Accession Number:

AD0672324

Title:

TERMINAL FRACTURE OF TITANIUM ALLOYS CONTAINING STRESS-CORROSION CRACKS,

Descriptive Note:

Corporate Author:

BOEING CO RENTON WASH COMMERCIAL AIRPLANE DIV

Personal Author(s):

• Carter,C. S.

Report Date:

1968-05-03

Pagination or Media Count:

32.0

Abstract:

Approximately one hundred precracked notch bend specimens of Ti-6Al-4V and Ti-4Al-3Mo-1V, previously sustain loaded in 3.5 sodium chloride solution have been examined. The conditions for complete separation of the specimens were determined. In general, this occurred when the stress intensity at the border of the extending stress-corrosion crack reached the plane strain fracture toughness KIc. Observed deviations from this behavior were primarily attributed to crack length measurement difficulties. The fatigue precrack in specimens loaded to stress intensity levels below the threshold stress intensity level KIscc was not affected by the environment, i.e., there was no blunting. Author

Descriptors:

• (*TITANIUM ALLOYS
• *MECHANICAL PROPERTIES)
• IMPACT TESTS
• FRACTURE(MECHANICS)
• CRACK PROPAGATION
• LOADS(FORCES)
• STRESS CORROSION
• HEAT TREATMENT
• DUCTILE BRITTLE TRANSITION

Subject Categories:

• Properties of Metals and Alloys

Distribution Statement:

APPROVED FOR PUBLIC RELEASE