Year-end Sale % OFF 
Abstract
Most aero-engine components and structures are subjected to life critical fatigue loads during service. Near-α titanium alloy IMI 834 is one candidate aero-engine material that is used as high-pressure compressor discs due to its superior fatigue strength and creep resistance. The effect of heat treatment on the microstructure and high-cycle fatigue behaviour of the material has been studied and reported here. The alloy was solution-heat-treated at 1060 °C and subsequently quenched in different media. A strong effect of quench media (cooling rate) on high-cycle fatigue life has been observed. Fractographic investigations were performed to correlate the fracture micro-mechanism with heat treatment. Further, a generalized stress-life model has been deduced from the fatigue data and integrated with finite element analysis to develop a fatigue model for the alloy.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
