where strength increases as grain size decreases. An optimum grain
size for optimum strength is in the nano range of about 30 to 100
nm. These alloys also have higher ductility.
SUMMARY
[0009] The present invention is a method for consolidating aluminum
alloy powders into useful components such as brackets, cases and
other components having improved strength and fracture toughness.
In embodiments, powders include an aluminum alloy having coherent
L1.sub.2 Al.sub.3X dispersoids where X is at least one first
element selected from scandium, erbium, thulium, ytterbium, and
lutetium, and at least one second element selected from gadolinium,
yttrium, zirconium, titanium, hafnium, and niobium. The balance is
substantially aluminum containing at least one alloying element
selected from silicon, magnesium, manganese, lithium, copper, zinc,
and nickel.
[0010] The aluminum alloy components and parts are formed by direct
extrusion of consolidated billets using a die with the required
component shape. Extrusion of these alloys produces considerable
improvement in mechanical properties, especially ductility compared
to the consolidated billet. Extrusion parameters include billet
temperature, billet soak time, extrusion rate, extrusion ratio and
die temperature.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] FIG. 1 is an aluminum scandium phase diagram.
[0012] FIG. 2 is an aluminum erbium phase diagram.
[0013] FIG. 3 is an aluminum thulium phase diagram.
[0014] FIG. 4 is an aluminum ytterbium phase diagram.
[0015] FIG. 5 is an aluminum lutetium phase diagram.
[0016] FIG. 6A is a schematic diagram of a vertical gas
atomizer.
[0017] FIG. 6B is a close up view of nozzle 108 in FIG. 6A.
[0018] FIGS. 7A and 7B are SEM photos of the inventive aluminum
alloy powder.
[0019] FIGS. 8A and 8B are optical micrographs showing the
microstructure of gas atomized L1.sub.2 aluminum alloy powder.
[0020] FIG. 9 is a diagram showing the steps of the gas atomization
process.
[0021] FIG. 10 is a diagram showing the processing steps to
consolidate the L1.sub.2 aluminum alloy powder.
[0022] FIG. 11 is a schematic diagram of blind die compaction.
[0023] FIG. 12 is a schematic diagram of a direct extrusion
process.
[0024] FIG. 13 A-C are extrusions and examples of products made by
sectioning off extrusions.
[0025] FIG. 14 is a schematic of a hollow extrusion die.
[0026] FIG. 15 is a photograph of duct produced for a rocket
engine.
DETAILED DESCRIPTION
1. L1.sub.2 Aluminum Alloys
[0027] Alloy powders of this invention are formed from aluminum
based alloys with high strength and fracture toughness for
applications at temperatures from about -420.degree. F.
(-251.degree. C.) up to about 650.degree. F. (343.degree. C.). The
aluminum alloy comprises a solid solution of aluminum and at least
one element selected from silicon, magnesium, manganese, lithium,
copper, zinc, and nickel strengthened by L1.sub.2 Al.sub.3X
coherent precipitates where X is at least one first element
selected from scandium, erbium, thulium, ytterbium, and lutetium,
and at least one second element selected from gadolinium, yttrium,
zirconium, titanium, hafnium, and niobium.
[0028] The binary aluminum magnesium system is a simple eutectic at
36 weight percent magnesium and 842.degree. F. (450.degree. C.).
There is complete solubility of magnesium and aluminum in the
rapidly solidified inventive alloys discussed herein
[0029] The binary aluminum silicon system is a simple eutectic at
12.6 weight percent silicon and 1070.6.degree. F. (577.degree. C.).
There is complete solubility of silicon and aluminum in the rapidly
solidified inventive alloys discussed herein.
[0030] The binary aluminum manganese system is a simple eutectic at
about 2 weight percent manganese and 1216.4.degree. F. (658.degree.
C.). There is complete solubility of manganese and aluminum in the
rapidly solidified inventive alloys discussed herein.
[0031] The binary aluminum lithium system is a simple eutectic at 8
weight percent lithium and 1105.degree. (596.degree. C.). The
equilibrium solubility of 4 weight percent lithium can be extended
significantly by rapid solidification techniques. There is complete
solubility of lithium in the rapid solidified inventive alloys
discussed herein.
[0032] The binary aluminum copper system is a simple eutectic at 32
weight percent copper and 1018.degree. F. (548.degree. C.). There
is complete solubility of copper in the rapidly solidified
inventive alloys discussed herein.
[0033] The aluminum zinc binary system is a eutectic alloy system
involving a monotectoid reaction and a miscibility gap in the solid
state. There is a eutectic reaction at 94 weight percent zinc and
718.degree. F. (381.degree. C.). Zinc has maximum solid solubility
of 83.1 weight percent in aluminum at 717.8.degree. F. (381.degree.
C.), which can be extended by rapid solidification processes.
Decomposition of the supersaturated solid solution of zinc in
aluminum gives rise to spherical and ellipsoidal GP zones, which
are coherent with the matrix and act to strengthen the alloy.
[0034] The aluminum nickel binary system is a simple eutectic at
5.7 weight percent nickel and 1183.8.degree. F. (639.9.degree. C.).
There is little solubility of nickel in aluminum. However, the
solubility can be extended significantly by utilizing rapid
solidification processes. The equilibrium phase in the aluminum
nickel eutectic system is L1.sub.2 intermetallic Al.sub.3Ni.
[0035] In the aluminum based alloys disclosed herein, scandium,
erbium, thulium, ytterbium, and lutetium are potent strengtheners
that have low diffusivity and low solubility in aluminum. All these
elements form equilibrium Al.sub.3X intermetallic dispersoids where
X is at least one of scandium, erbium, thulium, ytterbium, and
lutetium, that have an L1.sub.2 structure that is an ordered face
centered cubic structure with the X atoms located at the corners
and aluminum atoms located on the cube faces of the unit cell.
