The configuration and fit of gas turbine compressor blade roots and disc slots is critical, designed to withstand the vibrations and high dynamic forces generated in service.

Lightweight titanium alloys are extensively employed in aircraft turbine engines. Fretting wear between the mating surfaces of the disc and blade root is a major concern that must be addressed to reduce the potential of catastrophic failure.

This fretting is primarily the result of high frequency vibration generated by air flow through the compressor rotating blades.

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