Forced Response of the Mistuned First Stage Compressor Bladed Disc of an Aircraft Engine-Experimental and Numerical Results

There have been a number of aircraft first stage compressor blade failures. A total of 28 damaged rotor blades have been reported. An experiment was carried out on a first stage rotor blade in the compressor of an aircraft engine at the air force institute of technology in warsaw. The natural frequencies of rotor blades were measured. Next the tip-timing measurement of rotor blade was done in an engine working at various speeds. Various operation conditions were assumed, such as the presence of a foreign object in the engine inlet. Structure and flow calculations were carried out to compare the experimental results. The FEM was used to calculate the natural frequencies of a mistuned bladed disc. The FLUENT code was used to calculate the unsteady forces acting on rotor blades. The mistuned bladed disc was forced to vibrate when rotating at 15000 rpm.