Abstract
Fatigue cracking is one of the most common damage modes of aeroengine hot-end components, usually subjected to mixed-mode cracking. In this study, mixed-mode fatigue crack growth experiments at 550 °C are carried out using compact tension shear specimens made of nickel-based superalloy GH4169. Adaptive finite element method was used to verify several models at high temperature. The accuracy of angle dependent models was higher at 550 °C, and the rate of da/dN increased and decreased twice with crack propagating, which is different from room temperature (20–25 °C). This research could provide a basis for lifespan prediction of aeroengine hot-end components.
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