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Creep Under Complex Stress Systems at High Temperatures

Creep Under Complex Stress Systems at High Temperatures DURING the last few years a programme of creep tests under general stress systems at high temperatures has been carried out at the N.P.L., using four metallic alloys which were chosen as being representative of basic groups of materials used in practice in machinery operating at high temperatures. This work, it was hoped, would fulfil, at least partly, the great need for experimental data in this field, as opposed to the comparative abundance of theoretical work available, and also enable a critical examination of the merits of this theoretical work to be made. The materials chosen in order of examination were a cast 017 per cent carbon steel, an aluminium alloy R.R. 59, a magnesium alloy containing 2 per cent aluminium, and a nickelchromium alloy Nimonic 75. Each material was tested at temperatures lying within the normal working range of the material in question. Thus the 017 per cent carbon steel was tested at 350, 450 and 550 dcg. C. 662, 842 and 1,022 deg. F., the aluminium alloy at 150 and 200 deg. C. 302 and 392 dcg. F., the magnesium alloy at 20 and 50 deg. C. 68 and 122 dcg. F., and the nickelchromium alloy at 550 and 650 dcg. C. 1,022 and 1,202 deg. F.. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Creep Under Complex Stress Systems at High Temperatures

Johnson, A.E.
Aircraft Engineering and Aerospace Technology , Volume 24 (1): 11 – Jan 1, 1952
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032121
Publisher site
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Abstract

DURING the last few years a programme of creep tests under general stress systems at high temperatures has been carried out at the N.P.L., using four metallic alloys which were chosen as being representative of basic groups of materials used in practice in machinery operating at high temperatures. This work, it was hoped, would fulfil, at least partly, the great need for experimental data in this field, as opposed to the comparative abundance of theoretical work available, and also enable a critical examination of the merits of this theoretical work to be made. The materials chosen in order of examination were a cast 017 per cent carbon steel, an aluminium alloy R.R. 59, a magnesium alloy containing 2 per cent aluminium, and a nickelchromium alloy Nimonic 75. Each material was tested at temperatures lying within the normal working range of the material in question. Thus the 017 per cent carbon steel was tested at 350, 450 and 550 dcg. C. 662, 842 and 1,022 deg. F., the aluminium alloy at 150 and 200 deg. C. 302 and 392 dcg. F., the magnesium alloy at 20 and 50 deg. C. 68 and 122 dcg. F., and the nickelchromium alloy at 550 and 650 dcg. C. 1,022 and 1,202 deg. F..

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jan 1, 1952

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