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3.- Provide with an analytical expression for the change inblade frequency as a
function of the geometrical blade parameters participating inthe blade redesign.
One of the main aeroelastic problems in turbomachinery is force response due to different excitation sources. The identification of resonances is performed at the early design stage, by making use of Campbell diagrams. The following simplified geometry, representative of a section of a compressor will be analysed. The questions must be answered in hand-written format. c=0.5m 0.03 m 0.12 m 1 4 0.11 m 3 0.05 m 2