[0036] Scandium forms Al.sub.3Sc dispersoids that are fine and
coherent with the aluminum matrix. Lattice parameters of aluminum
and Al.sub.3Sc are very close (0.405 nm and 0.410 nm respectively),
indicating that there is minimal or no driving force for causing
growth of the Al.sub.3Sc dispersoids. This low interfacial energy
makes the Al.sub.3Sc dispersoids thermally stable and resistant to
coarsening up to temperatures as high as about 842.degree. F.
(450.degree. C.). Additions of magnesium in aluminum increase the
lattice parameter of the aluminum matrix, and decrease the lattice
parameter mismatch further increasing the resistance of the
Al.sub.3Sc to coarsening. Additions of zinc, copper, lithium,
silicon, manganese and nickel provide solid solution and
precipitation strengthening in the aluminum alloys. These
Al.sub.3Sc dispersoids are made stronger and more resistant to
coarsening at elevated temperatures by adding suitable alloying
elements such as gadolinium, yttrium, zirconium, titanium, hafnium,
niobium, or combinations thereof, that enter Al.sub.3Sc in
solution.
[0037] Erbium forms Al.sub.3Er dispersoids in the aluminum matrix
that are fine and coherent with the aluminum matrix. The lattice
parameters of aluminum and Al.sub.3Er are close (0.405 nm and 0.417
nm respectively), indicating there is minimal driving force for
causing growth of the Al.sub.3Er dispersoids. This low interfacial
energy makes the Al.sub.3Er dispersoids thermally stable and
resistant to coarsening up to temperatures as high as about
842.degree. F. (450.degree. C.). Additions of magnesium in aluminum
increase the lattice parameter of the aluminum matrix, and decrease
the lattice parameter mismatch further increasing the resistance of
the Al.sub.3Er to coarsening. Additions of zinc, copper, lithium,
silicon, manganese and nickel provide solid solution and
precipitation strengthening in the aluminum alloys. These
Al.sub.3Er dispersoids are made stronger and more resistant to
coarsening at elevated temperatures by adding suitable alloying
elements such as gadolinium, yttrium, zirconium, titanium, hafnium,
niobium, or combinations thereof that enter Al.sub.3Er in
solution.
[0038] Thulium forms metastable Al.sub.3Tm dispersoids in the
aluminum matrix that are fine and coherent with the aluminum
matrix. The lattice parameters of aluminum and Al.sub.3Tm are close
(0.405 nm and 0.420 nm respectively), indicating there is minimal
driving force for causing growth of the Al.sub.3Tm dispersoids.
This low interfacial energy makes the Al.sub.3Tm dispersoids
thermally stable and resistant to coarsening up to temperatures as
high as about 842.degree. F. (450.degree. C.). Additions of
magnesium in aluminum increase the lattice parameter of the
aluminum matrix, and decrease the lattice parameter mismatch
further increasing the resistance of the Al.sub.3Tm to coarsening.
Additions of zinc, copper, lithium, silicon, manganese and nickel
provide solid solution and precipitation strengthening in the
aluminum alloys. These Al.sub.3Tm dispersoids are made stronger and
more resistant to coarsening at elevated temperatures by adding
suitable alloying elements such as gadolinium, yttrium, zirconium,
titanium, hafnium, niobium, or combinations thereof that enter
Al.sub.3Tm in solution.
[0039] Ytterbium forms Al.sub.3Yb dispersoids in the aluminum
matrix that are fine and coherent with the aluminum matrix. The
lattice parameters of Al and Al.sub.3Yb are close (0.405 nm and
0.420 nm respectively), indicating there is minimal driving force
for causing growth of the Al.sub.3Yb dispersoids. This low
interfacial energy makes the Al.sub.3Yb dispersoids thermally
stable and resistant to coarsening up to temperatures as high as
about 842.degree. F. (450.degree. C.). Additions of magnesium in
aluminum increase the lattice parameter of the aluminum matrix, and
decrease the lattice parameter mismatch further increasing the
resistance of the Al.sub.3Yb to coarsening. Additions of zinc,
copper, lithium, silicon, manganese and nickel provide solid
solution and precipitation strengthening in the aluminum alloys.
These Al.sub.3Yb dispersoids are made stronger and more resistant
to coarsening at elevated temperatures by adding suitable alloying
elements such as gadolinium, yttrium, zirconium, titanium, hafnium,
niobium, or combinations thereof that enter Al.sub.3Yb in
solution.
[0040] Lutetium forms Al.sub.3Lu dispersoids in the aluminum matrix
that are fine and coherent with the aluminum matrix. The lattice
parameters of Al and Al.sub.3Lu are close (0.405 nm and 0.419 nm
respectively), indicating there is minimal driving force for
causing growth of the Al.sub.3Lu dispersoids. This low interfacial
energy makes the Al.sub.3Lu dispersoids thermally stable and
resistant to coarsening up to temperatures as high as about
842.degree. F. (450.degree. C.). Additions of magnesium in aluminum
increase the lattice parameter of the aluminum matrix, and decrease
the lattice parameter mismatch further increasing the resistance of
the Al.sub.3Lu to coarsening. Additions of zinc, copper, lithium,
silicon, manganese and nickel provide solid solution and
precipitation strengthening in the aluminum alloys. These
Al.sub.3Lu dispersoids are made stronger and more resistant to
coarsening at elevated temperatures by adding suitable alloying
elements such as gadolinium, yttrium, zirconium, titanium, hafnium,
niobium, or mixtures thereof that enter Al.sub.3Lu in solution.
[0041] Gadolinium forms metastable Al.sub.3Gd dispersoids in the
aluminum matrix that are stable up to temperatures as high as about
842.degree. F. (450.degree. C.) due to their low diffusivity in
aluminum. The Al.sub.3Gd dispersoids have a D0.sub.19 structure in
the equilibrium condition. Despite its large atomic size,
gadolinium has fairly high solubility in the Al.sub.3X
intermetallic dispersoids (where X is scandium, erbium, thulium,
ytterbium or lutetium). Gadolinium can substitute for the X atoms
in Al.sub.3X intermetallic, thereby forming an ordered L1.sub.2
phase which results in improved thermal and structural
stability.
