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Nickel Base Superalloy Turbine DiskA low solvus, high refractory alloy having unusually versatile processing mechanical property capabilities for advanced disks and rotors in gas turbine engines. The nickel base superalloy has a composition consisting essentially of, in weight percent, 3.0-4.0 N, 0.02-0.04 B, 0.02-0.05 C, 12.0-14.0 Cr, 19.0-22.0 Co, 2.0-3.5 Mo, greater than 1.0 to 2.1 Nb, 1.3 to 2.1 Ta,3.04.OTi,4.1 to 5.0 W, 0.03-0.06 Zr, and balance essentially Ni and incidental impurities. The superalloy combines ease of processing with high temperature capabilities to be suitable for use in various turbine engine disk, impeller, and shaft applications. The Co and Cr levels of the superalloy can provide low solvus temperature for high processing versatility. The W, Mo, Ta, and Nb refractory element levels of the superalloy can provide sustained strength, creep, and dwell crack growth resistance at high temperatures.
Document ID
20060009000
Acquisition Source
Headquarters
Document Type
Other - Patent
Authors
Gabb, Timothy P.
(NASA Glenn Research Center Cleveland, OH, United States)
Gauda, John
(NASA Glenn Research Center Cleveland, OH, United States)
Telesman, Ignacy
(NASA Glenn Research Center Cleveland, OH, United States)
Kantzos, Pete T.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 23, 2013
Publication Date
December 13, 2005
Subject Category
Metals And Metallic Materials
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-6,974,508|NASA-Case-LEW-17318-1
Patent Application
US-Patent-Appl-SN-283220
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