U.S. patent application number 15/219812 was filed with the patent office on 2018-02-01 for powdered titanium alloy composition and article formed therefrom.
The applicant listed for this patent is The Boeing Company. Invention is credited to Gary M. Backhaus, Robert Burkett, Michael S. Carr, Ryan J. Glamm, Joseph Pecina.
Application Number | 20180029131 15/219812 |
Document ID | / |
Family ID | 61011977 |
Filed Date | 2018-02-01 |
United States Patent
Application |
20180029131 |
Kind Code |
A1 |
Pecina; Joseph ; et
al. |
February 1, 2018 |
Powdered Titanium Alloy Composition and Article Formed
Therefrom
Abstract
A titanium alloy composition that includes, other than
impurities, about 7.0 to about 9.0 percent by weight vanadium (V),
about 3.0 to about 4.5 percent by weight aluminum (Al), about 0.8
to about 1.5 percent by weight iron (Fe), about 0.14 to about 0.22
percent by weight oxygen (O), optionally about 0.8 to about 2.4
percent by weight chromium (Cr), and the balance titanium.
Inventors: |
Pecina; Joseph; (Lynnwood,
WA) ; Burkett; Robert; (Everett, WA) ;
Backhaus; Gary M.; (Lake Stevens, WA) ; Carr; Michael
S.; (Clinton, WA) ; Glamm; Ryan J.; (Seattle,
WA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
The Boeing Company |
Chicago |
IL |
US |
|
|
Family ID: |
61011977 |
Appl. No.: |
15/219812 |
Filed: |
July 26, 2016 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
C22C 1/0458 20130101;
B22F 3/02 20130101; B22F 2003/248 20130101; B22F 3/10 20130101;
B22F 3/15 20130101; C22F 1/183 20130101; B22F 2998/10 20130101;
C22C 14/00 20130101; B22F 2998/10 20130101 |
International
Class: |
B22F 3/16 20060101
B22F003/16; B22F 3/24 20060101 B22F003/24; B22F 1/00 20060101
B22F001/00; B22F 3/15 20060101 B22F003/15; C22F 1/18 20060101
C22F001/18; C22C 14/00 20060101 C22C014/00 |
Claims
1. A titanium alloy consisting essentially of: about 7.0 to about
9.0 percent by weight vanadium; about 3.0 to about 4.5 percent by
weight aluminum; about 0.8 to about 1.5 percent by weight iron;
about 0.14 to about 0.22 percent by weight oxygen; optionally about
0.8 to about 2.4 percent by weight chromium; and balance
titanium.
2. The titanium alloy of claim 1 wherein said vanadium is present
at about 7.0 to about 8.5 percent by weight.
3. The titanium alloy of claim 1 wherein said vanadium is present
at about 7.5 to about 9.0 percent by weight.
4. The titanium alloy of claim 1 wherein said aluminum is present
at about 3.5 to about 4.5 percent by weight.
5. The titanium alloy of claim 1 wherein said aluminum is present
at about 3.0 to about 4.0 percent by weight.
6. The titanium alloy of claim 1 wherein said iron is present at
about 0.9 to about 1.5 percent by weight.
7. The titanium alloy of claim 1 wherein said iron is present at
about 0.8 to about 1.3 percent by weight.
8. The titanium alloy of claim 1 wherein said oxygen is present at
about 0.15 to about 0.22 percent by weight.
9. The titanium alloy of claim 1 wherein said oxygen is present at
about 0.14 to about 0.20 percent by weight.
10. The titanium alloy of claim 1 wherein said chromium is
optionally present at about 1.8 to about 2.4 percent by weight.
11. The titanium alloy of claim 1 wherein: said vanadium is present
at about 7.0 to about 8.5 percent by weight; said aluminum is
present at about 3.5 to about 4.5 percent by weight; said iron is
present at about 0.9 to about 1.5 percent by weight; and said
oxygen is present at about 0.15 to about 0.22 percent by
weight.
12. The titanium alloy of claim 11 wherein said optional chromium
is not present.
13. The titanium alloy of claim 1 wherein: said vanadium is present
at about 7.5 to about 9.0 percent by weight; said aluminum is
present at about 3.0 to about 4.0 percent by weight; said iron is
present at about 0.8 to about 1.3 percent by weight; said oxygen is
present at about 0.14 to about 0.20 percent by weight; and said
chromium is present at about 0.8 to about 2.4 percent by
weight.
