Aeroelastic Stability of Combined Plunge-Pitch Mode Shapes in a Linear Compressor Cascade

Modern aeroengine designs strive for peak specific fuel and thermal efficiency. To achieve these goals, engines have more highly loaded compressor stages, thinner aerofoils, blended titanium integrated disks (blisks) to reduce weight. These configurations promote the occurrence of aeroelastic phenomena such as flutter. Two important parameters known influence flutter stability are reduced frequency ratio plunge pitch components in a combined flap mode shape. used design criteria engine development process. However, limit is not fully understood. The following research aims bridge gap between semi-analytical models modern compressors by systematically investigating linear cascade. This paper introduces plunge-to-pitch incidence ratio, which defined function axis setback first (1F) Using numerical simulations, addition experimental validation, aerodynamic damping computed many modes build maps. results confirm importance two well demonstrate significance predicting limit.