[0042] Yttrium forms metastable Al.sub.3Y dispersoids in the
aluminum matrix that have an L1.sub.2 structure in the metastable
condition and a D0.sub.19 structure in the equilibrium condition.
The metastable Al.sub.3Y dispersoids have a low diffusion
coefficient, which makes them thermally stable and highly resistant
to coarsening. Yttrium has a high solubility in the Al.sub.3X
intermetallic dispersoids allowing large amounts of yttrium to
substitute for X in the Al.sub.3X L1.sub.2 dispersoids, which
results in improved thermal and structural stability.
[0043] Zirconium forms Al.sub.3Zr dispersoids in the aluminum
matrix that have an L1.sub.2 structure in the metastable condition
and D0.sub.23 structure in the equilibrium condition. The
metastable Al.sub.3Zr dispersoids have a low diffusion coefficient,
which makes them thermally stable and highly resistant to
coarsening. Zirconium has a high solubility in the Al.sub.3X
dispersoids allowing large amounts of zirconium to substitute for X
in the Al.sub.3X dispersoids, which results in improved thermal and
structural stability.
[0044] Titanium forms Al.sub.3Ti dispersoids in the aluminum matrix
that have an L1.sub.2 structure in the metastable condition and
D0.sub.22 structure in the equilibrium condition. The metastable
Al.sub.3Ti despersoids have a low diffusion coefficient, which
makes them thermally stable and highly resistant to coarsening.
Titanium has a high solubility in the Al.sub.3X dispersoids
allowing large amounts of titanium to substitute for X in the
Al.sub.3X dispersoids, which result in improved thermal and
structural stability.
[0045] Hafnium forms metastable Al.sub.3Hf dispersoids in the
aluminum matrix that have an L1.sub.2 structure in the metastable
condition and a D0.sub.23 structure in the equilibrium condition.
The Al.sub.3Hf dispersoids have a low diffusion coefficient, which
makes them thermally stable and highly resistant to coarsening.
Hafnium has a high solubility in the Al.sub.3X dispersoids allowing
large amounts of hafnium to substitute for scandium, erbium,
thulium, ytterbium, and lutetium in the above-mentioned Al.sub.3X
dispersoids, which results in stronger and more thermally stable
dispersoids.
[0046] Niobium forms metastable Al.sub.3Nb dispersoids in the
aluminum matrix that have an L1.sub.2 structure in the metastable
condition and a D0.sub.22 structure in the equilibrium condition.
Niobium has a lower solubility in the Al.sub.3X dispersoids than
hafnium or yttrium, allowing relatively lower amounts of niobium
than hafnium or yttrium to substitute for X in the Al.sub.3X
dispersoids. Nonetheless, niobium can be very effective in slowing
down the coarsening kinetics of the Al.sub.3X dispersoids because
the Al.sub.3Nb dispersoids are thermally stable. The substitution
of niobium for X in the above mentioned Al.sub.3X dispersoids
results in stronger and more thermally stable dispersoids.
[0047] Al.sub.3X L1.sub.2 precipitates improve elevated temperature
mechanical properties in aluminum alloys for two reasons. First,
the precipitates are ordered intermetallic compounds. As a result,
when the particles are sheared by glide dislocations during
deformation, the dislocations separate into two partial
dislocations separated by an anti-phase boundary on the glide
plane. The energy to create the anti-phase boundary is the origin
of the strengthening. Second, the cubic L1.sub.2 crystal structure
and lattice parameter of the precipitates are closely matched to
the aluminum solid solution matrix. This results in a lattice
coherency at the precipitate/matrix boundary that resists
coarsening. The lack of an interphase boundary results in a low
driving force for particle growth and resulting elevated
temperature stability. Alloying elements in solid solution in the
dispersed strengthening particles and in the aluminum matrix that
tend to decrease the lattice mismatch between the matrix and
particles will tend to increase the strengthening and elevated
temperature stability of the alloy.
[0048] L1.sub.2 phase strengthened aluminum alloys are important
structural materials because of their excellent mechanical
properties and the stability of these properties at elevated
temperature due to the resistance of the coherent dispersoids in
the microstructure to particle coarsening. The mechanical
properties are optimized by maintaining a high volume fraction of
L1.sub.2 dispersoids in the microstructure. The L1.sub.2 dispersoid
concentration following aging scales as the amount of L1.sub.2
phase forming elements in solid solution in the aluminum alloy
following quenching. Examples of L1.sub.2 phase forming elements
include but are not limited to Sc, Er, Th, Yb, and Lu. The
concentration of alloying elements in solid solution in alloys
cooled from the melt is directly proportional to the cooling
rate.
[0049] Exemplary aluminum alloys for this invention include, but
are not limited to (in weight percent unless otherwise
specified):
[0050] about Al-M-(0.1-4)Sc-(0.1-20)Gd;
[0051] about Al-M-(0.1-20)Er-(0.1-20)Gd;
[0052] about Al-M-(0.1-15)Tm-(0.1-20)Gd;
[0053] about Al-M-(0.1-25)Yb-(0.1-20)Gd;
[0054] about Al-M-(0.1-25)Lu-(0.1-20)Gd;
[0055] about Al-M-(0.1-4)Sc-(0.1-20)Y;
[0056] about Al-M-(0.1-20)Er-(0.1-20)Y;
[0057] about Al-M-(0.1-15)Tm-(0.1-20)Y;
[0058] about Al-M-(0.1-25)Yb-(0.1-20)Y;
[0059] about Al-M-(0.1-25)Lu-(0.1-20)Y;
[0060] about Al-M-(0.1-4)Sc-(0.05-4)Zr;
[0061] about Al-M-(0.1-20)Er-(0.05-4)Zr;
[0062] about Al-M-(0.1-15)Tm-(0.05-4)Zr;
[0063] about Al-M-(0.1-25)Yb-(0.05-4)Zr;
[0064] about Al-M-(0.1-25)Lu-(0.05-4)Zr;
[0065] about Al-M-(0.1-4)Sc-(0.05-10)Ti;
[0066] about Al-M-(0.1-20)Er-(0.05-10)Ti;
[0067] about Al-M-(0.1-15)Tm-(0.05-10)Ti;
[0068] about Al-M-(0.1-25)Yb-(0.05-10)Ti;
[0069] about Al-M-(0.1-25)Lu-(0.05-10)Ti;
[0070] about Al-M-(0.1-4)Sc-(0.05-10)Hf;
[0071] about Al-M-(0.1-20)Er-(0.05-10)Hf;
[0072] about Al-M-(0.1-15)Tm-(0.05-10)Hf;
[0073] about Al-M-(0.1-25)Yb-(0.05-10)Hf;
[0074] about Al-M-(0.1-25)Lu-(0.05-10)Hf;
[0075] about Al-M-(0.1-4)Sc-(0.05-5)Nb;
[0076] about Al-M-(0.1-20)Er-(0.05-5)Nb;
[0077] about Al-M-(0.1-15)Tm-(0.05-5)Nb;
[0078] about Al-M-(0.1-25)Yb-(0.05-5)Nb; and
[0079] about Al-M-(0.1-25)Lu-(0.05-5)Nb.
