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US4499156A Expired / Lapsed US ⏱️ 0.0 years remaining

Titanium metal-matrix composites

Assignee: United States, UNITED STATES AIR FORCE THE, Secretary of
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Filing: 1983-03-22
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Granted: 1985-02-12
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Expires: 2003-03-22
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Abstract

Abstract Titanium alloy composites having substantially reduced reaction zones are provided which comprise a high strength/high stiffness filament such as silicon carbide, silicon carbide-coated boron, boron carbide-coated boron and silicon-coated silicon carbide, embedded in a fine-grained titanium alloy containing at least 40 percent beta phase, less than 7 percent Al and having a beta-transus temperature below 1750 DEG F. (955 DEG C.). Also provided is a method for fabricating titanium composites which comprises mechanically working a desired titanium alloy to obtain sheetstock in a desired thickness and having a relatively fine grain size, laying up a preform and consolidating the preform under increased temperature and pressure, wherein consolidation is carried out at a temperature below the beta-transus temperature of the alloy, thereby reducing the amount of reaction zone between the filament and the alloy matrix.

Inventors

  • 👤 Paul R. Smith
  • 👤 Francis H. Froes

Bibliographic Details

Application Number —
Jurisdiction US
Data Source google_patents
Last Synchronized 2026-10-27 22:14
CPC Classifications
C; C22; C22C; C22C49/00; C22C49/02; C22C49/10; C22C49/11; C22C47/00; C22C47/20; Y; Y10; Y10T; Y10T428/00; Y10T428/12; Y10T428/12486

Claims Analysis

Total Claims: 5
Claim 1
Independent Claim 132 words
A method for fabricating a titanium 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 a titanium alloy having the nominal composition Ti-4.5Al-5Mo-1.5Cr, which method comprises the steps of extensively mechanically working said alloy at about room temperature to obtain sheetstock in a desired thickness and having a grain size of less than 10 microns, fabricating a preform consisting of alternating layers of said sheetstock and at least one of said filamentary materials, and applying heat and pressure to consolidate said preform, wherein consolidation is carried out at a temperature about 10° to 100° C. below the beta-transus temperature of said alloy at a pressure in the approximate range of 10 to 100 MPa.
Claim 2
Independent Claim 132 words
A method for fabricating a titanium 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 a titanium alloy having the nominal composition Ti-4.5Al-5Mo-1.5Cr, which method comprises the steps of extensively mechanically working said alloy at about room temperature to obtain sheetstock in a desired thickness and having a grain size of less than 10 microns, fabricating a preform consisting of alternating layers of said sheetstock and at least one of said filamentary materials, and applying heat and pressure to consolidate said preform, wherein consolidation is carried out at a temperature about 10° to 100° C. below the beta-transus temperature of said alloy at a pressure in the approximate range of 10 to 100 MPa.
Claim 3
Dependent Claim 59 words
A titanium matrix composite structure 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 embedded in a titanium alloy matrix having the nominal composition Ti-4.5Al-5Mo-1.5Cr, said composite having a reaction zone width at the filamentary material-matrix interface of less than about 0.5 μm.
Claim 4
Dependent Claim 59 words
A titanium matrix composite structure 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 embedded in a titanium alloy matrix having the nominal composition Ti-4.5Al-5Mo-1.5Cr, said composite having a reaction zone width at the filamentary material-matrix interface of less than about 0.5 μm.
Claim 5
Dependent Claim 22 words
The composite of claim 2 wherein said filamentary material is silicon carbide-coated boron, and said reaction zone width is about 0.25 μm.

References Cited (Backward Citations)

No citation records indexed.

USPTO Annuity & Maintenance Windows

Annuity Stage Window Opens Payment Deadline Surcharge Period Until Estimated Fee Status
3.5 Years (Year 4) 1988-02-12 1988-08-13 1989-02-12 $2000.00 Window Closed / Lapsed
7.5 Years (Year 8) 1992-02-12 1992-08-13 1993-02-12 $3760.00 Window Closed / Lapsed
11.5 Years (Year 12) 1996-02-12 1996-08-13 1997-02-12 $7700.00 Window Closed / Lapsed

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