Fatigue Crack Growth Investigation of a Ti-6A1-4V Forging under Complex Loading Conditions - NATO/AGARD Supplemental Engine Disk Program.

摘要

Fatigue crack growth rate testing was performed on a Titanium-6 Aluminum-4 Vanadium engine disk forging as part of the SUPPLEMENTAL Engine Disk Program sponsored by the North Atlantic Treaty Organization's Advisory Group for Aerospace Research and Development (NATO/AGARD). Such data were developed under room temperature conditions under a variety of load histories, ranging from constant amplitude with periodic overload to various forms of the TURBISTAN engine spectrum. The effects of each loading condition are examined with respect to fatigue crack growth rates. Crack growth mechanisms are identified for the various load histories based on SEM examinations. Comparisons are made between crack growth rates determined via electric potential methodology and those from fatigue striation measurements. Keywords: Aircraft engines. (aw)