High-Temperature, Cobalt-Tungsten Alloys for Aerospace ApplicationsSource: Journal of Manufacturing Science and Engineering:;1965:;volume( 087 ):;issue: 001::page 9DOI: 10.1115/1.3670768Publisher: The American Society of Mechanical Engineers (ASME)
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.
keyword(s): Alloys , Cobalt , Aerospace industry , Tungsten , High temperature , Rupture , Temperature , Stress , Ductility , Workability , Elongation , Nickel , Shapes AND Tantalum ,
|
Collections
Show full item record
contributor author | J. C. Freche | |
contributor author | R. L. Ashbrook | |
contributor author | G. D. Sandrock | |
date accessioned | 2017-05-08T23:36:57Z | |
date available | 2017-05-08T23:36:57Z | |
date copyright | February, 1965 | |
date issued | 1965 | |
identifier issn | 1087-1357 | |
identifier other | JMSEFK-27488#9_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/109391 | |
description 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. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | High-Temperature, Cobalt-Tungsten Alloys for Aerospace Applications | |
type | Journal Paper | |
journal volume | 87 | |
journal issue | 1 | |
journal title | Journal of Manufacturing Science and Engineering | |
identifier doi | 10.1115/1.3670768 | |
journal fristpage | 9 | |
journal lastpage | 20 | |
identifier eissn | 1528-8935 | |
keywords | Alloys | |
keywords | Cobalt | |
keywords | Aerospace industry | |
keywords | Tungsten | |
keywords | High temperature | |
keywords | Rupture | |
keywords | Temperature | |
keywords | Stress | |
keywords | Ductility | |
keywords | Workability | |
keywords | Elongation | |
keywords | Nickel | |
keywords | Shapes AND Tantalum | |
tree | Journal of Manufacturing Science and Engineering:;1965:;volume( 087 ):;issue: 001 | |
contenttype | Fulltext |