US20180029131A1

US20180029131A1 - Powdered Titanium Alloy Composition and Article Formed Therefrom

Info

Publication number: US20180029131A1
Application number: US15/219,812
Authority: US
Inventors: Joseph Pecina; Robert Burkett; Gary M. Backhaus; Michael S. Carr; Ryan J. Glamm
Original assignee: Boeing Co
Current assignee: Boeing Co
Priority date: 2016-07-26
Filing date: 2016-07-26
Publication date: 2018-02-01

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.

Description

FIELD

This application generally relates to titanium alloys and, more particularly, to titanium alloys for powder metallurgy.

BACKGROUND

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/cm³), 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.
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.
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.
Accordingly, those skilled in the art continue with research and development efforts in the field of titanium alloys.

SUMMARY

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.
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.
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.
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.
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.
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.
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

FIG. 1 is a flow diagram depicting one embodiment of the disclosed method for manufacturing an article;

FIG. 2 is a flow diagram of an aircraft manufacturing and service methodology; and

FIG. 3 is a block diagram of an aircraft.

DETAILED DESCRIPTION

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.
In a first embodiment, disclosed is an alpha-beta titanium alloy having the composition shown in Table 1.

	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

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.
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).
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 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

In a second embodiment, disclosed is an alpha-beta titanium alloy having the composition shown in Table 3.

	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

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.
One specific, non-limiting example of a titanium alloy of the second embodiment has the composition shown in Table 4.

	TABLE 4

	Element	Target (wt %)

	Vanadium	7.5
	Aluminum	4.0
	Iron	1.2
	Oxygen	0.20
	Titanium	Balance

In a third embodiment, disclosed is an alpha-beta titanium alloy having the composition shown in Table 5.

	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

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.
One specific, non-limiting example of a titanium alloy of the third embodiment has the composition shown in Table 6.

	TABLE 6

	Element	Target (wt %)

	Vanadium	8.0
	Aluminum	3.5
	Chromium	2.0
	Iron	1.0
	Oxygen	0.18
	Titanium	Balance

In one variation of the third embodiment, the disclosed alpha-beta titanium alloy may have the composition shown in Table 7.

	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

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.
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).
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.
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.
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.
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.
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° F. to about 2,500° 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).
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° F. to about 1,800° 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.
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° F. to about 1725° 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.
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° F. to about 1400° F., and maintaining the shaped mass at temperature for about 2 to about 8 hours before cooling back to room temperature.
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.
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.
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.
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.
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.
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.
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.
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.

Claims

What is claimed is:

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.