An analytical model is developed for predicting the onset of supersonic stall bending flutter in axial-flow compressors. The analysis is based on a modified two-dimensional, compressible, unsteady actuator disk theory. It is applied to a rotor blade row by considering a cascade of airfoils whose geometry and dynamic response coincide with those of a rotor blade element at 85 percent of the span height (measured from the hub). The rotor blades are assumed to be unshrouded (i.e., free standing) and to vibrate in their first flexural mode. The effects of shock waves and flow separation are included in the model through quasisteady, empirical, rotor total-pressure-loss and deviation-angle correlations. The actuator disk model predicts the unsteady aerodynamic force acting on the cascade blading as a function of the steady flow field entering the cascade and the geometry and dynamic response of the cascade. Calculations show that the present model predicts the existence of a bending flutter mode at supersonic inlet Mach numbers. This flutter mode is suppressed by increasing the reduced frequency of the system or by reducing the steady-state aerodynamic loading on the cascade. The validity of the model for predicting flutter is demonstrated by correlating the measured flutter boundary of a high-speed fan stage with its predicted boundary. This correlation uses a level of damping for the blade row (i.e., the log decrement of the rotor system) that is estimated from the experimental flutter data. The predicted flutter boundary is shown to be in good agreement with the measured boundary. These results show that the model can be used to estimate the relative stability between operating points of a given rotor system. If, in addition, a measure of the mechanical damping of the rotor system is available, the model can also be used to estimate the absolute stability at an operating point.
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July 1982
This article was originally published in
Journal of Engineering for Power
Research Papers
Supersonic Stall Flutter of High-Speed Fans
J. J. Adamczyk,
J. J. Adamczyk
National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio 44135
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W. Stevans,
W. Stevans
National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio 44135
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R. Jutras
R. Jutras
General Electric Company, Evendale, Ohio 45215
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J. J. Adamczyk
National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio 44135
W. Stevans
National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio 44135
R. Jutras
General Electric Company, Evendale, Ohio 45215
J. Eng. Power. Jul 1982, 104(3): 675-682 (8 pages)
Published Online: July 1, 1982
Article history
Received:
September 25, 1980
Revised:
December 23, 1980
Online:
September 28, 2009
Citation
Adamczyk, J. J., Stevans, W., and Jutras, R. (July 1, 1982). "Supersonic Stall Flutter of High-Speed Fans." ASME. J. Eng. Power. July 1982; 104(3): 675–682. https://doi.org/10.1115/1.3227331
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