Supersonic Torsional Flutter in Cascades.
Final technical rept. 16 Feb 72-16 Feb 73,
PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
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A combined analytical and experimental study was made to determine the mechanism of supersonic unstalled torsional flutter in cascades of compressor blades. An unsteady supersonic cascade analysis was used to predict the onset conditions for supersonic torsional flutter. Two sets of blades, characteristic of those used in high-speed fan rotors, were tested to determine the position of the flutter boundary, and the characteristics of the aeroelastic instability. Author Modified Abstract
- Fluid Mechanics
- Jet and Gas Turbine Engines