Crack Growth Modeling in an Advanced Powder Metallurgy Alloy
Final technical rept. 1 Sep 1977-1 Feb 1980
GENERAL ELECTRIC CO CINCINNATI OH
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An interpolative model has been developed to calculate the cyclic crack growth rate of an advanced aircraft engine disk alloy AF115. The test variables included within the model consists of stress ratio, temperature, frequency, and hold time. The model was based on experimental results conducted within a statistically designed test program. A nonsymmetric Sigmoidal equation consisting of six independent coefficients was used to equate stress intensity range to cyclic growth rate. Two verification tests were conducted at two conditions other than those used during the development of the model to evaluate the model.
- Metallurgy and Metallography