[0080] M is at least one of about (4-25) weight percent silicon,
(1-8) weight percent magnesium, (0.1-3) weight percent manganese,
(0.5-3) weight percent lithium, (0.2-6) weight percent copper,
(3-12) weight percent zinc, and (1-12) weight percent nickel.
[0081] The amount of silicon present in the fine grain matrix, if
any, may vary from about 4 to about 25 weight percent, more
preferably from about 5 to about 20 weight percent, and even more
preferably from about 6 to about 14 weight percent.
[0082] The amount of magnesium present in the fine grain matrix, if
any, may vary from about 1 to about 8 weight percent, more
preferably from about 3 to about 7.5 weight percent, and even more
preferably from about 4 to about 6.5 weight percent.
[0083] The amount of manganese present in the fine grain matrix, if
any, may vary from about 0.1 to about 3 weight percent, more
preferably from about 0.2 to about 2 weight percent, and even more
preferably from about 0.3 to about 1 weight percent.
[0084] The amount of lithium present in the fine grain matrix, if
any, may vary from about 0.5 to about 3 weight percent, more
preferably from about 1 to about 2.5 weight percent, and even more
preferably from about 1 to about 2 weight percent.
[0085] The amount of copper present in the fine grain matrix, if
any, may vary from about 0.2 to about 6 weight percent, more
preferably from about 0.5 to about 5 weight percent, and even more
preferably from about 2 to about 4.5 weight percent.
[0086] The amount of zinc present in the fine grain matrix, if any,
may vary from about 3 to about 12 weight percent, more preferably
from about 4 to about 10 weight percent, and even more preferably
from about 5 to about 9 weight percent.
[0087] The amount of nickel present in the fine grain matrix, if
any, may vary from about 1 to about 12 weight percent, more
preferably from about 2 to about 10 weight percent, and even more
preferably from about 4 to about 10 weight percent.
[0088] The amount of scandium present in the fine grain matrix, if
any, may vary from 0.1 to about 4 weight percent, more preferably
from about 0.1 to about 3 weight percent, and even more preferably
from about 0.2 to about 2.5 weight percent. The Al--Sc phase
diagram shown in FIG. 1 indicates a eutectic reaction at about 0.5
weight percent scandium at about 1219.degree. F. (659.degree. C.)
resulting in a solid solution of scandium and aluminum and
Al.sub.3Sc dispersoids. Aluminum alloys with less than 0.5 weight
percent scandium can be quenched from the melt to retain scandium
in solid solution that may precipitate as dispersed L1.sub.2
intermetallic Al.sub.3Sc following an aging treatment. Alloys with
scandium in excess of the eutectic composition (hypereutectic
alloys) can only retain scandium in solid solution by rapid
solidification processing (RSP) where cooling rates are in excess
of about 10.sup.3.degree. C./second.
[0089] The amount of erbium present in the fine grain matrix, if
any, may vary from about 0.1 to about 20 weight percent, more
preferably from about 0.3 to about 15 weight percent, and even more
preferably from about 0.5 to about 10 weight percent. The Al--Er
phase diagram shown in FIG. 2 indicates a eutectic reaction at
about 6 weight percent erbium at about 1211.degree. F. (655.degree.
C.). Aluminum alloys with less than about 6 weight percent erbium
can be quenched from the melt to retain erbium in solid solutions
that may precipitate as dispersed L1.sub.2 intermetallic Al.sub.3Er
following an aging treatment. Alloys with erbium in excess of the
eutectic composition can only retain erbium in solid solution by
rapid solidification processing (RSP) where cooling rates are in
excess of about 10.sup.3.degree. C./second.
[0090] The amount of thulium present in the alloys, if any, may
vary from about 0.1 to about 15 weight percent, more preferably
from about 0.2 to about 10 weight percent, and even more preferably
from about 0.4 to about 6 weight percent. The Al--Tm phase diagram
shown in FIG. 3 indicates a eutectic reaction at about 10 weight
percent thulium at about 1193.degree. F. (645.degree. C.). Thulium
forms metastable Al.sub.3Tm dispersoids in the aluminum matrix that
have an L1.sub.2 structure in the equilibrium condition. The
Al.sub.3Tm dispersoids have a low diffusion coefficient, which
makes them thermally stable and highly resistant to coarsening.
Aluminum alloys with less than 10 weight percent thulium can be
quenched from the melt to retain thulium in solid solution that may
precipitate as dispersed metastable L1.sub.2 intermetallic
Al.sub.3Tm following an aging treatment. Alloys with thulium in
excess of the eutectic composition can only retain Tm in solid
solution by rapid solidification processing (RSP) where cooling
rates are in excess of about 10.sup.3.degree. C./second.
[0091] The amount of ytterbium present in the alloys, if any, may
vary from about 0.1 to about 25 weight percent, more preferably
from about 0.3 to about 20 weight percent, and even more preferably
from about 0.4 to about 10 weight percent. The Al--Yb phase diagram
shown in FIG. 4 indicates a eutectic reaction at about 21 weight
percent ytterbium at about 1157.degree. F. (625.degree. C.).
