Fatigue cracking in gamma titanium aluminide

TL;DR

This study investigates how temperature variations affect fatigue crack growth in gamma titanium aluminide, revealing temperature-dependent crack growth rates, microstructural initiation sites, and crack mode transitions relevant for jet engine blade durability.

Contribution

It provides new insights into the effects of temperature cycling on fatigue crack growth and microstructural initiation in gamma titanium aluminide alloys.

Findings

Higher crack growth rates at 750°C compared to 400°C.

Temperature excursions retard crack growth during cycling.

Microstructural initiation occurs at small notches near failure stress.

Abstract

Cast and HIP'ed \textgamma-TiAl 4522XD is being developed for use in jet engine low pressure turbine blades, where temperature variations occur through the flight cycle. The effects of temperature variations on fatigue cracking were therefore examined in this study. It was found that fatigue crack growth rates were higher at 750C than 400C, but that $\Delta K_\mathrm{th}$ was also higher. Temperature excursions between 400 and 750C during fatigue crack growth resulted in retardation of the crack growth rate, both on heating and cooling. It was also found that for notches $0.6$~mm in length and smaller, initiation from the microstructure could instead be observed at stresses similar to the material failure stress; a microstructural initiation site exists. A change from trans- to mixed trans-, inter- and intra-lamellar cracking could be observed where the estimated size of the crack tip plastic zone exceeded the colony size.