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Topic Title: PATENT: Nickel Base Superalloy Turbine Disk
Topic Summary: U.S. Patent No. 6,974,508, Dec. 13, 2005
Created On: 2/10/2007 6:34 AM

 2/10/2007 6:34 AM

Lynette Karabin

Posts: 238
Joined: 2/5/2007

A 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.

SOURCE: Gabb, T.M., J. Gayda, I. Telesman and P. T. Kantzos. U.S. Patent No. 6,974,508, Dec. 13, 2005


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