Nickel alloy for turbine engine components
US6132527A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 8, 1998 |
| Grant date | Oct 17, 2000 |
| Priority date | — |
| Expiry date | Dec 8, 2018 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC22C19/056
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A new nickel base superalloy suitable for compressor or turbine discs of gas turbine engines with fatigue crack propagation resistance equal to Waspaloy, tensile strength higher than Waspaloy and higher operating temperature than Waspaloy or UDIMET 720 family of alloys. The nickel base superalloy has a preferred composition by weight % of 14.0-19.0% cobalt, 14.35-15.15 Chromium, 4.25-5.25 Molybdenum, 1.35-2.15 tantalum, 3.45-4.15 titanium, 2.85-3.15 aluminium, 0.01-0.025 boron, 0.012-0.033 carbon, 0.05-0.07 zirconium, 0.5-1.0 hafnium, up to 1.0 rhenium, up to 2.0 tungsten, less than 0.5 niobium, up to 0.1 yttrium, up to 0.1 vanadium, up to 1.0 iron, up to 0.2 silicon, up to 0.15 manganese and balance nickel plus incidental impurities.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.