J. Phys. III France
Volume 4, Numéro 4, April 1994
Page(s) 783 - 804
DOI: 10.1051/jp3:1994162
J. Phys. III France 4 (1994) 783-804

Flutter control of incompressible flow turbomachine blade rows by splitter blades

Hsiao-Wei D. Chiang and Sanford Fleeter

School of Mechanical Engineering, Purdue University, West Lafayette, Indiana 47907, U.S.A.

(Received 16 June 1993, revised 31 December 1993, accepted 6 January 1994)

Splitter blades as a passive flutter control technique are 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 aerodynamic 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.

© Les Editions de Physique 1994