Influence of clamping on the structural response of aircraft propeller blade

This paper deals with vibration behavior of aircraft propeller blade, which is clamped in its hub assembly. So as, in a fact, this clamping is not absolute, but depending on the blade actual design and operational conditions. The aim of this work is to investigate and show the influence of various possible boundary conditions on the calculated blade natural frequencies at different clamping simplifications. This is useful from the practical engineering point of view, e.g. at the calculations of the turboprop engine coupled vibrations including its prop blades. It allows then do not calculate precise details of the structure, but important part features only. The nonlinear contact in the blade hub is also closely mentioned. Finally, in this paper, the computed results are compared with the measured experimental data.