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Analysis of supersonic stall bending flutter in axial-flow compressor by actuator disk theoryAn analytical model was developed for predicting the onset of supersonic stall bending flutter in axial-flow compressors. The analysis is based on two-dimensional, compressible, unsteady actuator disk theory. It is applied to a rotor blade row by considering a cascade of airfoils. The effects of shock waves and flow separation are included in the model. Calculations show that the model predicts the onset, in an unshrouded rotor, of a bending flutter mode that exhibits many of the characteristics of supersonic stall bending flutter. The validity of the analysis for predicting this flutter mode is demonstrated.
Document ID
19790004832
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Adamczyk, J. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1345
E-9186
Accession Number
79N13003
Funding Number(s)
PROJECT: RTOP 510-55
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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