NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Supersonic stall flutter of high-speed fansAn analytical model is proposed for predicting the onset of supersonic stall bending flutter in high-speed rotors. The analysis is based on a modified two-dimensional, compressible, unsteady actuator disk theory. The stability boundary predicted by the analysis is shown to be in good agreement with the measured boundary of a high speed fan. The prediction that the flutter mode would be a forward traveling wave sensitive to wheel speed and aerodynamic loading is confirmed by experimental measurements. In addition, the analysis shows that reduced frequency and dynamic head also play a significant role in establishing the supersonic stall bending flutter boundary of an unshrouded fan.
Document ID
19810045674
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Adamczyk, J. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Stevans, W.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Jutras, R.
(General Electric Co. Evendale, Ohio, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
ASME PAPER 81-GT-184
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: Houston, TX
Start Date: March 9, 1981
End Date: March 12, 1981
Sponsors: American Society of Mechanical Engineers
Accession Number
81A30078
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available