Process for treating titanium alloy parts for use as compressor disks in aircraft propulsion systems
US4854977A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Apr 14, 1988 |
| Grant date | Aug 8, 1989 |
| Priority date | — |
| Expiry date | Apr 14, 2008 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC22F1/183
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
The process according to the invention comprises the following stages: PA1 (a) an ingot of the following composition is produced (% by weight): Al 3.8 to 5.4, Sn 1.5 to 2.5, Zr 2.8 to 4.8, Mo 1.5 to 4.5, Cr<2.5 and Cr+V 1.5 to 4.5, Fe<2.0, Si<0.3, 0<0.15, the remainder being Ti and impurities; PA1 (b) the ingot undergoes hot working, comprising a rough-shaping and then a final working preceded by preheating in the beta range; PA1 (c) the blank of the part obtained is solid solution heat treated by maintaining it at a temperature 10.degree. to 40.degree. C. lower than its real "beta transus"; PA1 (d) ageing for 4 to 12 h at between 550.degree. and 650.degree. C. is then carried out on the blank of the part or the part itself. The invention also relates to the process and the parts obtained under preferred conditions, said parts having in particular a good mechanical strength (Rm and R.sub.p0.2 respectively at least equal to 1200 and 1100 MPa), a good tenacity and a good creep resistance at 400.degree. C. (under 600 MPa, elongation of 0.5% in more than 200 h).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.