Patent US4094708A successfully refreshed from Google Patents.
US4094708A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Titanium-base alloys
Assignee: Imperial Metal Industries Kynoch Ltd
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Filing: 1977-02-17
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Granted: 1978-06-13
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Expires: 1997-02-17
Abstract
Abstract A high strength creep resistant titanium alloy comprising titanium, 6% aluminium, 5% zirconium, 0.5% molybdenum, 0.25% silicon is disclosed in a particular heat-treated condition. The alloy is particularly useful for engine components.
Inventors
- 👤 Roger Thomas John Hubbard
- 👤 Richard Ernest Goosey
- 👤 Donald Francis Neal
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 12:55
CPC Classifications
C; C22; C22C; C22C14/00
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
138 words
A high strength creep resistant titanium-base alloy consisting of 6% aluminium, 5% zirconium, 0.5% molybdenum, 0.25% silicon, balance titanium, apart from impurities, said alloy having a creep strain less than 0.1% in 100 hours at 520° C at a stress of 20 tonf/in 2 and in the as welded condition a room temperature ductility of at least 15% reduction in area and 10% elongation when measured on a gauge length of 4√S o where S o is the cross-sectional area, the alloy being beta solution treated at 1050° C, cooled and aged for not less than 24 hours at a temperature not less than 500° C, and air cooled, whereby the alloy has an alpha plate-like structure with precipitate at the alpha plate boundaries, said precipitate being a titanium/molybdenum silicide, and having a principally body centred cubic structure.
Claim 2
Dependent Claim
138 words
A high strength creep resistant titanium-base alloy consisting of 6% aluminium, 5% zirconium, 0.5% molybdenum, 0.25% silicon, balance titanium, apart from impurities, said alloy having a creep strain less than 0.1% in 100 hours at 520° C at a stress of 20 tonf/in 2 and in the as welded condition a room temperature ductility of at least 15% reduction in area and 10% elongation when measured on a gauge length of 4√S o where S o is the cross-sectional area, the alloy being beta solution treated at 1050° C, cooled and aged for not less than 24 hours at a temperature not less than 500° C, and air cooled, whereby the alloy has an alpha plate-like structure with precipitate at the alpha plate boundaries, said precipitate being a titanium/molybdenum silicide, and having a principally body centred cubic structure.
Claim 3
Dependent Claim
158 words
A shaped aircraft engine component which in service is subjected to a temperature of up to 520° C, said component being formed from an alloy which consists of a 6% aluminium, 5% zirconium, 0.5% molybdenum, 0.25% silicon, balance titanium, apart from impurities, said alloy having a creep strain less than 0.1% in 100 hours at 520° C at a stress of 20 tonf/in 2 and in the as welded condition a room temperature ductility of at least 15% reduction in area and 10% elongation when measured on a gauge length of 4√S o where S o is the cross-sectional area, the alloy being beta solution treated at 1050° C, cooled and aged for not less than 24 hours at a temperature not less than 500° C, and air cooled, whereby the alloy has an alpha plate-like structure with precipitate at the alpha plate boundaries, said precipitate being a titanium/molybdenum silicide and having a principally body centred cubic structure.
Claim 4
Dependent Claim
158 words
A shaped aircraft engine component which in service is subjected to a temperature of up to 520° C, said component being formed from an alloy which consists of a 6% aluminium, 5% zirconium, 0.5% molybdenum, 0.25% silicon, balance titanium, apart from impurities, said alloy having a creep strain less than 0.1% in 100 hours at 520° C at a stress of 20 tonf/in 2 and in the as welded condition a room temperature ductility of at least 15% reduction in area and 10% elongation when measured on a gauge length of 4√S o where S o is the cross-sectional area, the alloy being beta solution treated at 1050° C, cooled and aged for not less than 24 hours at a temperature not less than 500° C, and air cooled, whereby the alloy has an alpha plate-like structure with precipitate at the alpha plate boundaries, said precipitate being a titanium/molybdenum silicide and having a principally body centred cubic structure.
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) | 1981-06-12 | 1981-12-12 | 1982-06-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-06-12 | 1985-12-12 | 1986-06-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-06-12 | 1989-12-12 | 1990-06-13 | $7700.00 | Window Closed / Lapsed |