Flutter control of incompressible flow turbomachine blade rows by splitter bladesSplitter blades as a passive flutter control technique is investigated by developing a mathematical model to predict the stability of an aerodynamically loaded splittered-rotor operating in an incompressible flow field. The splitter blades, positioned circumferentially in the flow passage between two principal blades, introduce aerodynamic and/or combined aerodynamic-structural detuning into the rotor. The two-dimensional oscillating cascade unsteady aerodynamics, including steady loading effects, are determined by developing a complete first-order unsteady aerodynamic analysis together with an unsteady aerodynamic influence coefficient technique. The torsion mode flutter of both uniformly spaced tuned rotors and detuned rotors are predicted by incorporating the unsteady aerodyamic influence coefficients into a single-degree-of-freedom aeroelastic model. This model is then utilized to demonstrate that incorporating splitters into unstable rotor configurations results in stable splittered-rotor configurations.
Document ID
19910057022
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chiang, Hsiao-Wei D. (Purdue Univ. West Lafayette, IN, United States)
Fleeter, Sanford (Purdue University West Lafayette, IN, United States)