| 摘要 |
Nickel-based superalloys used in high-temperature gas turbine engine components such as turbine disks and compressor disks are provided, high-temperature gas turbine engine components such as turbine disks and compressor disks manufactured from the nickel-based superalloys are provided, and methods of manufacturing the high-temperature gas turbine engine components are provided. A nickel-based superalloy for gas turbine engine components comprises, in weight percent, 16.0% or more of cobalt, and 6.0% or more of tantalum. The content of nickel is 50% or more, 44 to 56%, or 48 to 52%. The nickel-based superalloy further comprises an aluminum content and a titanium content, wherein a ratio of the titanium content to the aluminum content is 0.57 or more. The nickel-based superalloy further comprises aluminum, titanium, and niobium, wherein a combined content of the tantalum, aluminum, titanium, and niobium is 12.3% or more. The nickel-based superalloy further comprises 6.0% or more of chromium. The nickel-based superalloy further comprises 2.5% or more of aluminum, and no more than 4.0% of each of the additional constituents if there are any additional constituents. The nickel-based superalloy further comprises 6.5% or more of a compound combined of one or more of aluminum, titanium, niobium, and hafnium.
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