Fatigue-Crack-Growth Analysis of Titanium Gas-Turbine Fan Blades.

摘要

First stage forged titanium gas turbine fan blades from a military aircraft were removed from service, cut into specimens and tested for fatigue crack growth properties. A method for determining stress intensity based on change in compliance with increasing crack length was applied. Results of testing in air and salt water environments are presented. A model, based on stress-strain curve behavior, is developed and applied to simulate the data. The data is compared to that taken from rolled baseplate forms of the same material and the applicability of the data to fan blade design and life-time estimates is discussed. (Author)