Abstract
ABSTRACT A frequent cause of turbomachinery rotor blade failure, including jet engines, aircraft engines, and turbogenerators, is excessive vibration due to flutter or forced response. A new system approach analysis will be developed to predict blade flutter and forced response. This analysis will provide a system approach, over and above the standard blade approach, for predicting potential aeroelastic problems. The blade flow field properties are analyzed as system initial input value, combined with finite element model, then to add blade surface subsonic, transonic, and supersonic unsteady forcing function generators and wakes, shock potentials, and inlet distortions in order to calculate turbomachinery blading forced response. The structural dynamic characteristics using experimental methods will be compared with finite element blade model results. This presented method can provide turbine engine manufacturer, co-generation, gas turbine generator, nuclear gas turbine generator, aircraft engine manufacturer, etc. with important analyses system to remedy existing flutter and forced response methods. This proposed research method can also widely use in fans, compressors, and turbines field analysis. Keywords：flutter, forced response, unsteady aerodynamics, turbine, jet engines, aircraft engines