Salt-Stress-Corrosion Cracking of Residually Stressed Ti-8Al-1Mo-1V Brake-Formed Sheet at 550 degrees F (561 degrees K)
Abstract
An experimental investigation of salt-stress-corrosion cracking with residual stresses has been conducted with one of the supersonic-transport candidate materials, Ti-8Al-1Mo-1V. Specimens with right-angle bends were brake formed from sheet material to produce residual stresses, coated with sodium chloride, and exposed at 550 deg F (561 deg K). After various exposure times, some of the specimens were given a reverse-bend test to determine the extent of cracking based on bending deflection. Other specimens were examined metallurgically. Salt-stress-corrosion cracks began to appear in less than 20 hours, and the effects were at least as severe as the effects produced by load-induced tensile stresses. Several approaches were examined for alleviating the corrosion cracking, and, of these, shot peening and nickel plating appear promising enough to warrant further investigation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1965
- Accession Number
- ADA397609
Entities
People
- John M. Woodard
- Richard A. Pride
Organizations
- National Aeronautics and Space Administration