Aluminum alloys with less than about 21 weight percent ytterbium
can be quenched from the melt to retain ytterbium in solid solution
that may precipitate as dispersed L1.sub.2 intermetallic Al.sub.3Yb
following an aging treatment. Alloys with ytterbium in excess of
the eutectic composition can only retain ytterbium in solid
solution by rapid solidification processing (RSP) where cooling
rates are in excess of about 10.sup.3.degree. C./second.
[0092] The amount of lutetium present in the alloys, if any, may
vary from about 0.1 to about 25 weight percent, more preferably
from about 0.3 to about 20 weight percent, and even more preferably
from about 0.4 to about 10 weight percent. The Al--Lu phase diagram
shown in FIG. 5 indicates a eutectic reaction at about 11.7 weight
percent Lu at about 1202.degree. F. (650.degree. C.). Aluminum
alloys with less than about 11.7 weight percent lutetium can be
quenched from the melt to retain Lu in solid solution that may
precipitate as dispersed L1.sub.2 intermetallic Al.sub.3Lu
following an aging treatment. Alloys with Lu in excess of the
eutectic composition can only retain Lu in solid solution by rapid
solidification processing (RSP) where cooling rates are in excess
of about 10.sup.3.degree. C./second.
[0093] The amount of gadolinium present in the alloys, if any, may
vary from about 0.1 to about 20 weight percent, more preferably
from about 0.3 to about 15 weight percent, and even more preferably
from about 0.5 to about 10 weight percent.
[0094] The amount of yttrium present in the alloys, if any, may
vary from about 0.1 to about 20 weight percent, more preferably
from about 0.3 to about 15 weight percent, and even more preferably
from about 0.5 to about 10 weight percent.
[0095] The amount of zirconium present in the alloys, if any, may
vary from about 0.05 to about 4 weight percent, more preferably
from about 0.1 to about 3 weight percent, and even more preferably
from about 0.3 to about 2 weight percent.
[0096] The amount of titanium present in the alloys, if any, may
vary from about 0.05 to about 10 weight percent, more preferably
from about 0.2 to about 8 weight percent, and even more preferably
from about 0.4 to about 4 weight percent.
[0097] The amount of hafnium present in the alloys, if any, may
vary from about 0.05 to about 10 weight percent, more preferably
from about 0.2 to about 8 weight percent, and even more preferably
from about 0.4 to about 5 weight percent.
[0098] The amount of niobium present in the alloys, if any, may
vary from about 0.05 to about 5 weight percent, more preferably
from about 0.1 to about 3 weight percent, and even more preferably
from about 0.2 to about 2 weight percent.
[0099] In order to have the best properties for the fine grain
matrix, it is desirable to limit the amount of other elements.
Specific elements that should be reduced or eliminated include no
more than about 0.1 weight percent iron, 0.1 weight percent
chromium, 0.1 weight percent vanadium, and 0.1 weight percent
cobalt. The total quantity of additional elements should not exceed
about 1% by weight, including the above listed impurities and other
elements.
2. L1.sub.2 Alloy Powder Formation and Consolidation
[0100] The highest cooling rates observed in commercially viable
processes are achieved by gas atomization of molten metals to
produce powder. Gas atomization is a two fluid process wherein a
stream of molten metal is disintegrated by a high velocity gas
stream. The end result is that the particles of molten metal
eventually become spherical due to surface tension and finely
solidify in powder form. Heat from the liquid droplets is
transferred to the atomization gas by convection. The
solidification rates, depending on the gas and the surrounding
environment, can be very high and can exceed 10.sup.6.degree.
C./second. Cooling rates greater than 10.sup.3.degree. C./second
are typically specified to ensure supersaturation of alloying
elements in gas atomized L1.sub.2 aluminum alloy powder in the
inventive process described herein.
[0101] A schematic of typical vertical gas atomizer 100 is shown in
FIG. 6A. FIG. 6A is taken from R. Germain, Powder Metallurgy
Science Second Edition MPIF (1994) (chapter 3, p. 101) and is
included herein for reference. Vacuum or inert gas induction melter
102 is positioned at the top of free flight chamber 104. Vacuum
induction melter 102 contains melt 106 which flows by gravity or
gas overpressure through nozzle 108. A close up view of nozzle 108
is shown in FIG. 6B. Melt 106 enters nozzle 108 and flows downward
till it meets the high pressure gas stream from gas source 110
where it is transformed into a spray of droplets. The droplets
eventually become spherical due to surface tension and rapidly
solidify into spherical powder 112 which collects in collection
chamber 114. The gas recirculates through cyclone collector 116
which collects fine powder 118 before returning to the input gas
stream. As can be seen from FIG. 6A, the surroundings to which the
melt and eventual powder are exposed are completely controlled.
[0102] There are many effective nozzle designs known in the art to
produce spherical metal powder. Designs with short gas-to-melt
separation distances produce finer powders. Confined nozzle designs
where gas meets the molten stream at a short distance just after it
leaves the atomization nozzle are preferred for the production of
the inventive L1.sub.2 aluminum alloy powders disclosed herein.
Higher superheat temperatures cause lower melt viscosity and longer
cooling times. Both result in smaller spherical particles.
[0103] A large number of processing parameters are associated with
gas atomization that affect the final product. Examples include
melt superheat, gas pressure, metal flow rate, gas type, and gas
purity. In gas atomization, the particle size is related to the
energy input to the metal. Higher gas pressures, higher superheat
temperatures and lower metal flow rates result in smaller particle
sizes. Higher gas pressures provide higher gas velocities for a
given atomization nozzle design.
[0104] To maintain purity, inert gases are used, such as helium,
argon, and nitrogen. Helium is preferred for rapid solidification
because the high heat transfer coefficient of the gas leads to high
quenching rates and high supersaturation of alloying elements.