14. The titanium alloy of claim 1 in powdered form.
15. The titanium alloy of claim 14 wherein said powdered form
consists of a mixture of at least two different powder
compositions.
16. The titanium alloy of claim 15 wherein said mixture comprises a
titanium powder and a master alloy powder.
17. The titanium alloy of claim 14 wherein said powdered form
consists of a plurality of powder particles, and wherein each
powder particle of said plurality of powder particles has
substantially the same composition.
18. The titanium alloy of claim 14 wherein said powdered form
consists of a plurality of substantially spherical powder
particles.
19. The titanium alloy of claim 18 wherein said plurality of
substantially spherical powder particles have a substantially
uniform particle size.
20. An article formed from the titanium alloy of claim 1.
21. An article formed from the titanium alloy of claim 14.
22. A method for manufacturing an article comprising: compacting
said powdered form titanium alloy of claim 14 to form a shaped
mass; and sintering said shaped mass.
23. The method of claim 22 wherein said compacting comprises metal
injection molding.
24. The method of claim 22 further comprising subjecting said
sintered shaped mass to hot isostatic pressing.
25. The method of claim 22 further comprising solution treating and
aging said sintered shaped mass.
26. The titanium alloy of claim 1 in powdered form and consisting
essentially of: about 7.0 to about 8.5 percent by weight vanadium;
about 3.5 to about 4.5 percent by weight aluminum; about 0.9 to
about 1.5 percent by weight iron; about 0.15 to about 0.22 percent
by weight oxygen; and balance titanium.
27. The titanium alloy composition of claim 26 consisting of a
plurality of powder particles, and wherein each powder particle of
said plurality of powder particles has substantially the same
composition.
28. The titanium alloy composition of claim 26 consisting of a
mixture of at least two different powder compositions.
29. The titanium alloy composition of claim 28 wherein said mixture
comprises a titanium powder and a master alloy powder.
30. An article formed from the titanium alloy composition of claim
26.
31. The titanium alloy of claim 1 in powdered form and consisting
essentially of: about 7.5 to about 9.0 percent by weight vanadium;
about 3.0 to about 4.0 percent by weight aluminum; about 0.8 to
about 2.4 percent by weight chromium; about 0.8 to about 1.3
percent by weight iron; about 0.14 to about 0.20 percent by weight
oxygen; and balance titanium.
32. The titanium alloy composition of claim 31 wherein said
chromium is present at about 1.8 to about 2.4 percent by
weight.
33. The titanium alloy composition of claim 31 consisting of a
plurality of powder particles, and wherein each powder particle of
said plurality of powder particles has substantially the same
composition.
34. The titanium alloy composition of claim 31 consisting of a
mixture of at least two different powder compositions.
35. The titanium alloy composition of claim 34 wherein said mixture
comprises a titanium powder and a master alloy powder.
36. An article formed from the titanium alloy composition of claim
31.
Description
FIELD
[0001] This application generally relates to titanium alloys and,
more particularly, to titanium alloys for powder metallurgy.
BACKGROUND
[0002] Titanium alloys offer high tensile strength over a broad
temperature range, yet are relatively light weight. Ti-6Al-4V is
perhaps the most common and widely used titanium alloy. In wrought
form, Ti-6Al-4V has a relatively low density (about 4.47
g/cm.sup.3), yet exhibits exceptional mechanical properties, such
as a yield strength in excess of 120 ksi (thousand pounds per
square inch), an ultimate tensile strength in excess of 130 ksi, an
elongation of at least 10 percent, and a fatigue limit (10 million
plus cycles) in excess of 90 ksi. Furthermore, titanium alloys are
resistant to corrosion. Therefore, titanium alloys, Ti-6Al-4V
specifically, are used in various demanding applications, such as
aircraft components, medical devices and the like.
[0003] Powder metallurgy manufacturing techniques, such as die
pressing, metal injection molding, direct hot isostatic pressing
and the like, result in the formation of net (or near net)
articles. Therefore, powder metallurgy manufacturing techniques
offer the opportunity for significant cost savings by significantly
reducing (if not completely eliminating) the need for machining
operations, which are time intensive and wasteful of materials.
