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RESEARCH PAPERS

High-Temperature, Cobalt-Tungsten Alloys for Aerospace Applications

[+] Author and Article Information
J. C. Freche

Fatigue and Alloys Research Branch, Lewis Research Center, National Aeronautics and Space Administration, Cleveland, Ohio

R. L. Ashbrook, G. D. Sandrock

Lewis Research Center, National Aeronautics and Space Administration, Cleveland, Ohio

J. Eng. Ind 87(1), 9-20 (Feb 01, 1965) (12 pages) doi:10.1115/1.3670768 History: Received September 21, 1964; Online December 08, 2011

Abstract

The high-temperature capability and workability of cobalt-tungsten alloys for aerospace applications is discussed. The average life at 1850 F and 15,000 psi of the strongest previously reported alloy, Co-25 W-1Ti-1Zr-0.4C, was doubled from 92 to 185 hr by small additions of chromium and rhenium. At 2200 F and 5000 psi, the strongest alloy, Co-25W-1Ti-1Zr-3Cr-2Re-0.4C, had a rupture life of 23 hr; the elevated-temperature rupture strength compared favorably with the strongest available conventional (high-chromium) cobalt-base alloys. Above approximately 2035 F and at reasonably high stress levels (10,000 and 15,000 psi), its stress-rupture life also exceeded those of the strongest known nickel-base alloys, including the NASA tantalum-modified alloy and SM-200. It is particularly significant that even the strongest alloys of this series were readily hot-rolled. Ingots 1/2 in. thick were reduced to 0.065-in. sheet and subsequently cold-rolled to 0.0125-in. sheet. Elongations as high as 31 percent were obtained at room temperature with annealed sheet specimens. The good ductility obtained suggests that these alloys could be fabricated into complex shapes required for various aerospace and other applications. Although the strongest alloys had a chromium content of only 3 percent, they did not oxidize catastrophically in air.

Copyright © 1965 by ASME
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