Investigation of the Difference Between Ordinary and FSI Numerical Solution for Flutter of Tandem Compressor

Abstract

This research aims to analyze and compare the flutter of turbine compressor blades from experimental, numerical, and fluid structure interaction (FSI) derived data. The results proved that the FSI solution results are closer to the experimental results. A reduced velocity parameter of 5 can be regarded as the flutter boundary in the bending flutter. Additionally, the incidence angle parameter equal to 1.5 can be characterized as the torsional flutter boundary. Tandem leads to strengthening the load applied on the compressor blades, reducing the number of compressor stages, and ultimately reducing the weight of the engine. Adding tandem to the rotor increases the vibration bending frequency by a factor of 2. Increasing the compressor velocity caused the FSI vibration frequency to be close to the experimental results. It was found that the vibration range of the main rotor is greater than that of the tandem. The vibration of the rotor and the tandem is damped for approximately 0.1 s to reach a constant frequency.