[0004] Ti-6Al-4V powders are available, and have been formed into
various articles using powder metallurgy manufacturing techniques.
However, articles formed from Ti-6Al-4V powders do not have the
same mechanical properties as articles formed from wrought
Ti-6Al-4V. For example, the fatigue limit of articles formed from
Ti-6Al-4V powders can be 20 to 30 percent less that the fatigue
limit of articles formed from wrought Ti-6Al-4V (e.g., 70 ksi for
powdered versus 95 ksi for wrought). In many applications, such a
significant reduction in the fatigue limit may not be
acceptable.
[0005] Accordingly, those skilled in the art continue with research
and development efforts in the field of titanium alloys.
SUMMARY
[0006] In one embodiment, the disclosed titanium alloy consists
essentially of about 7.0 to about 9.0 percent by weight vanadium
(V), about 3.0 to about 4.5 percent by weight aluminum (Al), about
0.8 to about 1.5 percent by weight iron (Fe), about 0.14 to about
0.22 percent by weight oxygen (O), optionally about 0.8 to about
2.4 percent by weight chromium (Cr), and the balance titanium.
[0007] In another embodiment, the disclosed titanium alloy consists
essentially of about 7.0 to about 8.5 percent by weight vanadium
(V), about 3.5 to about 4.5 percent by weight aluminum (Al), about
0.9 to about 1.5 percent by weight iron (Fe), about 0.15 to about
0.22 percent by weight oxygen (O), and the balance titanium.
[0008] In another embodiment, the disclosed titanium alloy consists
essentially of about 7.5 to about 9.0 percent by weight vanadium
(V), about 3.0 to about 4.0 percent by weight aluminum (Al), about
0.8 to about 1.3 percent by weight iron (Fe), about 0.14 to about
0.20 percent by weight oxygen (O), about 0.8 to about 2.4 percent
by weight chromium (Cr), and the balance titanium.
[0009] In one embodiment, the disclosed powdered titanium alloy
composition consists essentially of about 7.0 to about 9.0 percent
by weight vanadium (V), about 3.0 to about 4.5 percent by weight
aluminum (Al), about 0.8 to about 1.5 percent by weight iron (Fe),
about 0.14 to about 0.22 percent by weight oxygen (O), optionally
about 0.8 to about 2.4 percent by weight chromium (Cr), and the
balance titanium.
[0010] In another embodiment, the disclosed powdered titanium alloy
composition consists essentially of about 7.0 to about 8.5 percent
by weight vanadium (V), about 3.5 to about 4.5 percent by weight
aluminum (Al), about 0.9 to about 1.5 percent by weight iron (Fe),
about 0.15 to about 0.22 percent by weight oxygen (O), and the
balance titanium.
[0011] In another embodiment, the disclosed powdered titanium alloy
composition consists essentially of about 7.5 to about 9.0 percent
by weight vanadium (V), about 3.0 to about 4.0 percent by weight
aluminum (Al), about 0.8 to about 1.3 percent by weight iron (Fe),
about 0.14 to about 0.20 percent by weight oxygen (O), about 0.8 to
about 2.4 percent by weight chromium (Cr), and the balance
titanium.
[0012] Other embodiments of the disclosed titanium alloy
composition will become apparent from the following detailed
description, the accompanying drawings and the appended claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0013] FIG. 1 is a flow diagram depicting one embodiment of the
disclosed method for manufacturing an article;
[0014] FIG. 2 is a flow diagram of an aircraft manufacturing and
service methodology; and
[0015] FIG. 3 is a block diagram of an aircraft.
DETAILED DESCRIPTION
[0016] Disclosed is an alpha-beta titanium alloy that may be used
in wrought or powdered form. Significantly, articles formed from
the disclosed titanium alloy using powder metallurgy manufacturing
techniques may have mechanical properties, such as fatigue limit,
that are at least as good as (if not better than) the mechanical
properties of articles formed from wrought Ti-6Al-4V. Therefore,
the disclosed titanium alloy is an alternative to Ti-6Al-4V that is
particularly suitable for use in powder metallurgy.
[0017] In a first embodiment, disclosed is an alpha-beta titanium
alloy having the composition shown in Table 1.
