Abstract
The properties of Ti-6A1-4V remain attractive and provide a guideline for materials selection when considering the relative design efficiency achievable with titanium, aluminum and steel. However, the potential for further property improvements in this alloy by chemical composition modifications or by new thermomechanical processing (IMP) sequences appear to be very limited. The requirements of modern aircraft, which are designed with the aid of fracture mechanics criteria, has led to the need for an alloy whose strength is slightly greater than Ti-6A1-4V in the annealed condition and whose plane strain fracture toughness is significantly higher.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
Berryman, R. G., Froes, F. H., Chesnutt, J. C., Rhodes, C.G., Williams, J. C. and Malone, R. F., "High Toughness Titanium Alloy Development," Final Engineering Report, July 1974. Naval Air Systems Command Report TFD-74-657.
Froes, F. H., Petersen, V. C., Malone, R. F., Rhodes, C. G., Chesnutt, J. C. and Williams, J. C., "Research on Deep Hardenable Titanium Alloys for Large Airframe Structural Members," Final Technical Report, September 1975. AFML-TR-75-41.
Author information
Authors and Affiliations
Editor information
Rights and permissions
Copyright information
© 1982 Springer Science+Business Media New York
About this chapter
Cite this chapter
Froes, F.H., Berryman, R.G., Williams, J.C. (1982). Development of a New Moderate Strength, High Fracture Toughness Titanium Alloy: Ti-4.5A1-5Mo-L.5Cr (Corona 5). In: Williams, J.C., Belov, A.F. (eds) Titanium and Titanium Alloys. Springer, Boston, MA. https://doi.org/10.1007/978-1-4757-1758-7_50
Download citation
DOI: https://doi.org/10.1007/978-1-4757-1758-7_50
Publisher Name: Springer, Boston, MA
Print ISBN: 978-1-4757-1760-0
Online ISBN: 978-1-4757-1758-7
eBook Packages: Springer Book Archive