The physical concepts and mathematical techniques needed to examine the effects of friction dampers on gas turbine engine rotor stages are developed. Blade to ground dampers are studied using a single degree of freedom model of an isolated blade. The range of conditions for stable response, maximum stabilized negative damping, optimum damper parameters and the effect of external excitation are also examined. The use of friction dampers in three, six, nine and twelve bladed disks is considered.
|Original language||English (US)|
|Journal||[No source information available]|
|State||Published - Jan 1 1983|
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