[0105] Lower metal flow rates and higher gas flow ratios favor
production of finer powders. The particle size of gas atomized
melts typically has a log normal distribution. In the turbulent
conditions existing at the gas/metal interface during atomization,
ultra fine particles can form that may reenter the gas expansion
zone. These solidified fine particles can be carried into the
flight path of molten larger droplets resulting in agglomeration of
small satellite particles on the surfaces of larger particles. An
example of small satellite particles attached to inventive
spherical L1.sub.2 aluminum alloy powder is shown in the scanning
electron microscopy (SEM) micrographs of FIGS. 7A and 7B at two
magnifications. The spherical shape of gas atomized aluminum powder
is evident. The spherical shape of the powder is suggestive of
clean powder without excessive oxidation. Higher oxygen in the
powder results in irregular powder shape. Spherical powder helps in
improving the flowability of powder which results in higher
apparent density and tap density of the powder. The satellite
particles can be minimized by adjusting processing parameters to
reduce or even eliminate turbulence in the gas atomization process.
The microstructure of gas atomized aluminum alloy powder is
predominantly cellular as shown in the optical micrographs of
cross-sections of the inventive alloy in FIGS. 8A and 8B at two
magnifications. The rapid cooling rate suppresses dendritic
solidification common at slower cooling rates resulting in a finer
microstructure with minimum alloy segregation.
[0106] Oxygen and hydrogen in the powder can degrade the mechanical
properties of the final part. It is preferred to limit the oxygen
in the L1.sub.2 alloy powder to about 1 ppm to 2000 ppm. Oxygen is
intentionally introduced as a component of the helium gas during
atomization. An oxide coating on the L1.sub.2 aluminum powder is
beneficial for two reasons. First, the coating prevents
agglomeration by contact sintering and secondly, the coating
inhibits the chance of explosion of the powder. A controlled amount
of oxygen is important in order to provide good ductility and
fracture toughness in the final consolidated material. Hydrogen
content in the powder is controlled by ensuring the dew point of
the helium gas is low. A dew point of about minus 50.degree. F.
(minus 45.5.degree. C.) to minus 100.degree. F. (minus 73.3.degree.
C.) is preferred.
[0107] In preparation for final processing, the powder is
classified according to size by sieving. To prepare the powder for
sieving, if the powder has zero percent oxygen content, the powder
may be exposed to nitrogen gas which passivates the powder surface
and prevents agglomeration. Finer powder sizes result in improved
mechanical properties of the end product. While minus 325 mesh
(about 45 microns) powder can be used, minus 450 mesh (about 30
microns) powder is a preferred size in order to provide good
mechanical properties in the end product. During the atomization
process, powder is collected in collection chambers in order to
prevent oxidation of the powder. Collection chambers are used at
the bottom of atomization chamber 104 as well as at the bottom of
cyclone collector 116. The powder is transported and stored in the
collection chambers also. Collection chambers are maintained under
positive pressure with nitrogen gas which prevents oxidation of the
powder.
[0108] A schematic of the L1.sub.2 aluminum powder manufacturing
process is shown in FIG. 9. In the process aluminum 200 and L12
forming (and other alloying) elements 210 are melted in furnace 220
to a predetermined superheat temperature under vacuum or inert
atmosphere. Preferred charge for furnace 220 is prealloyed aluminum
200 and L1.sub.2 and other alloying elements before charging
furnace 220. Melt 230 is then passed through nozzle 240 where it is
impacted by pressurized gas stream 250. Gas stream 250 is an inert
gas such as nitrogen, argon or helium, preferably helium. Melt 230
can flow through nozzle 240 under gravity or under pressure.
Gravity flow is preferred for the inventive process disclosed
herein. Preferred pressures for pressurized gas stream 250 are
about 50 psi (10.35 MPa) to about 750 psi (5.17 MPa) depending on
the alloy.
[0109] The atomization process creates molten droplets 260 which
rapidly solidify as they travel through agglomeration chamber 270
forming spherical powder particles 280. The molten droplets
transfer heat to the atomizing gas by convention. The role of the
atomizing gas is two fold: one is to disintegrate the molten metal
stream into fine droplets by transferring kinetic energy from the
gas to the melt stream and the other is to extract heat from the
molten droplets to rapidly solidify them into spherical powder. The
solidification time and cooling rate vary with droplet size. Larger
droplets take longer to solidify and their resulting cooling rate
is lower. On the other hand, the atomizing gas will extract heat
efficiently from smaller droplets resulting in a higher cooling
rate. Finer powder size is therefore preferred as higher cooling
rates provide finer microstructures and higher mechanical
properties in the end product. Higher cooling rates lead to finer
cellular microstructures which are preferred for higher mechanical
properties. Finer cellular microstructures result in finer grain
sizes in consolidated product. Finer grain size provides higher
yield strength of the material through the Hall-Petch strengthening
model.
[0110] Key process variables for gas atomization include superheat
temperature, nozzle diameter, helium content and dew point of the
gas, and metal flow rate. Superheat temperatures of from about
150.degree. F. (66.degree. C.) to 200.degree. F. (93.degree. C.)
are preferred. Nozzle diameters of about 0.07 in. (1.8 mm) to 0.12
in. (3.0 mm) are preferred depending on the alloy. The gas stream
used herein was a helium nitrogen mixture containing 74 to 87 vol.
% helium. The metal flow rate ranged from about 0.8 lb/min (0.36
kg/min) to 4.0 lb/min (1.81 kg/min). The oxygen content of the
L1.sub.2 aluminum alloy powders was observed to consistently
decrease as a run progressed. This is suggested to be the result of
the oxygen gettering capability of the aluminum powder in a closed
system. The dew point of the gas was controlled to minimize
hydrogen content of the powder. Dew points in the gases used in the
examples ranged from -10.degree. F. (-23.degree. C.) to
-110.degree. F. (-79.degree. C.).
[0111] The powder is then classified by sieving process 290 to
create classified powder 300. Sieving of powder is performed under
an inert environment to minimize oxygen and hydrogen pickup from
the environment. While the yield of minus 450 mesh powder is
extremely high (95%), there are always larger particle sizes,
flakes and ligaments that are removed by the sieving. Sieving also
ensures a narrow size distribution and provides a more uniform
powder size. Sieving also ensures that flaw sizes cannot be greater
than minus 450 mesh which will be required for nondestructive
inspection of the final product.