TABLE-US-00001 TABLE 1 Element Range (wt %) Vanadium 7.0-9.0
Aluminum 3.0-4.5 Iron 0.8-1.5 Oxygen 0.14-0.22 Chromium 0 or
0.8-2.4 Titanium Balance
[0018] Chromium (Cr) is an optional component of the alpha-beta
titanium alloy of the first embodiment. When present, the
concentration of chromium may range from about 0.8 percent by
weight to about 2.4 percent by weight, such as from about 1.8
percent by weight to about 2.4 percent by weight.
[0019] Thus, the alpha-beta titanium alloy of the first embodiment
consists essentially of titanium (Ti), vanadium (V), aluminum (Al),
iron (Fe), oxygen (O) and, optionally, chromium (Cr).
[0020] Those skilled in the art will appreciate that various
impurities, which do not substantially affect the physical
properties of the alpha-beta titanium alloy of the first
embodiment, may also be present, and the presence of such
impurities will not result in a departure from the scope of the
present disclosure. For example, the impurities content of the
alpha-beta titanium alloy of the first embodiment may be controlled
as shown in Table 2.
TABLE-US-00002 TABLE 2 Impurity Maximum (wt %) Carbon 0.10 Nitrogen
0.05 Chlorine 0.05 Hydrogen 0.015 Silicon 0.05 Yttrium 0.005 Sodium
0.01 Magnesium 0.10 Other Elements, Each 0.10 Other Elements, Total
0.30
[0021] In a second embodiment, disclosed is an alpha-beta titanium
alloy having the composition shown in Table 3.
TABLE-US-00003 TABLE 3 Element Range (wt %) Vanadium 7.0-8.5
Aluminum 3.5-4.5 Iron 0.9-1.5 Oxygen 0.15-0.22 Titanium Balance
[0022] Thus, the alpha-beta titanium alloy of the second embodiment
consists essentially of titanium (Ti), vanadium (V), aluminum (Al),
iron (Fe) and oxygen (O). The impurities content of the alpha-beta
titanium alloy of the second embodiment may be controlled as shown
in Table 2.
[0023] One specific, non-limiting example of a titanium alloy of
the second embodiment has the composition shown in Table 4.
TABLE-US-00004 TABLE 4 Element Target (wt %) Vanadium 7.5 Aluminum
4.0 Iron 1.2 Oxygen 0.20 Titanium Balance
[0024] In a third embodiment, disclosed is an alpha-beta titanium
alloy having the composition shown in Table 5.
TABLE-US-00005 TABLE 5 Element Range (wt %) Vanadium 7.5-9.0
Aluminum 3.0-4.0 Chromium 0.8-2.4 Iron 0.8-1.3 Oxygen 0.14-0.20
Titanium Balance
[0025] Thus, the alpha-beta titanium alloy of the third embodiment
consists essentially of titanium (Ti), vanadium (V), aluminum (Al),
chromium (Cr), iron (Fe) and oxygen (O). The impurities content of
the alpha-beta titanium alloy of the third embodiment may be
controlled as shown in Table 2.
[0026] One specific, non-limiting example of a titanium alloy of
the third embodiment has the composition shown in Table 6.
TABLE-US-00006 TABLE 6 Element Target (wt %) Vanadium 8.0 Aluminum
3.5 Chromium 2.0 Iron 1.0 Oxygen 0.18 Titanium Balance
[0027] In one variation of the third embodiment, the disclosed
alpha-beta titanium alloy may have the composition shown in Table
7.
TABLE-US-00007 TABLE 7 Element Range (wt %) Vanadium 7.5-9.0
Aluminum 3.0-4.0 Chromium 1.8-2.4 Iron 0.8-1.3 Oxygen 0.14-0.20
Titanium Balance
[0028] The disclosed titanium alloy may be used to manufacture
various articles, such as aircraft parts and components, using
traditional casting or forging processes, or hybrid processes such
as powder metallurgy combined with forging, or rolling, or
extrusion, or welding (solid state (linear or rotational friction
or inertia) or traditional melting fusion or with filler).
Additionally the disclosed titanium alloys may be used for various
net shape and near net shape fabrication processes such as additive
manufacturing laser, electron beam, plasma arc melting techniques
and powder metallurgy additive laser or electron beam sintering
techniques. The disclosed titanium alloy may also be used in
powdered form to manufacture various articles using powder
metallurgy manufacturing techniques. As noted herein, the powdered
form of the disclosed titanium alloy (the disclosed powdered
titanium alloy composition) is significantly attractive,
particularly vis-a-vis Ti-6Al-4V in powdered form, due to an
anticipated improvement in the mechanical properties, particularly
fatigue limit, of the resulting articles.
