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Wear of a Gas Turbine Friction Damper

Wear of a Gas Turbine Friction Damper. MANE-6960 Friction, Wear, and Lubrication of Materials. Overview. Wear of a dry friction damper in turbine section of engine investigated

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Wear of a Gas Turbine Friction Damper

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  1. Wear of a Gas Turbine Friction Damper MANE-6960 Friction, Wear, and Lubrication of Materials

  2. Overview • Wear of a dry friction damper in turbine section of engine investigated • Blade excitation is one of many failure concerns due to risk of cyclic crack propagation from dynamic loading coupled with high thermal and static loading • Turbine blade vibration amplitude mitigated by use of under platform “cottage-roof” damper to dissipate kinetic energy by means of frictional contact and heat generation

  3. Theory and Methodology • Archard’s law for adhesive wear: • Relative tangential slip movement between damper wearing surface and blade counter surface on the order of 25 micrometers • Damper wear due to adhesion and fretting cannot be avoided, but mitigated with appropriate materials • Low change in damper volume is essential in retaining vibrational damping capability over the lifetime of the component

  4. Results • Various hardness values of high temperature alloys have an effect on damper wear rates • Nickel and Cobalt-Chromium alloy hardness can range from 165 BHN to 515 BHN in a high temperature environment • Surface modification by means of carburization can be an effective low cost solution over high bulk material hardness alloys

  5. Conclusion • Adhesive wear due to plastic deformation of asperity and bulk material cannot be avoided over high cyclic loading • Increasing material hardness retains damping capability of the part over lifetime of engine operation • Gas carburizing further improves part capability • Softer and lighter Ni alloy can behaves as high hardness Co-Cr alloy for most of part lifetime

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