[0112] Processing parameters of exemplary gas atomization runs are
listed in Table 1.
TABLE-US-00001 TABLE 1 Gas atomization parameters used for
producing powder Average Oxygen Oxygen Nozzle He Gas Dew Charge
Metal Content Content Diameter Content Pressure Point Temperature
Flow Rate (ppm) (ppm) Run (in) (vol %) (psi) (.degree. F.)
(.degree. F.) (lbs/min) Start End 1 0.10 79 190 <-58 2200 2.8
340 35 2 0.10 83 192 -35 1635 0.8 772 27 3 0.09 78 190 -10 2230 1.4
297 <0.01 4 0.09 85 160 -38 1845 2.2 22 4.1 5 0.10 86 207 -88
1885 3.3 286 208 6 0.09 86 207 -92 1915 2.6 145 88
[0113] The role of powder quality is extremely important to produce
material with higher strength and ductility. Powder quality is
determined by powder size, shape, size distribution, oxygen
content, hydrogen content, and alloy chemistry. Over fifty gas
atomization runs were performed to produce the inventive powder
with finer powder size, finer size distribution, spherical shape,
and lower oxygen and hydrogen contents. Processing parameters of
some exemplary gas atomization runs are listed in Table 1. It is
suggested that the observed decrease in oxygen content is
attributed to oxygen gettering by the powder as the runs
progressed.
[0114] Inventive L1.sub.2 aluminum alloy powder was produced with
over 95% yield of minus 450 mesh (30 microns) which includes powder
from about 1 micron to about 30 microns. The average powder size
was about 10 microns to about 15 microns. As noted above, finer
powder size is preferred for higher mechanical properties. Finer
powders have finer cellular microstructures. As a result, finer
cell sizes lead to finer grain size by fragmentation and
coalescence of cells during powder consolidation. Finer grain sizes
produce higher yield strength through the Hall-Petch strengthening
model where yield strength varies inversely as the square root of
the grain size. It is preferred to use powder with an average
particle size of 10-15 microns. Powders with a powder size less
than 10-15 microns can be more challenging to handle due to the
larger surface area of the powder. Powders with sizes larger than
10-15 microns will result in larger cell sizes in the consolidated
product which, in turn, will lead to larger grain sizes and lower
yield strengths.
[0115] Powders with narrow size distributions are preferred.
Narrower powder size distributions produce product microstructures
with more uniform grain size. Spherical powder was produced to
provide higher apparent and tap densities which help in achieving
100% density in the consolidated product. Spherical shape is also
an indication of cleaner and lower oxygen content powder. Lower
oxygen and lower hydrogen contents are important in producing
material with high ductility and fracture toughness. Although it is
beneficial to maintain low oxygen and hydrogen content in powder to
achieve good mechanical properties, lower oxygen may interfere with
sieving due to self sintering. An oxygen content of about 25 ppm to
about 500 ppm is preferred to provide good ductility and fracture
toughness without any sieving issue. Lower hydrogen is also
preferred for improving ductility and fracture toughness. It is
preferred to have about 25-200 ppm of hydrogen in atomized powder
by controlling the dew point in the atomization chamber. Hydrogen
in the powder is further reduced by heating the powder in vacuum.
Lower hydrogen in final product is preferred to achieve good
ductility and fracture toughness.
[0116] A schematic of the L1.sub.2 aluminum powder consolidation
process is shown in FIG. 10. The starting material is sieved and
classified L1.sub.2 aluminum alloy powders (step 310). Blending
(step 320) is a preferred step in the consolidation process because
it results in improved uniformity of particle size distribution.
Gas atomized L1.sub.2 aluminum alloy powder generally exhibits a
bimodal particle size distribution and cross blending of separate
powder batches tends to homogenize the particle size distribution.
Blending (step 320) is also preferred when separate metal and/or
ceramic powders are added to the L1.sub.2 base powder to form
bimodal or trimodal consolidated alloy microstructures.
[0117] Following blending (step 320), the powders are transferred
to a can (step 330) where the powder is vacuum degassed (step 340)
at elevated temperatures. The can (step 330) is an aluminum
container having a cylindrical, rectangular or other configuration
with a central axis. Cylindrical configurations are preferred with
hydraulic extrusion presses. Vacuum degassing times can range from
about 0.5 hours to about 8 days. A temperature range of about
300.degree. F. (149.degree. C.) to about 900.degree. F.
(482.degree. C.) is preferred. Dynamic degassing of large amounts
of powder is preferred to static degassing. In dynamic degassing,
the can is preferably rotated during degassing to expose all of the
powder to a uniform temperature. Degassing removes oxygen and
hydrogen from the powder.
[0118] Following vacuum degassing (step 340), the vacuum line is
crimped and welded shut (step 350). The powder is then fully
densified by blind die compaction or closed die forging as the
process is sometimes called (step 360). At this point the can may
be removed by machining (step 380) to form a useful billet (step
390).
[0119] A schematic showing blind die compaction (process 400) is
shown in FIGS. 11A and 11B. The equipment comprises base 410, die
420, ram 430, and means to apply pressure to ram 430 indicated by
arrow 450. Prior to compaction, billet 440 does not fill die cavity
460. After compaction, billet 445 completely fills the die cavity
and has taken the shape of die cavity 460. The die cavities can
have any shape provided they have a central symmetrical axis
parallel to arrow 450. Cylindrical shapes adopt well for extrusion
billets. Canned L1.sub.2 aluminum alloy powder preforms are easily
densified due to the large capacity of modern hydraulic
presses.
[0120] FIG. 12 is a perspective view of a direct extrusion process.
