Abstract
Multiple sets of growth rate data for small fatigue cracks in seven different aircraft gas turbine engine rotor materials, including both titanium alloys and nickel-based superalloys, have been collected and are critically compared against corresponding large-crack data. The database includes a wide range of microstructures as well as multiple stress ratios and temperatures. The ability of the simple El Haddad small-crack model and its length parameter a0 to correlate the small-crack and large-crack data by adjusting the small-crack driving force is critically evaluated. Different methods of estimating a0, including the traditional calculation from large-crack threshold and endurance limit properties, as well as a new approach based on empirical scaling from microstructural dimensions, are explored and compared. Strengths and limitations of the simple El Haddad approach for engineering applications are discussed, as well as the practical significance of small-crack effects for life prediction.
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