Date of Award
Master of Science in Mechanical Engineering (MSME)
A mathematical model is developed and utilized to analyze turbomachine cascade flutter and forced response. The flutter boundary, defined as the largest value of reduced frequency at which flutter occurs for a given cascade, was evaluated for single degree of freedom torsional oscillation as well as coupled bending and torsional oscillations. The maximum amplitude of forced response in bending and torsion was also considered. The unsteady aerodynamic lift and moment coefficients were determined from unsteady aerodynamic flow models for subsonic flow, supersonic flow with a subsonic axial component and supersonic axial flow. The effect of changing the Mach number, stagger angle and spacing-to-chord ratio on cascade stability was evaluated for flutter. Forced response of the cascade was then determined for bending and torsional oscillations.
Clark, Leland Bert, "Turbomachine Stability and Forced Response Prediction" (1992). Open Access Theses. 1239.