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Abstract

A second-stage compressor blade in an aircraft engine fractured after 21 h of service. The remaining portion of the blade was removed and examined as were several adjacent blades. Based on the results of SEM fractography, microstructural analysis, and hardness testing, the blade failed due to stress-corrosion cracking combined with the effects of inadequate tempering.

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Failure of a Second-Stage Compressor Blade in an Aircraft Engine, Failure Analysis of Engineering Structures: Methodology and Case Histories, By V. Ramachandran, A.C. Raghuram, R.V. Krishnan, S.K. Bhaumik, ASM International, 2005, p 133–134, https://doi.org/10.31399/asm.tb.faesmch.t51270133

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