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The S.A.E. National Aeronautic Meeting

The S.A.E. National Aeronautic Meeting 656. Design and Manufacturing Techniques with Titanium. O. A. Wheelon. The author's company undertook a project in which weight was an extremely critical factor, and it was found that the use of commercially pure titanium in certain applications would make possible a saving of about 5 per cent of the structural weight. In the temperature range 300 deg. F. to 800 deg. F. titanium and its alloys have considerable strengthweight advantages over the stainless steels previously used. The fabrication characteristics of the material were studied to ensure that structures could be produced economically. It was found possible to design and manufacture a large number of titanium parts, resulting in a saving of about 395 lb. on the structure. Forming annealed titanium was found similar to magnesium, and machining similar to stainless steel. Spot and fusion welding appeared unsatisfactory with the best current practice. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

The S.A.E. National Aeronautic Meeting

Aircraft Engineering and Aerospace Technology , Volume 23 (12): 4 – Dec 1, 1951
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032112
Publisher site
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Abstract

656. Design and Manufacturing Techniques with Titanium. O. A. Wheelon. The author's company undertook a project in which weight was an extremely critical factor, and it was found that the use of commercially pure titanium in certain applications would make possible a saving of about 5 per cent of the structural weight. In the temperature range 300 deg. F. to 800 deg. F. titanium and its alloys have considerable strengthweight advantages over the stainless steels previously used. The fabrication characteristics of the material were studied to ensure that structures could be produced economically. It was found possible to design and manufacture a large number of titanium parts, resulting in a saving of about 395 lb. on the structure. Forming annealed titanium was found similar to magnesium, and machining similar to stainless steel. Spot and fusion welding appeared unsatisfactory with the best current practice.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Dec 1, 1951

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