FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW.
Publication
, Conference
Kielb, RE; Ramsey, JK
Published in: American Society of Mechanical Engineers (Paper)
January 1, 1988
An application of a simple aeroelastic model to an advanced supersonic axial flow fan is presented. Lane's cascade theory is used to determine the unsteady aerodynamic loads. Parametric studies are performed to determine the effects of mode coupling, Mach number, damping, pitching axis location, solidity, stagger angle, and mistuning. The results show that supersonic axial flow fan and compressors blades are susceptible to a strong torsional mode flutter having critical reduced velocities which can be less than one.
Duke Scholars
Published In
American Society of Mechanical Engineers (Paper)
ISSN
0402-1215
Publication Date
January 1, 1988
Citation
APA
Chicago
ICMJE
MLA
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Kielb, R. E., & Ramsey, J. K. (1988). FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW. In American Society of Mechanical Engineers (Paper).
Kielb, R. E., and J. K. Ramsey. “FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW.” In American Society of Mechanical Engineers (Paper), 1988.
Kielb RE, Ramsey JK. FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW. In: American Society of Mechanical Engineers (Paper). 1988.
Kielb, R. E., and J. K. Ramsey. “FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW.” American Society of Mechanical Engineers (Paper), 1988.
Kielb RE, Ramsey JK. FLUTTER OF A FAN BLADE IN SUPERSONIC AXIAL FLOW. American Society of Mechanical Engineers (Paper). 1988.
Published In
American Society of Mechanical Engineers (Paper)
ISSN
0402-1215
Publication Date
January 1, 1988