Development of a New Moderate Strength, High Fracture Toughness Titanium Alloy: Ti-4.5A1-5Mo-L.5Cr (Corona 5)

  • F. H. Froes
  • R. G. Berryman
  • J. C. Williams


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.


Fracture Toughness Fatigue Crack Propagation Compact Tension Intergranular Crack Fatigue Crack Propagation Rate 
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  1. 1.
    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.Google Scholar
  2. 2.
    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.Google Scholar

Copyright information

© Springer Science+Business Media New York 1982

Authors and Affiliations

  • F. H. Froes
    • 1
  • R. G. Berryman
    • 2
  • J. C. Williams
    • 3
  1. 1.Colt IndustriesCrucible Materials Research CenterPittsburghUSA
  2. 2.Rockwell InternationalLos Angeles Aircraft DivisionEl SegundoUSA
  3. 3.Carnegie-Mellon UniversityDepartment of Metallurgy and Materials SciencePittsburghUSA

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