[0029] Various powdered forms of the disclosed titanium alloy may
be used without departing from the scope of the present disclosure.
Regarding shape, the powder particles of the disclosed powdered
titanium alloy composition may be spherical, flakey, spongy,
cylindrical, blocky, acicular or the like. Powder particle shape
may be substantially uniform throughout the powdered titanium alloy
composition (e.g., all spherical particles) or multiple different
shapes may be included in a particular powdered titanium alloy
composition. Regarding size, the powder particles of the disclosed
powdered titanium alloy composition may have a broad particle size
distribution (e.g., a mixture of relatively large and relative
small particles) or a narrow particle size distribution (e.g.,
substantially uniform particle size).
[0030] In one expression, the disclosed powdered titanium alloy
composition may be prepared as a physical mixture of at least two
distinct powder compositions. As one specific, non-limiting
example, the disclosed powdered titanium alloy composition may be
prepared by mixing a first powder composition (a substantially pure
titanium powder) with a second powder composition (a master alloy
powder) in sufficient proportions to achieve the compositional
limits recited in Table 1.
[0031] In another expression, the disclosed powdered titanium alloy
composition includes a single powder component, and each powder
particle of the single powder component has substantially the same
composition. Specifically, each powder particle of the single
powder component has a composition within the compositional limits
recited in Table 1. Such a powdered titanium alloy composition may
be prepared, for example, by atomization, wherein a molten mass
having a composition within the compositional limits recited in
Table 1 is forced through an orifice.
[0032] Also disclosed is a method for manufacturing articles using
the disclosed powdered titanium alloy composition. Referring to
FIG. 1, one embodiment of the disclosed method for manufacturing an
article, generally designated 10, may begin at Block 12 with the
step of preparing a powdered titanium alloy composition. The
powdered titanium alloy composition prepared at Block 12 may have a
composition falling within the compositional limits recited in
Table 1.
[0033] At Block 14, the powdered titanium alloy composition may be
compacted to form a shaped mass. Various compaction techniques may
be used without departing from the scope of the present disclosure.
As one example, the compaction step (Block 14) may include die
pressing. As another example, the compaction step (Block 14) may
include cold isostatic pressing. As another example, the compaction
step (Block 14) may include metal injection molding. As yet another
example, the compaction step (Block 14) may include direct hot
isostatic pressing.
[0034] At Block 16, the shaped mass may optionally be sintered.
Sintering may be required when the compaction step (Block 14) does
not simultaneously sinter/consolidate. For example, the sintering
step (Block 16) may include heating the shaped mass to an elevated
temperature (e.g., about 2,000.degree. F. to about 2,500.degree.
F.) and maintaining the shaped mass at the elevated temperature for
at least a minimum amount of time (e.g., at least 60 minutes, such
as about 90 minutes to about 150 minutes).
[0035] At Block 18, the shaped mass (e.g., the sintered shaped
mass) may optionally be subjected to hot isostatic pressing ("HIP")
to reduce (if not eliminate) voids in the sintered shaped mass. For
example, the hot isostatic pressing step (Block 18) may be
performed at a pressure ranging from about 13 ksi to about 16 ksi
and a temperature ranging from about 1,475.degree. F. to about
1,800.degree. F., and the elevated pressure and temperature may be
applied for at least about 60 minutes, such as for about 120
minutes to about 300 minutes.
[0036] At Block 20, the shaped mass (e.g., the HIPed and sintered
shaped mass) may optionally be solution treated. For example,
solution treatment may include reheating the shaped mass from room
temperature to a temperature ranging from about 1400.degree. F. to
about 1725.degree. F., and maintaining at temperature for
approximately 1 hour before rapidly cooling/quench using various
quench media, such as, but not limited to, water, ethylene glycol,
liquid polymer additives and gas atmospheres/partial pressures that
could include argon, nitrogen and helium, individually or combined,
along with forced atmosphere fan cooling.
[0037] At Block 22, the shaped mass (e.g., the solution treated,
HIPed and sintered shaped mass) may optionally be aged. For
example, aging may include reheating the shaped mass from room
temperature to a temperature ranging from about 900.degree. F. to
about 1400.degree. F., and maintaining the shaped mass at
temperature for about 2 to about 8 hours before cooling back to
room temperature.