In the process, a billet of, in this case, L1.sub.2 aluminum alloy
is extruded through a die having a cavity with a shape necessary to
produce a cross-sectional profile of the final part. The components
of extrusion process 500 are illustrated on the FIG. and comprise
container 510, container liner 520, and ram 540 with dummy block
550. Dummy block 550 isolates billet 530 from direct contact with
ram 540 during extrusion. During extrusion, billet 530 is forced
through opening (s) in die 560 by pressure on ram 540. Ram 540 can
be mechanically or hydraulically actuated. Hydraulic extrusion
presses are preferred for higher pressure operation. During
extrusion, die 560 is held in place against the ram pressure by die
backer 570. Other forms of extrusion are indirect extrusion,
hydrostatic extrusion, lateral extrusion, and others known to those
in the art.
[0121] An almost unlimited number of cross-sectional shapes of
extrusions can be achieved. Extrusion 580 in FIG. 12 has a simple
circular cross-section. FIG. 13 shows examples of other common
shapes. FIG. 13A is an example of how a bracket can be fabricated
from an extrusion. FIG. 13B is an example of a gear. FIG. 13C is
another exemplary shape. FIGS. 13B and 13C have hollow shapes and
are formed by the process of hollow die extrusion. During
extrusions, to produce parts with hollow cross-sections, the
L1.sub.2 aluminum alloy is divided during extrusion in port
sections of a first (interior) hollow die into a plurality of
portions, which are again joined (welded) to each other in a second
(exterior) die with a welding chamber section, to form a welded
portion, thereby producing a hollow section having a complicated
profile.
[0122] A perspective representation of hollow die system 600 used
to form a rectangular tube is shown in FIG. 14. The die system
comprises internal die 660 and external die 665. Internal die 660
contains a plurality of inlet ports 620 and internal bearing 630.
When assembled, internal bearing 630 fits inside external bearing
635 such that there is clearance between bearing wall 640 of
internal bearing 630 and bearing wall 645 of external bearing 635.
During extrusion, L1.sub.2 alloy billet 610 is forced in direction
of arrow 615 in a container (not shown) by a ram (not shown) such
that the alloy is forced to flow through port (s) 620 such that it
flows around internal bearing 630. The metal rejoins in welding
chamber 665 and flows through the gap between internal bearing 630
and external bearing 635 and is formed into rectangular hollow
extrusion 670 with dimensions formed by bearing surfaces 640 and
645. Die 660 (shown) is termed a porthole die. Other dies used to
form extrusions with hollow features are spider and bridge dies and
others known to those in the art.
[0123] L1.sub.2 aluminum alloy parts useful for turbine and rocket
engine applications can be rapidly and efficiently made by direct
extrusion including brackets, cases, tubes, ducts, beams,
spars.
TABLE-US-00002 TABLE 2 Effect of compaction and extrusion
parameters on extruded L1.sub.2 Al alloys duct Ultimate Compaction
Extrusion Extrusion Tensile Temperature, Temperature, Extrusion
Speed, Strength, 0.2% Yield Elongation, Reduction Billet ID F. F.
Ratio ipm ksi Strength, ksi % in Area, % 1 750 700 10:01 0.5 115.0
104.0 9.0 18.5 2 750 650 10:01 0.5 114.0 103.0 6.5 12.0 3 750 650
6:01 0.5 117.0 107.0 7.5 15.0 4 750 600 10:01 3 112.0 10.4.0 6.5
12.5 5 750 700 15:01 3 105.0 96.0 10.0 20.0 6 750 550 10:01 3 112.0
102.0 7.5 12.0 7 750 500 10:01 3 118.0 108.0 8.0 16.0
Extrusion parameters including extrusion temperature, billet
soaking time, extrusion ratio and extrusion speed have significant
influence on mechanical properties of L1.sub.2 aluminum alloy duct.
Billet soaking time was kept constant at 1.5 hours for all these
billets. These billets were compacted at 750 F using vacumm hot
pressing resulting in 100% dense billets which were extruded to
produce ducts. Lower extrusion temperature of 500 F at ratio of
10:1 and speed of 3 inch per minute resulted in 118 ksi tensile
strength, 8% elongation and 16% reduction in area. Higher extrusion
temperature of 700 F at ratio of 10:1 and speed of 0.5 inch per
minute resulted in 115 ksi tensile strength, 9% elongation and
18.5% reduction in area. In other example, extrusion temperature of
650 F at ratio of 6:1 and speed of 0.5 inch per minute resulted in
117 ksi tensile strength, about 7.5% elongation and 15% reduction
in area. In other example, extrusion temperature of 700 F, ratio of
15:1 and speed of 3:1 resulted in 105 ksi tensile strength, 10%
elongation and 20% reduction in area. A number of examples of
extrusion demonstrated excellent tensile properties with about
105-120 ksi tensile strength and ductility in terms of reduction in
area of about 10 to 20%. These examples suggest that a unique
combination of extrusion parameters that have been developed in the
present invention can lead to a good combination of tensile
strength and ductility for L1.sub.2 aluminum alloys ducts and that
can be applied to other extruded products also including brackets,
cases, tubes, beams, spars.
[0124] Extrusions when carried at very high speeds can result in
reduced strength and higher ductility due to adiabatic heating
generated during extrusion. Higher the speed larger the adiabatic
heat generated due to friction during extrusion. Therefore higher
speed is not preferred from strength point of view. Higher speed is
preferred from cost point of view since more number of components
can be produced in same amount of time. Slower speeds do not
produce adiabatic heat and therefore preferred for higher strength
extrusions. Slower the speed less adiabatic heat is produced.
However, below certain speed extrusion becomes uneconomical and
therefore it is not preferred to use too low extrusion speed. Based
on all the results produced, extrusion speed of about 0.1 inch per
minute to about 20 inch per minute is preferred for present
inventive L1.sub.2 aluminum alloys based on balanced mechanical
properties resulting in good combination of strength and
ductility.
[0125] A photograph of a duct produced for a jet engine is shown in
FIG. 15. Products such as this are a significant improvement in the
industry.
[0126] Although the present invention has been described with
reference to preferred embodiments, workers skilled in the art will
recognize that changes may be made in form and detail without
departing from the spirit and scope of the invention.
* * * * *