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US4733816A
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Method to produce metal matrix composite articles from alpha-beta titanium alloys
Assignee: United States Department of the Air Force
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Filing: 1986-12-11
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Granted: 1988-03-29
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Expires: 2006-12-11
Abstract
Abstract A method for fabricating an improved titanium alloy composite consisting of at least one high strength/high stiffness filament or fiber embedded in an alpha-beta titanium alloy matrix which comprises the steps of providing a rapidly-solidified foil made of an alpha-beta titanium alloy, fabricating a preform consisting of alternating layers of the rapidly-solidified foil and the filamentary material, and applying heat and pressure to consolidate the preform, wherein consolidation is carried out at a temperature below the beta-transus temperature of the alloy.
Inventors
- 👤 Daniel Eylon
- 👤 Francis H. Froes
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 15:04
CPC Classifications
C; C22; C22C; C22C47/00; C22C47/20
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
110 words
A method for fabricating a titanium alloy composite consisting of at least one filamentary material selected from the group consisting of silicon carbide, silicon carbide-coated boron, boron carbide-coated boron, and silicon-coated silicon carbide, and an alpha-beta titanium alloy which comprises the steps of: (a) providing a rapidly solidified foil of said alloy; (b) fabricating a preform consisting of alternating layers of at least one of said filamentary materials and said foil; and (c) applying heat at a level about 100° to 300° C. below the beta transus temperature of said alloy and a pressure of about 1.5 to 15 ksi for about 0.2 to 24 hours to consolidate said preform.
Claim 2
Independent Claim
110 words
A method for fabricating a titanium alloy composite consisting of at least one filamentary material selected from the group consisting of silicon carbide, silicon carbide-coated boron, boron carbide-coated boron, and silicon-coated silicon carbide, and an alpha-beta titanium alloy which comprises the steps of: (a) providing a rapidly solidified foil of said alloy; (b) fabricating a preform consisting of alternating layers of at least one of said filamentary materials and said foil; and (c) applying heat at a level about 100° to 300° C. below the beta transus temperature of said alloy and a pressure of about 1.5 to 15 ksi for about 0.2 to 24 hours to consolidate said preform.
Claim 3
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-6Al-4V.
Claim 4
Dependent Claim
19 words
The method of claim 2 wherein said preform is consolidated at 730° C. at 10 ksi for 24 hours.
Claim 5
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-6Al-6V-2Sn.
Claim 6
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-8Mn.
Claim 7
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-7Al-4Mo.
Claim 8
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-4.5Al-5Mo-1.5Cr.
Claim 9
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-6Al-2Sn-4Zr-6Mo.
Claim 10
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-5Al-2Sn-2Zr-4Mo-4Cr.
Claim 11
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-6Al-2Sn-2Zr-2Mo-2Cr.
Claim 12
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-5.5Al-3.5Sn-3Zr-0.3Mo-1Nb-0.3Si.
Claim 13
Dependent Claim
10 words
The method of claim 1 wherein said alloy is Ti-5.5Al-4Sn-4Zr-0.3Mo-1Nb-0.5Si-0.06C.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1991-03-29 | 1991-09-28 | 1992-03-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-03-29 | 1995-09-28 | 1996-03-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-03-29 | 1999-09-28 | 2000-03-29 | $7700.00 | Window Closed / Lapsed |