[0038] Accordingly, the disclosed method 10 may be used to
efficiently manufacture articles of various shapes and sized,
including articles (e.g., aircraft parts) having complex
geometries. Because the articles are produced to net (or near net)
shapes, little or no machining is required to finalize the article,
thereby significantly reducing both material and labor costs.
[0039] Articles formed from the disclosed powdered titanium alloy
composition may exhibit excellent mechanical properties. Indeed, it
is believed that articles formed from powdered forms of the
titanium alloy compositions presented in Tables 4 and 6 will
exhibit an ultimate tensile strength (ASTM-E8) of at least 130 ksi,
a yield strength (ASTM-E8) of at least 120 ksi and an elongation
(ASTM-E8) of at least 10 percent, which is comparable to that
achieved using wrought or powdered Ti-6Al-4V. Furthermore, it is
believed that articles formed from powdered forms of the titanium
alloy compositions presented in Tables 4 and 6 will exhibit a
fatigue limit of at least 95 ksi, which is comparable to that
achieved using wrought Ti-6Al-4V, but significantly better than
that achieved using powdered Ti-6Al-4V. Standard fatigue test
methods can include, but are not limited to, alternating and mean
stress imposed on various fatigue test specimen designs, such as,
but not limited to, rotational bending, cantilever flat, axial dog
bone, torsion, tension, three (3) or four (4) point bending.
[0040] Examples of the disclosure may be described in the context
of an aircraft manufacturing and service method 100, as shown in
FIG. 2, and an aircraft 102, as shown in FIG. 3. During
pre-production, the aircraft manufacturing and service method 100
may include specification and design 104 of the aircraft 102 and
material procurement 106. During production, component/subassembly
manufacturing 108 and system integration 110 of the aircraft 102
takes place. Thereafter, the aircraft 102 may go through
certification and delivery 112 in order to be placed in service
114. While in service by a customer, the aircraft 102 is scheduled
for routine maintenance and service 116, which may also include
modification, reconfiguration, refurbishment and the like.
[0041] Each of the processes of method 100 may be performed or
carried out by a system integrator, a third party, and/or an
operator (e.g., a customer). For the purposes of this description,
a system integrator may include without limitation any number of
aircraft manufacturers and major-system subcontractors; a third
party may include without limitation any number of venders,
subcontractors, and suppliers; and an operator may be an airline,
leasing company, military entity, service organization, and so
on.
[0042] As shown in FIG. 3, the aircraft 102 produced by example
method 100 may include an airframe 118 with a plurality of systems
120 and an interior 122. Examples of the plurality of systems 120
may include one or more of a propulsion system 124, an electrical
system 126, a hydraulic system 128, and an environmental system
130. Any number of other systems may be included.
[0043] The disclosed titanium alloy composition may be employed
during any one or more of the stages of the aircraft manufacturing
and service method 100. As one example, components or subassemblies
corresponding to component/subassembly manufacturing 108, system
integration 110, and or maintenance and service 116 may be
fabricated or manufactured using the disclosed titanium alloy
composition. As another example, the airframe 118 may be
constructed using the disclosed titanium alloy composition. Also,
one or more apparatus examples, method examples, or a combination
thereof may be utilized during component/subassembly manufacturing
108 and/or system integration 110, for example, by substantially
expediting assembly of or reducing the cost of an aircraft 102,
such as the airframe 118 and/or the interior 122. Similarly, one or
more of system examples, method examples, or a combination thereof
may be utilized while the aircraft 102 is in service, for example
and without limitation, to maintenance and service 116.
[0044] The disclosed titanium alloy composition is described in the
context of an aircraft; however, one of ordinary skill in the art
will readily recognize that the disclosed titanium alloy
composition may be utilized for a variety of applications. For
example, the disclosed titanium alloy composition may be
implemented in various types of vehicle including, for example,
helicopters, passenger ships, automobiles, marine products (boat,
motors, etc.) and the like.
[0045] Although various embodiments of the disclosed titanium alloy
composition and article formed therefrom have been shown and
described, modifications may occur to those skilled in the art upon
reading the specification. The present application includes such
modifications and is limited only by the scope of the claims.
* * * * *